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  • 1
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    STAEBL: Structural tailoring of engine blades, phase 2 (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Structural Tailoring of Engine Blades (STAEBL) program was initiated at NASA Lewis Research Center in 1980 to introduce optimal structural tailoring into the design process for aircraft gas turbine engine blades. The standard procedure for blade design is highly iterative with the engineer directly providing most of the decisions that control the design process. The goal of the STAEBL program has been to develop an automated approach to generate structurally optimal blade designs. The program has evolved as a three-phase effort with the developmental work being performed contractually by Pratt & Whitney Aircraft. Phase 1 was intended as a proof of concept in which two fan blades were structurally tailored to meet a full set of structural design constraints while minimizing DOC+I (direct operating cost plus interest) for a representative aircraft. This phase was successfully completed and was reported in reference 1 and 2. Phase 2 has recently been completed and is the basis for this discussion. During this phase, three tasks were accomplished: (1) a nonproprietary structural tailoring computer code was developed; (2) a dedicated approximate finite-element analysis was developed; and (3) an approximate large-deflection analysis was developed to assess local foreign object damage. Phase 3 is just beginning and is designed to incorporated aerodynamic analyses directly into the structural tailoring system in order to relax current geometric constraints.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Recent Experiences in Multidisciplinary Analysis and Optimization, Part 1; 13 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A shock capturing technique for hypersonic, chemically relaxing flows (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A fully coupled, shock capturing technique is presented for chemically reacting flows at high Mach numbers. The technique makes use of a total variation diminishing (TVD) dissipation operator which results in sharp, crisp shocks. The eigenvalues and eigenvectors of the fully coupled system, which includes species conversion equations in addition to the gas dynamics equations, are analytically derived for a general reacting gas. Species production terms for a model dissociating gas are introduced and are included in the algorithm. The convective terms are solved using a first-order TVD scheme while the source terms are solved using a fourth-order Runge-Kutta scheme to enhance stability. Results from one-dimensional numerical experiments are shown for a two species and a three species gas.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0231
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Structural tailoring of engine blades (STAEBL) theoretical manual (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This Theoretical Manual includes the theories included in the Structural Tailoring of Engine Blades (STAEBL) computer program which was developed to perform engine fan and compressor blade numerical optimizations. These blade optimizations seek a minimum weight or cost design that satisfies practical blade design constraints, by controlling one to twenty design variables. The STAEBL constraint analyses include blade stresses, vibratory response, flutter, and foreign object damage. Blade design variables include airfoil thickness at several locations, blade chord, and construction variables: hole size for hollow blades, and composite material layup for composite blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-175112 , NAS 1.26:175112 , PWA-5774-40
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Structural tailoring of engine blades (STAEBL) user's manual (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This User's Manual contains instructions and demonstration case to prepare input data, run, and modify the Structural Tailoring of Engine Blades (STAEBL) computer code. STAEBL was developed to perform engine fan and compressor blade numerical optimizations. This blade optimization seeks a minimum weight or cost design that satisfies realistic blade design constraints, by tuning one to twenty design variables. The STAEBL constraint analyses include blade stresses, vibratory response, flutter, and foreign object damage. Blade design variables include airfoil thickness at several locations, blade chord, and construction variables: hole size for hollow blades, and composite material layup for composite blades.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-175113 , NAS 1.26:175113 , PWA-5774-39
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Structural tailoring of advanced turboprops (STAT): User's manual (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This user's manual describes the Structural Tailoring of Advanced Turboprops program. It contains instructions to prepare the input for optimization, blade geometry and analysis, geometry generation, and finite element program control. In addition, a sample input file is provided as well as a section describing special applications (i.e., non-standard input).
