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  • Other Sources  (651)
  • AIRCRAFT PROPULSION AND POWER  (651)
  • 1980-1984  (651)
  • 1950-1954
  • 1925-1929
  • 1983  (199)
  • 1982  (197)
  • 1980  (255)
  • 1
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    Turbine engine materials durability research (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: High temperature environmental attack of dollar intensive turbine components reduces turbine efficiency and can limit life. The mechanisms of alloy and coating attack and the effects of interaction with the environment on mechanical behavior. This base of understanding provides the foundation for developing life prediction methods and identifying strategies for controlling attack. Subjects discussed in detail include oxidation and new developments in thermal barrier coating research.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Advan. Mater. Technol.; p 313-334
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  • 2
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    Identification of multivariable high performance turbofan engine dynamics from closed loop data (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The multivariable instrumental variable/approximate maximum likelihood (IV/AML) method of recursive time-series analysis is used to identify the multivariable (four inputs-three outputs) dynamics of the Pratt and Whitney F100 engine. A detailed nonlinear engine simulation is used to determine linear engine model structures and parameters at an operating point using open loop data. Also, the IV/AML method is used in a direct identification made to identify models from actual closed loop engine test data. Models identified from simulated and test data are compared to determine a final model structure and parameterization that can predict engine response for a wide class of inputs. The ability of the IV/AML algorithm to identify useful dynamic models from engine test data is assessed. Previously announced in STAR as N82-20339
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 3
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    Numerical analysis of a scramjet inlet flow field using the three-dimensional Navier-Stokes equations (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A computer program has been developed to analyze supersonic combustion ramjet (scramjet) inlet flow fields. The program solves the three-dimensional Euler or Navier-Stokes equations in full conservation form by a well-known explicit, predictor-corrector technique. Turbulence is modeled by an algebraic eddy-viscosity model. Detailed laminar and turbulent flow results are presented for a symmetric wedge corner and a comparison is made with the available experimental results to allow assessment of the program. Results are then presented for an actual scramjet inlet configuration.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: APL Computational Methods for Ramjets; p 25-40
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  • 4
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    Numerical study of scramjet and ramjet flow fields (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Two computer programs have been developed to numerically calculate complex, two-dimensional flow fields in scramjets. The first program is written for inlet analysis whereas the second program is written primarily for combustor analysis. Both programs solve the full two-dimensional Navier-Stokes equations by a well-known explicit, predictor-corrector technique. Turbulence is modeled by an algebraic eddy-viscosity model. The combustor program also includes one or more species conservation equations to calculate mixing and reacting flows. The hydrogen/air chemistry in this program is modeled by a complete reaction model. The combustor program has been recently modified to analyze axisymmetric ramjet dump combustor flow field. Results from these computer programs are presented that predict the flow in several scramjet inlet configurations, two model scramjet engine configurations, and in a dump combustor simulator. Computed results are also compared with available experimental data to allow assessment of the programs.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: APL Computational Methods for Ramjets; p 9-24
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  • 5
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    A look into the future: The potential of the all-electric secondary power system for the energy efficient transport (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Materials illustrating a presentation on the all-electric aircraft power system are presented. The advantages of the system and the planning time table are outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Elec. Flight Systems; p 113-124
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  • 6
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    Potential propulsion considerations and study areas for all-electric aircraft (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Materials illustrating a presentation on all-electric aircraft propulsion systems are presented. Propulsion system impacts on aircraft design and areas requiring further study are outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Elec. Flight Systems; p 103-112
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  • 7
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    A propulsion view of the all-electric airplane (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Materials illustrating a presentation on electric propulsion systems are presented. The electric engine and engine/generator configurations are described and NASA's role outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Elec. Flight Systems; p 95-102
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  • 8
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    Rotor wake characteristics relevant to rotor-stator interaction noise generation (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 01, p. 13, Accession no. A82-10456)
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 9
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    JT9D performance deterioration results from a simulated aerodynamic load test (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 3268, Accession no. A81-40963
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: (ISSN 0021-8669)
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  • 10
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    Combustion hot section technology (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The overall objective of the Turbine Engine Hot Section Technology Combustion Project is to develop and verify improved and more accurate analysis methods for increasing the ability to design with confidence the combustion system for advanced aircraft turbine engines. The analysis methods developed will be generically applicable to combustion systems and not restricted to one specific engine or manufacturer. This project's approach was to first assess and evaluate existing combustor aerothermal analysis models by means of a contracted effort initiated during FY 1982. This evaluation effort has assessed and quantified known models' strengths and deficiencies. During FY 1984 the Aerothermal Modeling Program, Phase 2 will be initiated, which is expected to have contracted model development efforts in the areas of improved numerical methods for turbulent viscous flows, flow interactions, and fuel spray flow foekd interactions. A Phase 3 effort is planned to address remaining model deficiencies. The primary inhouse effort in this area will be the determination of high pressure flame radiation characteristics in a full annular combustor. This experiment will be conducted in the NASA LeRC High Pressure Facility with the results compiled into a comprehensive flame radiation and liner heat flux model.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 129-133
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  • 11
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    Validation of structural analysis methods using the in-house liner cyclic rigs (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Test conditions and variables to be considered in each of the test rigs and test configurations, and also used in the validation of the structural predictive theories and tools, include: thermal and mechanical load histories (simulating an engine mission cycle; different boundary conditions; specimens and components of different dimensions and geometries; different materials; various cooling schemes and cooling hole configurations; several advanced burner liner structural design concepts; and the simulation of hot streaks. Based on these test conditions and test variables, the test matrices for each rig and configurations can be established to verify the predictive tools over as wide a range of test conditions as possible using the simplest possible tests. A flow chart for the thermal/structural analysis of a burner liner and how the analysis relates to the tests is shown schematically. The chart shows that several nonlinear constitutive theories are to be evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 335-344
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  • 12
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    Airfoil deposition model (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The methodology to predict deposit evolution (deposition rate and subsequent flow of liquid deposits) as a function of fuel and air impurity content and relevant aerodynamic parameters for turbine airfoils is developed in this research. The spectrum of deposition conditions encountered in gas turbine operations includes the mechanisms of vapor deposition, small particle deposition with thermophoresis, and larger particle deposition with inertial effects. The focus is on using a simplified version of the comprehensive multicomponent vapor diffusion formalism to make deposition predictions for: (1) simple geometry collectors; and (2) gas turbine blade shapes, including both developing laminar and turbulent boundary layers. For the gas turbine blade the insights developed in previous programs are being combined with heat and mass transfer coefficient calculations using the STAN 5 boundary layer code to predict vapor deposition rates and corresponding liquid layer thicknesses on turbine blades. A computer program is being written which utilizes the local values of the calculated deposition rate and skin friction to calculate the increment in liquid condensate layer growth along a collector surface.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 241-257
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  • 13
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    Turbine heat transfer (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Objectives and approaches to research in turbine heat transfer are discussed. Generally, improvements in the method of determining the hot gas flow through the turbine passage is one area of concern, as is the cooling air flow inside the airfoil, and the methods of predicting the heat transfer rates on the hot gas side and on the coolant side of the airfoil. More specific areas of research are: (1) local hot gas recovery temperatures along the airfoil surfaces; (2) local airfoil wall temperature; (3) local hot gas side heat transfer coefficients on the airfoil surfaces; (4) local coolant side heat transfer coefficients inside the airfoils; (5) local hot gas flow velocities and secondary flows at real engine conditions; and (6) local delta strain range of the airfoil walls.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 119-136
