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  • AIRCRAFT PROPULSION AND POWER  (4)
  • 1980-1984  (4)
  • 1
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    On optimal design for the blade-root/hub interface in jet engines (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two major problems identified with the design of the blade-root/hub interface are discussed. The first is the so-called friction contact problem which has two special features: unilateral contact and Coulomb's friction. One of the difficulties in this problem is that the portions of contact and sticking/sliding surfaces are not known a priori. The second is the shape optimization problem which is characterized either by the minimization of the maximum contact pressure or by the minimization of the equivalent stress on the boundary. Design variables are the shapes of the blade-root and the hub. It is noted that friction contact and shape optimization problems are strongly coupled in the present design problem.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Energy Efficient Engine (E3) combustion system component technology performance report (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Energy Efficient Engine (E3) combustor effort was conducted as part of the overall NASA/GE E3 Program. This effort included the selection of an advanced double-annular combustion system design. The primary intent of this effort was to evolve a design that meets the stringent emissions and life goals of the E3, as well as all of the usual performance requirements of combustion systems for modern turbofan engines. Numerous detailed design studies were conducted to define the features of the combustion system design. Development test hardware was fabricated, and an extensive testing effort was undertaken to evaluate the combustion system subcomponents in order to verify and refine the design. Technology derived from this effort was incorporated into the engine combustion hardware design. The advanced engine combustion system was then evaluated in component testing to verify the design intent. What evolved from this effort was an advanced combustion system capable of satisfying all of the combustion system design objectives and requirements of the E3.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168274 , NAS 1.26:168274 , R82AEB401
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Energy Efficient Engine combustor test hardware detailed design report (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Energy Efficient Engine (E3) Combustor Development effort was conducted as part of the overall NASA/GE E3 Program. This effort included the selection of an advanced double-annular combustion system design. The primary intent was to evolve a design which meets the stringent emissions and life goals of the E3 as well as all of the usual performance requirements of combustion systems for modern turbofan engines. Numerous detailed design studies were conducted to define the features of the combustion system design. Development test hardware was fabricated, and an extensive testing effort was undertaken to evaluate the combustion system subcomponents in order to verify and refine the design. Technology derived from this development effort will be incorporated into the engine combustion system hardware design. This advanced engine combustion system will then be evaluated in component testing to verify the design intent. What is evolving from this development effort is an advanced combustion system capable of satisfying all of the combustion system design objectives and requirements of the E3. Fuel nozzle, diffuser, starting, and emissions design studies are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168301 , NAS 1.26:168301 , R82AEB472
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Design and development of the combustor inlet diffuser for the NASA/GE energy efficient engine (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results of an experimental investigation of the aerodynamic performance of a split duct annular combustor inlet diffuser system are presented. Several diffuser configurations were investigated in 3X-scale water table tests and the preferred design was evaluated in full-scale annular airflow model tests. Pressure recovery and flow losses were determined as a function of prediffuser inlet velocity profile, flow extraction at the prediffuser exit, and distribution of flow in the combustor. Inlet velocity profile and turbulence levels were found to have a pronounced effect on system performance. Flow extraction at the prediffuser exit was found to have little influence on system performance. Generally, the annular split duct diffuser system was found to satisfy the performance objectives for the engine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 81-GT-129 , Gas Turbine Conference and Products Show; Mar 09, 1981 - Mar 12, 1981; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
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