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  • 1
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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
  • 2
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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
  • 3
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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
  • 4
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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
  • 5
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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
  • 6
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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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