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-187101 , NAS 1.26:187101 , PWA-5967-43
    Format: application/pdf
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  • 6
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    Structural tailoring of engine blades (STAEBL) (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematical optimization procedure was developed for the structural tailoring of engine blades and was used to structurally tailor two engine fan blades constructed of composite materials without midspan shrouds. The first was a solid blade made from superhybrid composites, and the second was a hollow blade with metal matrix composite inlays. Three major computerized functions were needed to complete the procedure: approximate analysis with the established input variables, optimization of an objective function, and refined analysis for design verification.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-167949 , NAS 1.26:167949 , PWA-5774-21
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Candidate techniques for non-intrusive measurement of flight boundary-layer properties (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Techniques to measure gas composition and chemical activity in the hypersonic boundary layer associated with entry research vehicles and with a tethered satellite deployed at 100-125 km altitude are currently being investigated at the NASA-Langley Research Center. These measurements are appropriate for the study of the aerothermodynamic properties of these vehicles when operating with controlled trajectories in the thermosphere between 125 and 55 km. A number of the required quantitative physical measurements have been identified, and candidate techniques to obtain the measurements without perturbing the flow are being considered. Two candidate techniques are discussed in this paper: a mass spectrometer to analyze the gas composition at the vehicle surface, and Rayleigh scattering to obtain density, velocity, and temperature gradients from the surface to the edge of the boundary layer.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0970
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Structural Tailoring of Advanced Turboprops (STAT) programmer's manual (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Structural Tailoring of Advanced Turboprops (STAT) computer program was developed to perform numerical optimizations on highly swept propfan blades. This manual describes the functionality of the STAT system from a programmer's viewpoint. It provides a top-down description of module intent and interaction. The purpose of this manual is to familiarize the programmer with the STAT system should he/she wish to enhance or verify the program's function.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-182164 , NAS 1.26:182164 , PWA-5967-51
    Format: application/pdf
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  • 9
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    Chemical and thermal nonequilibrium heat transfer analysis for hypervelocity, low Reynolds number flow (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Chemical and thermal nonequilibrium phenomena are studied in the stagnation region of a hypervelocity blunt body. This investigation is motivated by the need to predict the heat transfer rate to the leading edge of Aeromaneuvering Orbital Transfer Vehicles. Flight speeds of approximately 10 km/s at altitudes of approximately 80 km are considered for body radii of 1 to 50 cm. The analysis is based on continuum theory and is applicable to the viscous-layer and incipient-merged-layer rarefied-flow regimes. A two-species, two-temperature gas model is assumed. Comparisons are made with previous theories, experimental data, and results based on the thermodynamic equilibrium assumption. The equation accounting for vibrational nonequilibrium is presented and its effects on flow properties are discussed. Parameters which require further investigation are identified. Preliminary results indicate that the inclusion of vibrational relaxation has little effect on heat transfer rate for a catalytic surface. However, vibrational nonequilibrium may increase the heat transfer rate to a noncatalytic surface, depending on the degree of nonequilibrium.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-1033
    Format: text
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  • 10
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    Aerothermodynamic heating analysis of aerobraking and aeromaneuvering orbital-transfer vehicles (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The thermal-protection requirements of two aeroassisted orbital-transfer vehicles (AOTVs) are analyzed for return missions between the geosynchronous and Shuttle orbits. One of the designs is a specialized version of a previously proposed generic aerobraking vehicle that is capable of only delivery-type operations. The other is a high-lift aeromaneuvering vehicle that is optimized for low-earth orbit sortie missions involving large, multiple plane-inclination changes. The aerothermal environment of the aerobraking vehicle is analyzed using state-of-the-art methods for nonequilibrium-radiative and convective heating that incorporate refinements unique to the configuration. The heating analysis of the aeromaneuvering vehicle required the development of a flow-field model for rarefied-hypersonic flow over a lifting surface at incidence. The predicted aerothermodynamic heating characteristics for both vehicles are correlated with thermal-control requirements and flight performance capabilities for the specified mission guidelines. The results help identify technical issues related to the development of future operational systems.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1711
    Format: text
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