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  • Aircraft Propulsion and Power  (11)
  • 2010-2014  (6)
  • 2000-2004  (4)
  • 1995-1999  (1)
  • 1960-1964
  • 1950-1954
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  • 2010-2014  (6)
  • 2000-2004  (4)
  • 1995-1999  (1)
  • 1960-1964
  • 1950-1954
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  • 1
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    Low-Noise Potential of Advanced Fan Stage Stator Vane Designs Verified in NASA Lewis Wind Tunnel Test (1999)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: With the advent of new, more stringent noise regulations in the next century, aircraft engine manufacturers are investigating new technologies to make the current generation of aircraft engines as well as the next generation of advanced engines quieter without sacrificing operating performance. A current NASA initiative called the Advanced Subsonic Technology (AST) Program has set as a goal a 6-EPNdB (effective perceived noise) reduction in aircraft engine noise relative to 1992 technology levels by the year 2000. As part of this noise program, and in cooperation with the Allison Engine Company, an advanced, low-noise, high-bypass-ratio fan stage design and several advanced technology stator vane designs were recently tested in NASA Lewis Research Center's 9- by 15-Foot Low-Speed Wind Tunnel (an anechoic facility). The project was called the NASA/Allison Low Noise Fan.
    Keywords: Aircraft Propulsion and Power
    Type: Research and Technology 1998; NASA/TM-1999-208815
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Vibration Test Demonstrated Dynamic Capability of an Operating Stirling Convertor (2001)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The NASA Glenn Research Center and the U.S. Department of Energy are currently developing a high-efficiency, long-life, free piston Stirling convertor for use as an advanced spacecraft power system for future NASA missions. As part of this development, a Stirling Technology Demonstrator Converter (TDC), developed by Stirling Technology Company for the Department of Energy, was vibration tested at Glenn's Structural Dynamics Laboratory in November and December 1999. This testing demonstrated that the Stirling TDC is able to withstand the harsh random vibration (20 to 2000 Hz) seen during a typical spacecraft launch and to survive with no structural damage or functional power performance degradation, thereby enabling its use in future spacecraft power systems. Glenn and Stirling personnel conducted tests on a single 55 We TDC. The purpose was to characterize the TDC's structural response to vibration and to determine if the TDC could survive the vibration criteria established by the Jet Propulsion Laboratory for launch environments. The TDC was operated at full-stroke and full power conditions during the vibration testing.
    Keywords: Aircraft Propulsion and Power
    Type: Research and Technology 2000; NASA/TM-2001-210605
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Overview of ERA Ultra High Bypass Propulsor Technology Development (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A review of the current research being conducted under the Environmentally Responsible Aviation (ERA) Ultra High Bypass (UHB) Testing subelement is presented. The four exiting tasks under the subelement, a description of each task, and the current status of each are given. The four tasks are: 1. Collaborate with P&W to design, fabricate and test a second generation of Geared Turbofan 2. Design, fabricate and test advanced Over the Rotor acoustic treatment and acoustically treated Soft Vanes 3. Develop a Shape Memory Alloy Variable Area Nozzle concept and demonstrate prototype 4. Refurbish and update the GRC Ultra High Bypass Drive Rig Following the current task updates, an overview of three proposed additional tasks to support the existing tasks is presented. The additional tasks would allow noise reduction and noise diagnostic testing technologies to be demonstrated at TRL 4 as part of existing planned fan model testing in the NASA Glenn 9 x15 Low Speed Wind Tunnel under the ERA UHB Testing subelement.