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  • 14
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    Laser anemometer optimization (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design, construction, and testing of laser anemometer configurations for hot section velocity measurements is discussed. The optimization of the laser anemometer systems include the data processing algorithms used. Some relevant hot section properties considered are high temperature with a large background radiation, difficulty of optical access, large flow velocity variations, the presence of solid surfaces that generate reflections and low seed particle density.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 113-118
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  • 15
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    Dynamic gas temperature measurement system (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The development of an advanced measuring system which measures the rapidly varying gas temperature at the exit of an aircraft jet engine combustor during ground based testing of hot section components was identified. Sensor guidelines, technical approach/program schedule, and the accomplishments are reviewed. The environment of a present generation combustor is shown. The method uses two beadless junctions type-B thermocouples to measure heat transfer coefficient in situ. Heat conduction effects are shown by a finite element model of the thermocouple.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 75-82
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  • 16
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    Pre-HOST high temperature crack propagation (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The highlights of NASA contract CR-167896, Fracture Mechanics Criteria for Turbine Engine Hot Section Components, are presented. The five technical tasks of the program are reviewed. Results of several tasks are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 55-63
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  • 17
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    HOST instrumentation R and D program overview (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The turbine hot-section technology (HOST) Instrumentation R&D program focuses on two main classes of instrumentation: (1) those that characterizes the environment around the turbine engine components, which include gas flows measurement, gas temperatures, and heat fluxes; (2) to characterize the effect of the environment on the turbine engine components, which include strain measurements and an optical system to structural responses such as cracking, buckling, spalling, carbon buildup. The HOST Instrumentation R&D program concentrates on the critical measurements that can not be made by commercially available instruments or with instruments that are already in development. The measurements of strain and gas flow are emphasized, these measurements are extremely critical to the success of the HOST program and the HOST requirements differ from the current state of the art by a considerable margin.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 65-68
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  • 18
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    Nonlinear structural and life analyses of a combustor liner (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Three-dimensional, nonlinear, finite element structural analyses were performed for a simulated aircraft combustor liner specimen in order to assess the capability of nonlinear analyses using classical inelastic material models to represent the thermoplastic-creep response of the component. In addition, the computed stress-strain history at the critical location was input into life prediction methods in order to evaluate the ability of these procedures to predict crack initiation life. It is concluded that: (1) elastic analysis is adequate for obtaining strain range and critical location; (2) inelastic analyses did not accurately represent cyclic behavior of materials; and (3) none of the crack initiation life prediction methods were satisfactory.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 45-53
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  • 19
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    Nonlinear structural and life analyses of a turbine blade (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The most critical structural requirements that aircraft gas turbine engines must meet result from the diversity of extreme environmental conditions in the turbine section components. Accurate life assessment of the components under these conditions requires sound analytical tools and techniques. The utility of advanced structural analysis techniques and advanced life prediction techniques in the life assessment of hot-section components was evaluated. The extend to which a three-dimensional cyclic isoparametric finite element analysis of a hot-section component would improve the accuracy of component life predictions was assessed. At the same time, high temperature life prediction theories such as strainrange partitioning and the frequency modified approaches were applied and their efficiency judged. A stress analysis was performed on a commercial air-cooled turbine blade. The evaluation of the life prediction methods indicated that none of those studied were satisfactory.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 39-44
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  • 20
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    HOST structural analysis program overview (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Hot section components of aircraft gas turbine engines are subjected to severe thermal structural loading conditions, especially during the start up and take off portions of the engine cycle. The most severe and damaging stresses and strains are those induced by the steep thermal gradients induced during the start up transient. These transient stresses and strains are also the most difficult to predict, in part because of the temperature gradients and distributions are not well known or readily predictable, and also because the cyclic elastic viscoplastic behavior of the materials at these extremes of temperature and strain are not well known or readily predictable. A broad spectrum of structures related technology programs is underway to address these deficiencies. One element of the structures program is developing improved time varying thermal mechanical load models for the entire engine mission cycle from start up to shutdown. Another major part of the program is the development of new and improved nonlinear 3-D finite elements and associated structural analysis programs, including the development of temporal elements with time dependent properties to account for creep effects in the materials and components.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 153-158
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  • 21
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    Combustion system for radiation investigations (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An inlet interface flange, inlet diffuser, fuel struts and nozzles, combustor liner, liner housing and exhaust flange comprise a system to be installed in an existing test facility. The system was designed for operation at 40 atmospheres inlet pressure, 900 K inlet temperature, and air flow to 80 kg/sec. Six penetrations are provided in the outer pressure housing. Adapters at the penetrations, permit use of various types of radiation instrumentation. Five total radiation radiometers and two heat flux gases were installed. Rotating exhaust instrumentation can also be used to determine combustor performance. Data are presented showing total radiation at three axial positions of the combustor, and comparison of total radiation with data from a heat flux gage.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 331-334
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  • 22
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    Aerothermal modeling program (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some significant features of the approach adopted for the combustor aerothermal modeling program are described. The individual computerized models utilized in the aero design approach are characterized. The preliminary design module provides the overall envelope definition of the burner. The diffuser module provides the detailed contours of the diffuser and combustor cowl region, as well as the pressure loss characteristics into each of the individual flow passages into the dome and around the combustor. The flow distribution module provides the air entry quantities through each of the aperatures and the overall pressure drop. The heat transfer module provides detailed metal temperature distribution throughout the metal structure as input to stress and life analysis that are not part of the aerothermo design effort. Finally, the internal flow module, INTFLOW, is described and the approach for model evaluation using laboratory data is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 301-306
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  • 23
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    Effects of surface chemistry on hot corrosion life: Overview (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This program concentrates on analyzing a limited number of hot corroded components from the field and the carrying out of a series of controlled laboratory experiments to establish the effects of oxide scale and coating chemistry on hot corrosion life. This is to be determined principally from the length of the incubation period, the investigation of the mechanisms of hot corrosion attack, and the fitting of the data generated from the test exposure experiments to an empirical life prediction model.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 263-267
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  • 24
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    Combustion hot section technology (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Turbine Engine Hot Section Technology Combustion Program is briefly described. The overall objective of the project is to develop and verify improved and more accurate analysis methods for increasing the ability to design with confidence the combustion system for advanced aircraft turbine engines. The approach is to first assess and evaluate existing combustor aerothermal analysis models by means of a contracted effort initiated during FY-82. The program also includes both analytical and experimental research efforts in the areas of aerothermal modeling and liner cyclic life. It is expected that the combustor model development effort will generate improved understanding in the areas of high pressure flame radiation characteristics, model numerical methods and solution schemes, complex geometrical boundary conditions, fuel spray - flow field interactions, combustion kinetics, flow and mixing of dilution jets, turbulence and heat transfer, and soot and carbon formation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 269-281
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  • 25
