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  • Other Sources  (78)
  • MECHANICAL ENGINEERING  (46)
  • AIRCRAFT PROPULSION AND POWER
  • 1980-1984  (78)
  • 1982  (78)
  • 1
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    Energy efficient engine high-pressure turbine detailed design report (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The energy efficient engine high-pressure turbine is a single stage system based on technology advancements in the areas of aerodynamics, structures and materials to achieve high performance, low operating economics and durability commensurate with commercial service requirements. Low loss performance features combined with a low through-flow velocity approach results in a predicted efficiency of 88.8 for a flight propulsion system. Turbine airfoil durability goals are achieved through the use of advanced high-strength and high-temperature capability single crystal materials and effective cooling management. Overall, this design reflects a considerable extension in turbine technology that is applicable to future, energy efficient gas-turbine engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165608 , NAS 1.26:165608 , PWA-5594-171
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Development of an ultra-low-shock separation nut (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The technical problems encountered in the development of an advanced separation nut design are described. The nut is capable of sustaining a large preload and releasing that load with a low level of induced pyrotechnic shock, while demonstrating a tolerance for extremely high shock imposed by other pyrotechnic devices. The analysis of the separation nut was performed to acquire additional understanding of the phenomena affecting operation of the nut and to provide quantitative evaluation of design modification for aerospace applications.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Kennedy Space Center Center The 16th Aerospace Mech. Symp.; p 87-98
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Energy efficient engine: Turbine intermediate case and low-pressure turbine component test hardware detailed design report (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A four stage, low pressure turbine component has been designed to power the fan and low pressure compressor system in the Energy Efficient Engine. Designs for a turbine intermediate case and an exit guide vane assembly also have been established. The components incorporate numerous technology features to enhance efficiency, durability, and performance retention. These designs reflect a positive step towards improving engine fuel efficiency on a component level. The aerodynamic and thermal/mechanical designs of the intermediate case and low pressure turbine components are presented and described. An overview of the predicted performance of the various component designs is given.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-167973 , NAS 1.26:167973 , PWA-5594-191
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Energy efficient engine. Low pressure turbine test hardware detailed design report (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The low pressure turbine for the energy efficient engine is a five-stage configuration with moderate aerodynamic loading incorporating advanced features of decambered airfoils and extended blade overlaps at platforms and shrouds. Mechanical integrity of 18,000 hours on flowpath components and 36,000 hours on all other components is achieved along with no aeromechanical instabilities within the steady-state operating range. Selection of a large number (156) of stage 4 blades, together with an increased stage 4 vane-to-blade gap, assists in achieving FAR 36 acoustic goals. Active clearance control (ACC) of gaps at blade tips and interstage seals is achieved by fan air cooling judiciously applied at responsive locations on the casing. This ACC system is a major improvement in preventing deterioration of the 0.0381 cm (0.015 in.) clearances required to meet the integrated-core/low-spool turbine efficiency goal of 91.1% and the light propulsion system efficiency goal of 91.7%.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-167956 , NAS 1.26:167956 , R81AEG597
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Advanced stratified charge rotary aircraft engine design study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technology base of new developments which offered potential benefits to a general aviation engine was compiled and ranked. Using design approaches selected from the ranked list, conceptual design studies were performed of an advanced and a highly advanced engine sized to provide 186/250 shaft Kw/HP under cruise conditions at 7620/25,000 m/ft altitude. These are turbocharged, direct-injected stratified charge engines intended for commercial introduction in the early 1990's. The engine descriptive data includes tables, curves, and drawings depicting configuration, performance, weights and sizes, heat rejection, ignition and fuel injection system descriptions, maintenance requirements, and scaling data for varying power. An engine-airframe integration study of the resulting engines in advanced airframes was performed on a comparative basis with current production type engines. The results show airplane performance, costs, noise & installation factors. The rotary-engined airplanes display substantial improvements over the baseline, including 30 to 35% lower fuel usage.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-165398 , NAS 1.26:165398 , CW-WR-81.021
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A Computer Code for Swirling Turbulent Axisymmetric Recirculating Flows in Practical Isothermal Combustor Geometries (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A primitive pressure-velocity variable finite difference computer code was developed to predict swirling recirculating inert turbulent flows in axisymmetric combustors in general, and for application to a specific idealized combustion chamber with sudden or gradual expansion. The technique involves a staggered grid system for axial and radial velocities, a line relaxation procedure for efficient solution of the equations, a two-equation k-epsilon turbulence model, a stairstep boundary representation of the expansion flow, and realistic accommodation of swirl effects. A user's manual, dealing with the computational problem, showing how the mathematical basis and computational scheme may be translated into a computer program is presented. A flow chart, FORTRAN IV listing, notes about various subroutines and a user's guide are supplied as an aid to prospective users of the code.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-3442
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    On the mechanism of lubrication by tricresylphosphate /TCP/ - The coefficient of friction as a function of temperature for TCP on M-50 steel (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: MECHANICAL ENGINEERING
    Type: ASLE PREPRINT 82-LC-4C-1 , American Society of Mechanical Engineers and American Society of Lubrication Engineers, Lubrication Conference; Oct 05, 1982 - Oct 07, 1982; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Rotor redesign for a highly loaded 1800 ft/sec tip speed fan. 3: Laser Doppler velocimeter report (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Laser Doppler velocimeter (LDV) techniques were employed for testing a highly loaded, 550 m/sec (1800 ft/sec) tip speed, test fan stage, the objective to provide detailed mapping of the upstream, intrablade, and downstream flowfields of the rotor. Intrablade LDV measurements of velocity and flow angle were obtained along four streamlines passing through the leading edge at 45%, 69%, 85%, and 95% span measured from hub to tip, at 100% of design speed, peak efficiency; 100% speed, near surge; and 95% speed, peak efficiency. At the design point, most passages appeared to have a strong leading edge shock, which moved forward with increasing strength near surge and at part speeds. The flow behind the shock was of a complex mixed subsonic and supersonic form. The intrablade flowfields were found to be significantly nonperiodic at 100% design speed, peak efficiency.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-167954 , NAS 1.26:167954 , PWA-5523-122
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Nonlinear analysis of rotor-bearing systems using component mode synthesis (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The method of component mode synthesis is developed to determine the forced response of nonlinear, multishaft, rotor-bearing systems. The formulation allows for simulation of system response due to blade loss, distributed unbalance, base shock, maneuver loads, and specified fixed frame forces. The motion of each rotating component of the system is described by superposing constraint modes associated with boundary coordinates and constrained precessional modes associated with internal coordinates. The precessional modes are truncated for each component and the reduced component equations are assembled with the nonlinear supports and interconnections to form a set of nonlinear system equations of reduced order. These equations are then numerically integrated to obtain the system response. A computer program, which is presently restricted to single shaft systems, has been written and results are presented for transient system response associated with blade loss dynamics with squeeze film dampers, and with interference rubs.
    Keywords: MECHANICAL ENGINEERING
    Type: ASME PAPER 82-GT-303 , International Gas Turbine Conference and Exhibit; Apr 18, 1982 - Apr 22, 1982; London
    Format: text
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  • 10
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    Tribology (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: The adhesion, friction, and wear properties of materials are reviewed and some of the factors influencing these properties are discussed. The forms of lubrication and types of lubricants will also be discussed.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Langley Research Center Advan. Mater. Technol.; p 391-410
    Format: text
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