    Keywords: Aircraft Propulsion and Power
    Type: E-17844 , Acoustics Technical Working Group Meeting; Apr 21, 2011 - Apr 22, 2011; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Far-Field Acoustic Characteristics of Multiple Blade-Vane Configurations for a High Tip Speed Fan (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The acoustic characteristics of a model high-speed fan stage were measured in the NASA Glenn 9- by 15-Foot Low Speed Wind Tunnel at takeoff and approach flight conditions. The fan was designed for a corrected rotor tip speed of 442 m/s (1450 ft/s), and had a powered core, or booster stage, giving the model a nominal bypass ratio of 5. A simulated engine pylon and nozzle bifurcation was contained within the bypass duct. The fan stage consisted of all combinations of 3 possible rotors, and 3 stator vane sets. The 3 rotors were (1) wide chord, (2) forward swept, and (3) shrouded. The 3 stator sets were (1) baseline, moderately swept, (2) swept and leaned, and (3) swept integral vane/frame which incorporated some of the swept and leaned features as well as eliminated the downstream support structure. The baseline configuration is considered to be the wide chord rotor with the radial vane stator. A flyover Effective Perceived Noise Level (EPNL) code was used to generate relative EPNL values for the various configurations. The swept and leaned stator showed a 3 EPNdB reduction at lower fan speeds relative to the baseline stator; while the swept integral vane/frame stator showed lowest noise levels at high fan speeds. The baseline, wide chord rotor was typically the quietest of the three rotors. A tone removal study was performed to assess the acoustic benefits of removing the fundamental rotor interaction tone and its harmonics. Reprocessing the acoustic results with the bypass tone removed had the most impact on reducing fan noise at transonic rotor speeds. Removal of the bypass rotor interaction tones (BPF and nBPF) showed up to a 6 EPNdB noise reduction at transonic rotor speeds relative to noise levels for the baseline (wide chord rotor and radial stator; all tones present) configuration.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2004-213093 , E-14568 , NAS/1.15:2004-213093
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The Promise and Challenges of Ultra High Bypass Ratio Engine Technology and Integration (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: In this presentation, an overview of the research being conducted by the ERA Project in Ultra High Bypass aircraft propulsion and in partnership with Pratt & Whitney with their Geared TurboFan (GTF) is given. The ERA goals are shown followed by a discussion of what areas need to be addressed on the engine to achieve the goals and how the GTF is uniquely qualified to meet the goals through a discussion of what benefits the cycle provides. The first generation GTF architecture is then shown highlighting the areas of collaboration with NASA, and the fuel burn, noise and emissions reductions possible based on initial static ground test and flight test data of the first GTF engine. Finally, a 5 year technology roadmap is presented focusing on Ultra High Bypass propulsion technology research areas that are being pursued and being planned by ERA and P&W under their GTF program.
    Keywords: Aircraft Propulsion and Power
    Type: HQ-STI-11-012 , E-17843 , 49th AIAA Aero Sciences Meeting; Jan 04, 2011 - Jan 07, 2011; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Performance Optimization of a Rotor Alone Nacelle for Acoustic Fan Testing (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the techniques, equipment, and results from the optimization of a two-axis traverse actuation system used to maintain concentricity between a sting-mounted fan and a wall-mounted nacelle in the 9 x 15 (9 Foot by 15 Foot Test Section) Low Speed Wind Tunnel (LSWT) at the NASA Glenn Research Center (GRC). The Rotor Alone Nacelle (RAN) system, developed at GRC by the Engineering Design and Analysis Division (EDAD) and the Acoustics Branch, used nacelle-mounted lasers and an automated control system to maintain concentricity as thermal and thrust operating loads displace the fan relative to the nacelle. This effort was critical to ensuring rig/facility safety and experimental consistency of the acoustic data from a statorless, externally supported nacelle configuration. Although the tip clearances were originally predicted to be about 0.020 in. at maximum rotor (fan) operating speed, proximity probe measurements showed that the nominal clearance was less than 0.004 in. As a result, the system was optimized through control-loop modifications, active laser cooling, data filtering and averaging, and the development of strict operational procedures. The resultant concentricity error of RAN was reduced to +/- 0.0031 in. in the Y-direction (horizontal) and +0.0035 in./-0.001 3 in. in the Z-direction (vertical), as determined by error analysis and experimental results. Based on the success of this project, the RAN system will be transitioned to other wind tunnel research programs at NASA GRC.