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    Aerothermal modeling (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objectives, approach, and status of a program to develop the computational fluid dynamics tools needed to improve combustor design and analysis are outlined. The calculation procedure selected consists of a finite difference solution of the time averaged, steady state, primitive variable, elliptic form of the Reynolds equations. Standard TEACH type numerics are used to solve the resulting equations. These include hybrid differencing, SIMPLE algorithm for the pressure field, line by line iterative solution using the ADI method and the tridiagonal matrix algorithm (TDMA). Convergence is facilitated by using under relaxation. The physical processes are modeled by a two equation eddy viscosity model for turbulence; combustion is represented by a simple, irreversible, one step chemical reaction whose rate is influenced only by the time scale of the turbulence. The model evaluation procedure is also described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 283-299
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  • 26
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    Burner liner thermal/structural load modelling (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objective of this program is to develop a thermal data transfer computer program module for the Burner Liner Thermal-Structural Load Modelling Program. This will be accomplished by reviewing existing methodologies for thermal data transfer and selecting three heat transfer codes for application in this program, evaluating the selected codes to establish criteria for developing a computer program module to transfer thermal data from the heat transfer codes to selected stress analysis codes, developing the automated thermal load transfer module, and verifying and documenting the module. The overall objectives of this thermal transfer module are that it handle independent mesh configurations, perform the transfer in an accurate and efficient fashion and that the total system be flexible for future improvements.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 185-196
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  • 27
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    Structural analysis (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Hot section components of aircraft gas turbine engines are subjected to severe thermal-structural loading conditions, especially during the start-up and take-off portions of the engine cycle. The most severe and damaging stresses and strains are those induced by the steep thermal gradients induced during the start-up transient. These transient stresses and strains are also the most difficult to predict, in part because the temperature gradients and distributions are not well known or predictable, and also because the cyclic elasto-viscoplastic behavior of the materials at these extremes of temperature and strain are not well known or predictable. One element of the structures program will develop improved time-varying thermal-mechanical load models for the entire engine mission cycle from start-up to shutdown. The thermal model refinements will be consistent with those required by the structural code including considerations of mesh-point density, strain concentrations, and thermal gradients. Models will be developed for the burner liner, turbine vane and turbine blade.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 181-184
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  • 28
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    Coolant passage heat transfer with rotation (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Although the effects of the coriolis and buoyancy forces due to rotation on coolant-side heat transfer are generally not included in the design methods for blades, the influence of these forces could be large. Comparisons of nonrotating heat transfer data and extrapolations of available correlation for the average heat transfer coefficients with radial outflow of cooling air showed that neglecting rotation at gas turbine engine conditions result in variations in the heat transfer coefficient by as much as 45 percent. This, in effect, results in blade metal temperatures running as much as 100 F different from predicted values. This also may explain why rotating blade metal temperatures in engine tests are often higher than expected from results obtained in nonrotating cascade tests.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 175-179
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  • 29
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    Jet array impingement flow distributions and heat transfer characteristics: Effects of initial crossflow and nonuniform array geometry (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flow distributions and heat transfer characteristics for two-dimensional arrays of circular air jets impinging on a surface parallel to the jet orifice plate were determined. The configurations considered were intended to model those of interest in current and contemplated gas turbine airfoil midchord cooling applications. The geometry of the airfoil applications considered dictates that all of the jet flow, after impingement, exit in the chordwise (i.e., streamwise) direction toward the trailing edge. Experimental results for the effect of an initial crossflow on both flow distributions and heat transfer characteristics for a number of the prior uniform array geometries. The effects of nonuniform array geometries on flow distributions and heat transfer characteristics for noninitial crossflow configurations are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 161-173
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  • 30
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    Gas side heat transfer: 2-D flow (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Significant progress was made in advancing the idea of establishing a unified approach for predicting airfoil heat transfer for a wide range of operating conditions and geometries. Preliminary results are encouraging and further mixing length (ml) turbulence modeling ideas will be explored, concentrating on transition behavior. The capability of available modeling techniques to predict airfoil surface heat transfer distributions in a two-dimensional flow field was assessed, experimental data as required for model verification were acquired, and improvements in the analytic models was made and verified.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 137-147
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  • 31
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    Gas flow environment and heat transfer nonrotating 3D program (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A complete set of benchmark quality data for the flow and heat transfer within a large rectangular turning duct is provided. These data are to be used to evaluate, and verify, three-dimensional internal viscous flow models and computational codes. The analytical contract objective is to select a computational code and define the capabilities of this code to predict the experimental results obtained. Details of the proper code operation will be defined and improvements to the code modeling capabilities will be formulated. Internal flow in a large rectangular cross-sectioned 90 deg. bend turning duct was studied. The duct construction was designed to allow detailed measurements to be made for the following three duct wall conditions: (1) an isothermal wall with isothermal flow; (2) an adiabatic wall with convective heat transfer by mixing between an unheated surrounding flow; and (3) an isothermal wall with heat transfer from a uniformly hot inlet flow.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 149-159
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    Hot section laser anemometry (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objectives and problems faced in the development of a laser anemometry system for hot section applications was discussed. The goal was to map the flow profiles through and between the vanes and between the rotating blades of a turbine. A laser anemometer system was developed which measures the Doppler shift directly along the optical axis. Some testing is being conducted in a small bench top combustor facility. The cost involved in this testing was also discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 109-112
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  • 33
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    Heat flux sensors for burner liners and turbine blades and vanes (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The technology of heat flux measurement is addressed. The development of total heat flux sensors for burner liners and also the demonstration of total and radiant heat flux sensors in a combustor test is covered. A thorough review of potential approaches is conducted including both transient and steady state measurements. Measurement of total heat flux was emphasized, consequently configurations are sought which produce minimum disturbance to the heat flux which would be present without the sensor in place. Approaches to the turbine blade and vane heat flux sensor program are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 101-108
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  • 34
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    Preparing aircraft propulsion for a new era in energy and the environment (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Improving fuel efficiency, new sources of jet fuel, and noise and emission control are subjects of NASA's aeronautics program. Projects aimed at attaining a 5% fuel savings for existing engines and a 13-22% savings for the next generation of turbofan engines using advanced components, and establishing a basis for turboprop-powered commercial air transports with 30-40% savings over conventional turbofan aircraft at comparable speeds and altitudes, are discussed. Fuel sources are considered in terms of reduced hydrogen and higher aromatic contents and resultant higher liner temperatures, and attention is given to lean burning, improved fuel atomization, higher freezing-point fuel, and deriving jet fuel from shale oil or coal. Noise sources including the fan, turbine, combustion process, and flow over internal struts, and attenuation using acoustic treatment, are discussed, while near-term reduction of polluting gaseous emissions at both low and high power, and far-term defining of the minimum gaseous-pollutant levels possible from turbine engines are also under study.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 18; Jan. 198
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  • 35
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    Engine technology (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Materials used in a presentation on development of engine technology for electric flight systems are presented. Component and system technology issues, NASA's role, and flight test requirements are outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Elec. Flight Systems; p 235-240
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  • 36
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    Digital electronic engine control system - F-15 flight test (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 19, p. 3268, Accession no. A81-40912)
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 37
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    Subsonic/supersonic aeropropulsive characteristics of nonaxisymmetric nozzles installed on an F-18 model (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 3266, Accession no. A81-40878
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: (ISSN 0021-8669)
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  • 38
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    Advanced electrical power system technology for the all electric aircraft (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The application of advanced electric power system technology to an all electric airplane results in an estimated reduction of the total takeoff gross weight of over 23,000 pounds for a large airplane. This will result in a 5 to 10 percent reduction in direct operating costs (DOC). Critical to this savings is the basic electrical power system component technology. These advanced electrical power components will provide a solid foundation for the materials, devices, circuits, and subsystems needed to satisfy the unique requirements of advanced all electric aircraft power systems. The program for the development of advanced electrical power component technology is described. The program is divided into five generic areas: semiconductor devices (transistors, thyristors, and diodes); conductors (materials and transmission lines); dielectrics; magnetic devices; and load management devices. Examples of progress in each of the five areas are discussed. Bipolar power transistors up to 1000 V at 100 A with a gain of 10 and a 0.5 microsec rise and fall time are presented. A class of semiconductor devices with a possibility of switching up to 100 kV is described. Solid state power controllers for load management at 120 to 1000 V and power levels to 25 kW were developed along with a 25 kW, 20 kHz transformer weighing only 3.2 kg. Previously announced in STAR as N83-24764
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 39
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    Development and operating characteristics of an advanced two-stage combustor (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 06, p. 813, Accession no. A82-17833
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: (ISSN 0146-0412)
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  • 40
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    Turbine blade nonlinear structural and life analysis (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 17, p. 2687, Accession no. A82-34981
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: (ISSN 0021-8669)
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  • 41
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    Design and development of a mixer compound exhaust system (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 22, p. 3815, Accession no. A81-45893)
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 42
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    Effect of variable guide vanes on the performance of a high-bypass turbofan engine (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 19, p. 3265, Accession no. A81-40842)
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 43
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    Turbofan engine blade pressure and acoustic radiation at simulated forward speed (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 07, p. 1010, Accession no. A81-20598)
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 44
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    NASA/General Electric Broad-Specification Fuels Combustion Technology Program - Phase I. (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 17, p. 2687, Accession no. A82-35000
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Journal of Energy (ISSN 0146-0412); 7; 508-517
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  • 45
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    A piecewise linear state variable technique for real time propulsion system simulation (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The emphasis on increased aircraft and propulsion control system integration and piloted simulation has created a need for higher fidelity real time dynamic propulsion models. A real time propulsion system modeling technique which satisfies this need and which provides the capabilities needed to evaluate propulsion system performance and aircraft system interaction on manned flight simulators was developed and demonstrated using flight simulator facilities at NASA Ames. A piecewise linear state variable technique is used. This technique provides the system accuracy, stability and transient response required for integrated aircraft and propulsion control system studies. The real time dynamic model includes the detail and flexibility required for the evaluation of critical control parameters and propulsion component limits over a limited flight envelope. The model contains approximately 7.0 K bytes of in-line computational code and 14.7 K of block data. It has an 8.9 ms cycle time on a Xerox Sigma 9 computer. A Pegasus-Harrier propulsion system was used as a baseline for developing the mathematical modeling and simulation technique. A hydromechanical and water injection control system was also simulated. The model was programmed for interfacing with a Harrier aircraft simulation at NASA Ames. Descriptions of the real time methodology and model capabilities are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 46
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    HOST liner cyclic facilities: Facility description (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A quartz lamp box, a quartz lamp annular rig, and a low pressure liner cyclic can rig planned for liner cyclic tests are described. Special test instrumentation includes an IR-TV camera system for measuring liner cold side temperatures, thin film thermocouples for measuring liner hot side temperatures, and laser and high temperature strain gages for obtaining local strain measurements. A plate temperature of 2,000 F was obtained in an initial test of an apparatus with three quartz lamps. Lamp life, however, appeared to be limited for the standard commercial quartz lamps available. The design of vitiated and nonvitiated preheaters required for the quartz lamp annular rig and the cyclic can test rigs is underway.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 345-360
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  • 47
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    Dilution jet mixing (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Schematics are given for test section configurations, orifice configurations, and the dilution jet mixing test rig used to collect a data base on mixing a single sided and a two sided row of jets with a confined cross flow. Parameters investigated include momentum ratio; nonuniform cross stream temperature and velocity profiles; cold/hot injection, and cross stream flow area convergence. Graphs show measured theta momentum distributions for: (1) in line and staggered orifice configurations; and (2) the profiled mainstream; and (3) flow area convergence.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 315-329
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  • 48
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    Laser speckle technique for burner liner strain measurements (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Thermal and mechanical strains were measured on samples of a common material used in jet engine burner liners, which were heated from room temperature to 870 C and cooled back to 220 C, in a laboratory furnance. The physical geometry of the sample surface was recorded at selected temperatures by a set of 12 single exposure speckle-grams. Sequential pairs of specklegrams were compared in a heterodyne interferometer which give high precision measurement of differential displacements. Good speckle correlation between the first and last specklegrams is noted which allows a check on accumulate errors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 93-99
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  • 49
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    Dilution zone mixing studies (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objectives and status of a project to investigate various aspects of the jet in a confined cross flow problem are outlined. The experiments performed thus far dealt primarily with a single row of jets mixing into an isothermal flow in a constant cross section duct. Variations in the mixing were observed as a function of jet to mainstream momentum ratio, orifice size, and spacing. The current experiments examine perturbations of this problem characteristic to gas turbine combustion chambers, namely: flow area convergence, nonisothermal mainstream flow, and opposed in line and staggered injection. An empirical model was developed to describe the observed temperature distributions. The current interactive code provides a 3-D pictorial representation of the temperature, as given by these correlations, for any user specified downstream location, flow, and orifice parameters.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 307-314
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  • 50
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    Surface protection overview (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A first-cut integrated environmental attack life prediction methodology for hot section components is addressed. The HOST program is concerned with oxidation and hot corrosion attack of metallic coatings as well as their degradation by interdiffusion with the substrate. The effects of the environment and coatings on creep/fatigue behavior are being addressed through a joint effort with the Fatigue sub-project. An initial effort will attempt to scope the problem of thermal barrier coating life prediction. Verification of models will be carried out through benchmark rig tests including a 4 atm. replaceable blade turbine and a 50 atm. pressurized burner rig.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 231-239
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  • 51
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    HOST high temperature crack propagation (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Methods for characterizing and predicting crack growth at elevated temperatures are discussed. Nonlinear behavior, thermal gradients, and thermomechanical cycling are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 227-229
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  • 52
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    Life prediction and constitutive models for anisotropic materials (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The intent of this program is to develop a basic understanding of cyclic creep-fatigue deformation mechanisms and damage accumulation, a capability for reliable life prediction, and the ability to model the constitutive behavior of anisotropic single crystal (SC) and directionally solidified or recrystallized (DSR) comprise the program, and the work breakdown for each option reflects a distinct concern for two classes of anisotropic materials, SC and DSR materials, at temperatures encountered in the primary gas path (airfoil temperatures), and at temperatures typical of the blade root attachment and shank area. Work directed toward the higher temperature area of concern in the primary gas path includes effects of coatings on the behavior and properties of the materials of interest. The blade root attachment work areas will address the effects of stress concentrations associated with attachment features.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 223-226
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  • 53