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2000-210599 , NAS 1.15:210599 , E-12557 , AIAA Paper 2001-0164 , Aerospace Sciences; Jan 08, 2001 - Jan 11, 2001; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    NASA Collaborative Research on the Ultra High Bypass Engine Cycle and Potential Benefits for Noise, Performance, and Emissions (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The National Aeronautics and Space Administration has taken an active role in collaborative research with the U.S. aerospace industry to investigate technologies to minimize the impact of aviation on the environment. In December 2006, a new program, called the Fundamental Aeronautics Program, was established to enhance U.S. aeronautics technology and conduct research on energy, efficiency and the environment. A project within the overall program, the Subsonic Fixed Wing Project, was formed to focus on research related to subsonic aircraft with specific goals and time based milestones to reduce aircraft noise, emissions and fuel burn. This paper will present an overview of the Subsonic Fixed Wing Project environmental goals and describe a segment of the current research within NASA and also were worked collaboratively with partners from the U.S. aerospace industry related to the next generation of aircraft that will have lower noise, emissions and fuel burn.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2013-216345 , ISABE-2009-1274 , E-17282 , International Symposium on Air Breathing Engines (ISABE 2009); Sep 07, 2009 - Sep 11, 2009; Montreal, Quebec; Canada
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Aircraft Engine Technology for Green Aviation to Reduce Fuel Burn (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Fundamental Aeronautics Program Subsonic Fixed Wing Project and Integrated Systems Research Program Environmentally Responsible Aviation Project in the Aeronautics Research Mission Directorate are conducting research on advanced aircraft technology to address the environmental goals of reducing fuel burn, noise and NOx emissions for aircraft in 2020 and beyond. Both Projects, in collaborative partnerships with U.S. Industry, Academia, and other Government Agencies, have made significant progress toward reaching the N+2 (2020) and N+3 (beyond 2025) installed fuel burn goals by fundamental aircraft engine technology development, subscale component experimental investigations, full scale integrated systems validation testing, and development validation of state of the art computation design and analysis codes. Specific areas of propulsion technology research are discussed and progress to date.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2013-217690 , AIAA Paper 2011-3531 , E-18373 , Atmospheric and Space Environments Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    The Aerodynamic Performance of an Over-the-Rotor Liner With Circumferential Grooves on a High Bypass Ratio Turbofan Rotor (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: While liners have been utilized throughout turbofan ducts to attenuate fan noise, additional attenuation is obtainable by placing an acoustic liner over-the-rotor. Previous experiments have shown significant fan performance losses when acoustic liners are installed over-the-rotor. The fan blades induce an oscillating flow in the acoustic liners which results in a performance loss near the blade tip. An over-the-rotor liner was designed with circumferential grooves between the fan blade tips and the acoustic liner to reduce the oscillating flow in the acoustic liner. An experiment was conducted in the W-8 Single-Stage Axial Compressor Facility at NASA Glenn Research Center on a 1.5 pressure ratio fan to evaluate the impact of this over-the-rotor treatment design on fan aerodynamic performance. The addition of a circumferentially grooved over-the-rotor design between the fan blades and the acoustic liner reduced the performance loss, in terms of fan adiabatic efficiency, to less than 1 percent which is within the repeatability of this experiment.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2013-218066 , GT2013-95114 , E-18742 , ASME Turbo Expo 2013; Jun 03, 2013 - Jun 07, 2013; San Antonio, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    The Aerodynamic Performance of an Over-The-Rotor Liner with Circumferential Grooves on a High Bypass Ratio Turbofan Rotor (2013)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: While liners have been utilized throughout turbofan ducts to attenuate fan noise, additional attenuation is obtainable by placing an acoustic liner over-the-rotor. Previous experiments have shown significant fan performance losses when acoustic liners are installed over-the-rotor. The fan blades induce an oscillating flow in the acoustic liners which results in a performance loss near the blade tip. An over-the-rotor liner was designed with circumferential grooves between the fan blade tips and the acoustic liner to reduce the oscillating flow in the acoustic liner. An experiment was conducted in the W-8 Single-Stage Axial Compressor Facility at NASA Glenn Research Center on a 1.5 pressure ratio fan to evaluate the impact of this over-the-rotor treatment design on fan aerodynamic performance. The addition of a circumferentially grooved over-the-rotor design between the fan blades and the acoustic liner reduced the performance loss, in terms of fan adiabatic efficiency, to less than 1% which is within the repeatability of this experiment.
    Keywords: Aircraft Propulsion and Power
    Type: GT2013-95114 , E-18742-1 , ASME Turbo Exp 2013; Jun 03, 2013 - Jun 07, 2013; San Antonio, TX; United States
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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