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    Constitutive model development for isotropic materials (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objective is to develop a unified constitutive model for finite-element structural analysis of turbine engine hot section components. This effort constitutes a different approach for nonlinear finite-element computer codes which were heretofore based on classical inelastic methods. A unified constitutive theory will avoid the simplifying assumptions of classical theory and should more accurately represent the behavior of superalloy materials under cyclic loading conditions and high temperature environments. Model development will be directed toward isotropic, cast nickel-base alloys used for aircooled turbine blades and vanes. The contractor will select a base material for model development and an alternate material for verification purposes from a list of three alloys specified by NASA. The candidate alloys represent a cross-section of turbine blade and vane materials of interest to both large and small size engine manufacturers. Material stock for the base and alternate materials will be supplied to the Contractor by the government.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 215-221
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  • 54
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    Life prediction and constitutive behavior: Overview (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The evolution of programs to investigate high temperature consititutive behavior and develop cyclic life prediction methods is reviewed. Contracts granted for developing and verifying workable engineering methods for the calculation, in advance of service, of the local stress-strain response at the critical life governing location in typical hot section components as well as the resultant cyclic crack initiation and crack growth lifetimes are listed. The Langley fatigue facility is being upgraded to include: (1) a servocontrolled testing machine for high temperature crack growth; (2) three servocontrolled tension/torsion machines for biaxial studies; (3) a HOST/satellite computer for data acquisition, processing, storage, and retrieval; and (4) HCV/LCF machines for cumulative damage studies.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 209-212
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  • 55
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    Creep-fatigue life prediction for engine hot section materials (isotropic) (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objectives of this program are the investigation of fundamental approaches to high temperature crack initiation life prediction, identification of specific modeling strategies and the development of specific models for component relevant loading conditions. A survey of the hot section material/coating systems used throughout the gas turbine industry is included. Two material/coating systems will be identified for the program. The material/coating system designated as the base system shall be used throughout Tasks 1-12. The alternate material/coating system will be used only in Task 12 for further evaluation of the models developed on the base material. In Task II, candidate life prediction approaches will be screened based on a set of criteria that includes experience of the approaches within the literature, correlation with isothermal data generated on the base material, and judgements relative to the applicability of the approach for the complex cycles to be considered in the option program. The two most promising approaches will be identified. Task 3 further evaluates the best approach using additional base material fatigue testing including verification tests. Task 4 consists of technical, schedular, financial and all other reporting requirements in accordance with the Reports of Work clause.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 213-214
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  • 56
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    The 3-D inelastic analysis methods for hot section components: Brief description (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Advanced 3-D inelastic structural/stress analysis methods and solution strategies for more accurate yet more cost-effective analysis of components subjected to severe thermal gradients and loads in the presence of mechanical loads, with steep stress and strain gradients are being developed. Anisotropy, time and temperature dependent plasticity and creep effects are also addressed. The approach is to develop four different theories, one linear and three higher order theories (polynomial function, special function, general function). The theories are progressively more complex from linear to general function in order to provide streamlined analysis capability with increasing accuracy for each hot section component and for different parts of the same component according to the severity of the local stress, strain and temperature gradients associated with hot spots, cooling holes and surface coating cracks. To further enhance the computational effectiveness, the higher order theories will have embedded singularities (cooling passages, for example) in the generic modeling region. Each of the four theories consists of three formulation models derivable from independent theoretical formulations. These formulation models are based on: (1) mechanics of materials; (2) special finite elements; and (3) an advanced formulation to be recommended by the contractor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 203-208
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  • 57
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    Component-specific modeling (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The ability to accurately structurally analyze engine components to assure that they can survive for their designed lifetime in an increasingly harsh environment is discussed. Under the HOST (HOt Section Technology) program, advanced component-specific modeling methods, with built-in analysis capability, will be developed separately for burner liners, turbine blades and vanes. These modeling methods will make maximum use of, but will not rely solely on, existing analysis methods and techniques, to analyze the three identified components. Nor will the complete structural analysis of a component necessarily be performed as a single analysis. The approach to be taken will develop complete software analysis packages with internal, component-specific, self-adaptive solution strategies. Each package will contain a set of modeling and analysis tools. The selection and order of specific methods and techniques within the set to be applied will depend on the specific-component, the current thermo-mechanical loading, and the current state of the component. All modeling and analysis decisions will be made internally based on developed decision criteria within the solution strategies; minimal user intervention will be required.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 197-202
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  • 58
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    Equivalent damage: A critical assessment (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The overall goal of achieving improved life cycle management of aircraft engine, gas turbine components is a major industry thrust. Low cycle fatigue (LCF) crack initiation prediction, an important element of life cycle management as traditionally applied, may be overly conservative in estimating total cyclic life capability. Consequently, there is increasing pressure to improve predictive methods both for crack initiation and for subsequent crack propagation. The utility of equivalent damage concepts for application to hot section components of aircraft engines was studied. Specifically, the topics examined were mean stress, cumulative damage, and multiaxiality. Other factors inherently linked to this study were the basic formulation of damage parameters at elevated temperatures and the fact that hot section components experience severe temperature fluctuations throughout their service lifetime.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 11-23
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  • 59
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    Benchmark notch test for life prediction (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Aircraft gas turbine engine components are subjected to severe stress, temperature, and environmental conditions. Economic and reliabilty demands have prompted inordinate effort in development of analytic methods to predict stresses and strains in aircraft engines. There remains, however, the need to check or verify these analytical methodologies against actual experimental data measurements. The laser interferometric strain displacement gage was recognized as having the potential to accomplish this task and was employed in this program. The actual strains incurred at the root of a discontinuity in cyclically loaded test samples subjected to inelastic deformation at high temperature where creep deformation readily occur were measured. The steady-state, cyclic stress-strain response at the root of the discontinuity in the tested samples was analyzed for comparison with the measured results. A comprehensive set of local notch root strain measurements for a variety of load patterns in an Inconel 718 notch specimen at 649 C (1200 F) was obtained and documented using the laser interferometric strain displacement gage.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 25-37
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  • 60
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    End-wall boundary layer measurements in a two-stage fan (1983)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Detailed flow measurements made in the casing boundary layer of a two-stage transonic fan are summarized. These measurements were taken at stations upstream of the fan, between all blade rows, and downstream of the last blade row. At the design tip speed of 429 m/sec the fan achieved a peak efficiency of 0.846 at a pressure ratio of 2.471. The boundary layer data were obtained at three weight flows at the design speed: one near choke flow, one near peak efficiency, and one near stall. Conventional boundary layer parameters were calculated from the data measured at each measuring station for each of the three flows. A classical two dimensional casing boundary layer was measured at the fan inlet and extended inward to approximately 15 percent of span. A highly three dimensional boundary layer was measured at the exit of each blade row and extended inward to approximately 10 percent of span. The steep radial gradient of axial velocity noted at the exit of the rotors was reduced substantially as the flow passed through the stators. This reduced gradient is attributed to flow mixing. The amount of flow mixing was reflected in the radial redistribution of total temperature as the flow passed through the stators. The data also show overturning of the tip flow at the stator exits that is consistent with the expected effect of the secondary flow field. The blockage factors calculated from the measured data show an increase in blockage across the rotors and a decrease across the stators.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Viscous Effects in Turbomachines; 23 p
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  • 61
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    State-of-the-art SiAlON materials (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The state of the art of SiAlONs is examined. The review includes work on phase relations, crystal structure, synthesis, fabrication, and properties of various SiAlONs. The essential features of compositions, fabrication methods, and microstructure are reviewed. High temperature flexure strength, creep, fracture toughness, oxidation, and thermal shock resistance are discussed. These data are compared to those for some currently produced silicon nitride ceramics to assess the potential of SiAlON materials for use in advanced gas turbine engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Ceram. for Turbine Eng. Appl.; 15 p
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  • 62
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    Space shuttle main engine digital controller (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The controller provides responsive control of engine thrust and mixture ratio through the digital computer in the controller, updating the instructions to the engine control elements 50 times per second (every 20 milliseconds). Additionally, precise engine performance is achieved through closed loop control, utilizing 16 bit computation, 10 bit input/output resolution, and self calibrating analog-to-digital conversion. Engine reliability is enhanced by a dual redundant control system that allows normal operation after the first failure and a fail-safe shutdown after a second failure. The digital computer is programmable, allowing modification of engine control equations and constants by change of the stored program (software). The controller is packaged in a sealed, pressurized chassis with cooling provided by convection heat transfer through pin fins as part of the main chassis. The electronics are distributed on functional modules having special provisions for thermal and vibrational protection.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Advan. Control Systems for Aircraft Powerplants; 11 p
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    Design, evaluation and test of an electronic, multivariable control for the F100 turbofan engine (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A digital, multivariable control design procedure for the F100 turbofan engine is described. The controller is based on locally linear synthesis techniques using linear, quadratic regulator design methods. The control structure uses an explicit model reference form with proportional and integral feedback near a nominal trajectory. Modeling issues, design procedures for the control law and the estimation of poorly measured variables are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Advan. Control Systems for Aircraft Powerplants; 21 p
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  • 64
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    Computerized systems analysis and optimization of aircraft engine performance, weight, and life cycle costs (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The computational techniques are described which are utilized at Lewis Research Center to determine the optimum propulsion systems for future aircraft applications and to identify system tradeoffs and technology requirements. Cycle performance, and engine weight can be calculated along with costs and installation effects as opposed to fuel consumption alone. Almost any conceivable turbine engine cycle can be studied. These computer codes are: NNEP, WATE, LIFCYC, INSTAL, and POD DRG. Examples are given to illustrate how these computer techniques can be applied to analyze and optimize propulsion system fuel consumption, weight and cost for representative types of aircraft and missions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD The Use of Computers as a Design Tool; 15 p
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  • 65
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    Performance seeking controls (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A performance logic algorithm (PSL) was developed to optimize the performance of propulsion systems for component and sensor degradations by monitoring the performance of the engine system and minimizing thrust specific fuel consumption (TSFC) while retaining a constant engine net thrust. Engine constraints such as surge margin, speed, pressure, and temperature are observed. The PSL algorithm was applied to the quiet, clean, short haul experimental engine. Engine control set points were modified for component degradations in order to restore the nominal net thrust. Results show convergence to the optimum value can be obtained within 60 to 90 seconds, which makes the program acceptable to on line operation with present state of the art minicomputers. Tests indicate that in most cases the PSL algorithm offers some improvement in thrust specific fuel consumption over the manual throttle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 11-17
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  • 66
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    Multivarable nyquist array method with application to turbofan engine control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Extensions to the multivariable Nyquist array (MNA) method are used to design a feedback control system for the quiet clean shorthaul experimental engine. The results of this design are compared with those obtained from the deployment of an alternate control system design on a full scale nonlinear, real time digital simulation. The results clearly demonstrate the utility of the MNA synthesis procedures for highly nonlinear sophisticated design applications.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 105-110
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  • 67
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    Propulsion controls (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Increased system requirements and functional integration with the aircraft have placed an increased demand on control system capability and reliability. To provide these at an affordable cost and weight and because of the rapid advances in electronic technology, hydromechanical systems are being phased out in favor of digital electronic systems. The transition is expected to be orderly from electronic trimming of hydromechanical controls to full authority digital electronic control. Future propulsion system controls will be highly reliable full authority digital electronic with selected component and circuit redundancy to provide the required safety and reliability. Redundancy may include a complete backup control of a different technology for single engine applications. The propulsion control will be required to communicate rapidly with the various flight and fire control avionics as part of an integrated control concept.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 49-59
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  • 68
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    VCE test bed engine for supersonic cruise research (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Various design concepts for a variable cycle engine applicable to a supersonic, mixed mission propulsion system which would combine the merits of a turbofan at subsonic operating conditions with those of a turbojet for supersonic operating conditions are briefly examined. In particular the integration of the variable area bypass injector with the core driven (aft fan block) fan stage is discussed and the technical benefits of the configuration are summarized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Supersonic Cruise Res. 1979, Pt. 1; p 347-356
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  • 69
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    Preliminary design of a supersonic cruise aircraft high-pressure turbine (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Development of the supersonic cruise aircraft engine continued in this National Aeronautics and Space Administration (NASA) sponsored Pratt and Whitney program for the Preliminary Design of an Advanced High-Pressure Turbine. Airfoil cooling concepts and the technology required to implement these concepts received particular emphasis. Previous supersonic cruise aircraft mission studies were reviewed and the Variable Stream Control Engine (VSCE) was chosen as the candidate or the preliminary turbine design. The design was evaluated for the supersonic cruise mission. The advanced technology to be generated from these designs showed benefits in the supersonic cruise application and subsonic cruise application. The preliminary design incorporates advanced single crystal materials, thermal barrier coatings, and oxidation resistant coatings for both the vane and blade. The 1990 technology vane and blade designs have cooled turbine efficiency of 92.3 percent, 8.05 percent Wae cooling and a 10,000 hour life. An alternate design with 1986 technology has 91.9 percent efficiency and 12.43 percent Wae cooling at the same life. To achieve these performance and life results, technology programs must be pursued to provide the 1990's technology assumed for this study.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-174878 , NAS 1.26:174878 , PWA-5923-14
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  • 70
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    Turbofan aft duct suppressor study program listing and user's guide (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A description of the structure of the Annular Flow Duct Program (AFDP) for the calculation of acoustic suppression due to treatment in a finite length annular duct carrying sheared flow is presented. Although most appropriate for engine exhaust ducts, this program can be used to study sound propagation in any duct that maintains annular geometry over a considerable length of the duct. The program is based on the modal analysis of sound propagation in ducts with axial segments of different wall impedances. For specified duct geometry, wall impedance, flow and acoustic conditions in the duct (including mode amplitude distribution of the source) and duct termination reflection characteristics, the program calculates the suppression due to the treatment in the duct. The presence of forward and backward traveling modes in the duct due to the reflection and redistribution of modes at segment interfaces and duct end terminations are taken into account in the calculations. The effects of thin wall boundary layers (with a linear or mean flow velocity profile) on the acoustic propagation are also included in the program. A functional description of the major subroutines is included and a sample run is provided with an explanation of the output.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-175067 , NAS 1.26:175067
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  • 71
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    Fuel system technology overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Fuel system research and technology studies are being conducted to investigate the correlations and interactions of aircraft fuel system design and environment with applicable characteristics of the fuel. Topics include: (1) analysis of in-flight fuel temperatures; (2) fuel systems for high freezing point fuels; (3) experimental study of low temperature pumpability; (4) full scale fuel tank simulation; and (5) rapid freezing point measurement.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 195-203
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  • 72
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    Combustion technology overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An overview of combustor technology developments required for use of broadened property fuels in jet aircraft is presented. The intent of current investigations is to determine the extent to which fuel properties can be varied, to obtain a data base of combustion - fuel quality effects, and to determine the trade-offs associated with broadened property fuels. Subcomponents of in-service combustors such as fuel injectors and liners, as well as air distributions and stoichiometry, are being altered to determine the extent to which fuel flexibility can be extended. Finally, very advanced technology consisting of new combustor concepts is being evolved to optimize the fuel flexibility of gas turbine combustors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 67-73
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  • 73
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    Fuels research: Fuel thermal stability overview (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Alternative fuels or crude supplies are examined with respect to satisfying aviation fuel needs for the next 50 years. The thermal stability of potential future fuels is discussed and the effects of these characteristics on aircraft fuel systems are examined. Advanced fuel system technology and design guidelines for future fuels with lower thermal stability are reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 161-168
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  • 74
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    Preliminary studies of combustor sensitivity to alternative fuels (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Combustion problems associated with using alternative fuels ground power and aeropropulsion applications were studied. Rectangular sections designed to simulate large annular combustor test conditions were examined. The effects of using alternative fuels with reduced hydrogen content, increased aromatic content, and a broad variation in fuel property characteristics were also studied. Data of special interest were collected which include: flame radiation characteristics in the various combustor zones; the correponding increase in liner temperature from increased radiant heat flux; the effect of fuel bound nitrogen on oxides of nitrogen (NO sub x) emissions; and the overall total effect of fuel variations on exhaust emissions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels; p 153-160
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  • 75
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    Outlook for alternative energy sources (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Predictions are made concerning the development of alternative energy sources in the light of the present national energy situation. Particular emphasis is given to the impact of alternative fuels development on aviation fuels. The future outlook for aircraft fuels is that for the near term, there possibly will be no major fuel changes, but minor specification changes may be possible if supplies decrease. In the midterm, a broad cut fuel may be used if current development efforts are successful. As synfuel production levels increase beyond the 1990's there may be some mixtures of petroleum-based and synfuel products with the possibility of some shale distillate and indirect coal liquefaction products near the year 2000.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 5-9
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  • 76
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    F100 exhaust nozzle area control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The details of the F100 nozzle mechanism design are highlighted, placing particular emphasis upon the evolution of design constraints or drivers from initial concept through current operational deployment. A kinematic description of the area control mechanism is given, and several environmental constraints which complicate the normal mechanism design process are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center Proc. of the 14th Aerospace Mech. Symp.; p 211-223
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  • 77
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    Positive displacement type general-aviation engines: Summary and concluding remarks (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The activities of programs investigating various aspects of aircraft internal combustion engines are briefly described including developments in fuel injection technology, cooling systems and drag reduction, turbocharger technology, and stratified-charge rotary engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 313-314
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  • 78
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    Advanced rotary engine studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A review of rotary engine developments relevant to a stratified charge rotary aircraft engine is presented. Advantages in module size and weight, fuel efficiency, reliability, and multi-fuel capability are discussed along with developments in turbocharging, increased mean effective pressure, improved apex seal/trochoid wear surfacing materials, and high strength and temperature aluminum casting alloys. A carbureted prototype aircraft engine is also described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 287-311
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  • 79
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    AiResearch QCGAT engine: Acoustic test results (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The noise levels of the quiet, general aviation turbofan (QCGAT) engine were measured in ground static noise tests. The static noise levels were found to be markedly lower than the demonstrably quiet AiResearch model TFE731 engine. The measured QCGAT noise levels were correlated with analytical noise source predictions to derive free-field component noise predictions. These component noise sources were used to predict the QCGAT flyover noise levels at FAR Part 36 conditions. The predicted flyover noise levels are about 10 decibels lower than the current quietest business jets.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 65-100
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  • 80
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    High-freezing-point fuel studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Considerable progress in developing the experimental and analytical techniques needed to design airplanes to accommodate fuels with less stringent low temperature specifications is reported. A computer technique for calculating fuel temperature profiles in full tanks was developed. The computer program is being extended to include the case of partially empty tanks. Ultimately, the completed package is to be incorporated into an aircraft fuel tank thermal analyser code to permit the designer to fly various thermal exposure patterns, study fuel temperatures versus time, and determine holdup.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 205-219
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  • 81
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    Fuel/engine/airframe tradeoff study, phase 1 (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effects of broadening the specifications for JP-4 and JP-8 fueled on the performance and cost of all USAF aircraft presently using JP-4 as well as those expected to be introduced into the force structure by 1983 are investigated. Test results indicated that there was no impact on engine performance, turbine durability, and coking, however there was a small maintenance cost increase as a result of a small combustor life decrease. Using JP-4 as standard fuel will avoid the use of high demand middle distillate fuels and give producers flexibility. Extensive use of JP-8 in the United States will increase middle distillate demand and cause a slight increase in engine hot-section maintenance. It is also concluded that the maximum allowable freeze point of JP-4 or JP-8 cannot be increased without degrading system performance and safety as critical conditions are approached.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 41-47
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  • 82
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    Current jet fuel trends (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Data concerning the properties of commercial jet fuels during the period between 1974 and 1979 are discussed. During this period the average aromatics content of fuels increased from 16% to 17.5%. It is evident that the arrival of Alaska North Slope crude in 1977 had a significant impact upon the aromatics content of jet fuel supply at West Coast points with less effect upon the entire United States domestic market. This increase in aromatics has not been accompanied by a corresponding reduction in burning quality as measured by smoke point. There has been a reduction of .6 smoke point on the average. Looking at hydrogen content as a measure of burning quality, the all refinery average calculated hydrogen for 1978 was approximately 13.7%. The relationship between hydrogen content and aromatics content shows a slope of .043% reduction in hydrogen for 1% increase in aromatics.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 11-14
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  • 83
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    NASA/General Electric broad-specification fuels combustion technology program, phase 1 (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of broad specification fuels in aircraft turbine engine combustion systems was examined. Three different combustor design concepts were evaluated for their ability to use broad specification fuels while meeting several specific emissions, performance, and durability goals. These combustor concepts covered a range from those having limited complexity and relatively low technical risk to those having high potential for achieving all of the program goals at the expense of increased technical risk.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 109-113
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  • 84
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    Air Force fuel mainburner/turbine effects programs (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A program for the determination of fuel property effects on aircraft gas turbine engine mainburners and turbines is discussed. The six engines selected as test candidates are the J79, J85, J57, TF30, TF39, and F100. Fuels election is the responsibility of the contractors with two fuels as exceptions. The petroleum JP-4 is to be used as a baseline in all tests. The shale JP-4 is to be used in nearly all tests. Fuel properties are to be correlated with combustion system performance paramters. In addition, life predictions are to be made for combustor and turbine hardware. These predictions are to be based on a typical mission for each system, measured metal temperatures and temperature gradients, and oxidation/corrosion effects.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 99-103
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  • 85
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    The broadened-specification fuels combustion technology program at Pratt and Whitney Aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The impact of the use of broadened specification fuels on combustor design was investigated. Particular emphasis was placed on establishing the viability of various combustor modifications to permit the use of broadened specification fuels while meeting exhaust emissions and performance specifications and maintaining acceptable combustor operational and durability characteristics. Three different combustor concepts will be evaluated. Various design modifications on the operating capability of each of the combustor concepts with experimental referee broadened specification Fuel. The modifications that were evaluated included perturbations of the combustor airflow schedules to alter local stoichiometry and residence time histories revisions to the fuel injectors, and variations in liner cooling including the use of thermal barrier coatings and/or advanced cooling concepts.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 105-108
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  • 86
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    An overview of NASA research on positive displacement general-aviation engines (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The research and technology program related to improved and advanced general aviation engines is described. Current research is directed at the near-term improvement of conventional air-cooled spark-ignition piston engines and at future alternative engine systems based on all-new spark-ignition piston engines, lightweight diesels, and rotary combustion engines that show potential for meeting program goals in the midterm and long-term future. The conventional piston engine activities involve efforts on applying existing technology to improve fuel economy, investigation of key processes to permit leaner operation and reduce drag, and the development of cost effective technology to permit flight at high-altitudes where fuel economy and safety are improved. The advanced engine concepts activities include engine conceptual design studies and enabling technology efforts on the critical or key technology items.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 227-229
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  • 87
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    Summary of NASA QCGAT program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of large turbofan engine technology to small general aviation turbofan engines to achieve low noise, low emissions, and acceptable fuel consumption is described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 189-193
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  • 88
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    New opportunities for future, small, General-Aviation Turbine Engines (GATE) (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The results of four independent contracted studies to explore the opportunities for future small turbine engines are summarized in a composite overview. Candidate advanced technologies are screened, various cycles and staging arrangements are parametrically evaluated, and optimum conceptual engines are identified for a range of 300 to 600 horsepower applications. Engine improvements of 20 percent in specific fuel consumption and 40 percent in engine cost were forecast using high risk technologies that could be technically demonstrated by 1988. The ensuing economic benefits are in the neighborhood of 20 to 30 percent for twin-engine aircraft currently powered by piston engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 195-219
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  • 89
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    Avco Lycoming quiet clean general aviation turbofan engine (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A fan module was developed using an existing turboshaft engine. The fan was designed using the latest in large engine noise control technology. A mixer was added to reduce the already low exhaust gas velocity. A nacelle incorporating sound treatment was provided for the test engine. A noise prediction model was used through the design process to evaluate the various design alternatives. Acoustic tests were then made to verify the prediction and identify the noise characteristics of the fan, core, jet, and sound treatment. Analysis of the recorded data yielded close agreement with the expected results. Core noise, as was expected, was the predominant source of noise for the quiet clean general aviation turbofan (QCGAT) engine. Flyover noise predictions were made which indicated that the Avco Lycoming QCGAT engine would meet the goals set for the QCGAT program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 155-187
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  • 90
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    Low speed propellers: Impact of advanced technologies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sensitivity studies performed to evaluate the potential of several advanced technological elements on propeller performance, noise, weight, and cost for general aviation aircraft are discussed. Studies indicate that the application of advanced technologies to general aviation propellers can reduce fuel consumption in future aircraft an average of ten percent, meeting current regulatory noise limits. Through the use of composite blade construction, up to 25 percent propeller weight reduction can be achieved. This weight reduction in addition to seven percent propeller efficiency improvements through application of advanced technologies result in four percent reduction in direct operating costs, ten percent reduction in aircraft acquisition cost, and seven percent lower gross weight for general aviation aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 327-343
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  • 91
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    NASA propeller noise research (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The research in propeller noise prediction, noise/performance optimization, and interior reduction is described. Selected results are presented to illustrate the status of the technology and the direction of future research.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 405-420
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  • 92
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    Advanced propeller aerodynamic analysis (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The analytical approaches as well as the capabilities of three advanced analyses for predicting propeller aerodynamic performance are presented. It is shown that two of these analyses use a lifting line representation for the propeller blades, and the third uses a lifting surface representation.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 375-385
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  • 93
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    NASA propeller technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A program on propeller technology applicable to both low and high speed general aviation aircraft is summarized, and the overall program objectives and approach are outlined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Gen. Aviation Propulsion; p 315-325
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  • 94
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    Lightweight diesel aircraft engines for general aviation (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A methodical design study was conducted to arrive at new diesel engine configurations and applicable advanced technologies. Two engines are discussed and the description of each engine includes concept drawings. A performance analysis, stress and weight prediction, and a cost study were also conducted. This information was then applied to two airplane concepts, a six-place twin and a four-place single engine aircraft. The aircraft study consisted of installation drawings, computer generated performance data, aircraft operating costs and drawings of the resulting airplanes. The performance data shows a vast improvement over current gasoline-powered aircraft. At the completion of this basic study, the program was expanded to evaluate a third engine configuration. This third engine incorporates the best features of the original two, and its design is currently in progress. Preliminary information on this engine is presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 247-285
    Format: application/pdf
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    Avco Lycoming QCGAT program design cycle, demonstrated performance and emissions (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A high bypass ratio, twin spool turbofan engine of modular design which incorporates a front fan module driven by a modified LTS101 core engine was tested. The engine is housed in a nacelle incorporating full length fan ducting with sound treatment in both the inlet and fan discharge flow paths. Design goals of components and results of component tests are presented together with full engine test results. The rationale behind the combustor design selected for the engine is presented as well as the emissions test results. Total system (engine and nacelle) test results are included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Gen. Aviation Propulsion; p 135-154
    Format: application/pdf
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    Effect of fuel molecular structure on soot formation in gas turbine combustion (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effect of fuel variations at the same hydrogen content on the formation of soot in a gas turbine combustor was studied. Six fuels were burned to a combustor over a matrix of about 50 test conditions with test conditions ranging over 500-1800 kPa (5-18 atm) pressure and 500-1000 K burner inlet temperature; fuel-air ratios were varied from 0.008-0.024. Flame radiation measurements were made through a sapphire window toward the end of the primary zone. The hydrogen content of the six test fuels ranged from 12.80 to 12.88%. Five fuels emphasized hydrocarbon types: (mono, di, and tricyclic), naphthenes (decalin) and partially hydrogenated aromatics (tetralin); the sixth fuel emphasized final boiling point.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 147-152
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    Fuel property effects in stirred combustors (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Soot formation in strongly backmixed combustion was investigated using the jet-stirred combustor (JSC). This device provided a combustion volume in which temperature and combustion were uniform. It simulated the recirculating characteristics of the gas turbine primary zone; it was in this zone where mixture conditions were sufficiently rich to produce soot. Results indicate that the JSC allows study of soot formation in an aerodynamic situation revelant to gas turbines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 139-146
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    Soot formation and burnout in flames (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The amount of soot formed when burning a benzene/hexane mixture in a turbulent combustor was examined. Soot concentration profiles in the same combustor for kerosene fuel are given. The chemistry of the formation of soot precursors, the nucleation, growth and subsequent burnout of soot particles, and the effect of mixing on the previous steps were considered.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels; p 131-137
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    Antimisting kerosene (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The antimisting additive ((FM-9) was tested in terms of its propulsion systems performance. The effect of the additive on engine operation was evaluated, operating problems were identified, the adaptability of engines to antimisting kerosene was assessed, and the potential viability of this fuel for use in present and future fan jet engines was determined.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aircraft Res. and Technol. for Future Fuels Jul. 1980; p 125-130
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    Atomization of broad specification aircraft fuels (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The atomization properties of liquid fuels for the potential use in aircraft gas turbine engines are discussed. The significance of these properties are addressed with respect to the ignition and subsequent combustion behavior of the fuel spray/air mixture. It is shown that the fuel properties which affect the atomization behavior (viscosity, surface tension, and density) are less favorable for the broad specification fuels as compared to with those for conventional fuels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Aircraft Res. and Technol. for Future Fuels Jul. 1980; p 117-124
    Format: application/pdf
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