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  • 2005-2009  (7)
  • 1
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    Engine Conceptual Design Studies for a Hybrid Wing Body Aircraft (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Worldwide concerns of air quality and climate change have made environmental protection one of the most critical issues in aviation today. NASA's current Fundamental Aeronautics research program is directed at three generations of aircraft in the near, mid and far term, with initial operating capability around 2015, 2020, and 2030, respectively. Each generation has associated goals for fuel burn, NOx, noise, and field-length reductions relative to today's aircrafts. The research for the 2020 generation is directed at enabling a hybrid wing body (HWB) aircraft to meet NASA's aggressive technology goals. This paper presents the conceptual cycle and mechanical designs of the two engine concepts, podded and embedded systems, which were proposed for a HWB cargo freighter. They are expected to offer significant benefits in noise reductions without compromising the fuel burn.
    Keywords: Aircraft Design, Testing and Performance
    Type: GT2009-59568 , E-16910 , ASME Turbo 2009; Jun 08, 2009 - Jun 12, 2009; Florida; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    An Assessment of NASA Aeropropulsion Technologies: A System Study (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aviation industry s robust growth rate has given rise to growing concerns about the contribution that aviation emissions will make to local air quality and global climate change. Over the last several years, NASA has been engaged in the development of aeropropulsion technologies with specific objectives to reduce aircraft emissions. A system analysis was performed to evaluate the potential impact of these propulsion technologies on aircraft CO2 (directly proportional to fuel burn) and NOx reductions. A large subsonic aircraft, with two 396-kN thrust (85,000-pound) engines was chosen for the study. Performance benefit estimates are presented for each technology, with a summary of potential emissions reduction possible from the development of these technologies. The results show that NASA s aeropropulsion technologies have the potential to significantly reduce the CO2 and NO(x) emissions. The results are used to support informed decision-making on the development of aeropropulsion technology portfolio for CO2 and NO(x) reductions.
    Keywords: Environment Pollution
    Type: ISABE-2007-1285 , ISABE 2007; Sep 02, 2007 - Sep 07, 2007; Beijing; China
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Adaptive Engine Technologies for Aviation CO2 Emissions Reduction (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Adaptive turbine engine technologies are assessed for their potential to reduce carbon dioxide emissions from commercial air transports.Technologies including inlet, fan, and compressor flow control, compressor stall control, blade clearance control, combustion control, active bearings and enabling technologies such as active materials and wireless sensors are discussed. The method of systems assessment is described, including strengths and weaknesses of the approach. Performance benefit estimates are presented for each technology, with a summary of potential emissions reduction possible from the development of new, adaptively controlled engine components.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2006-214392 , E-15670 , AIAA Paper 2006-5105 , 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jul 09, 2006 - Jul 12, 2006; Sacreamento, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    A Comparative Propulsion System Analysis for the High-Speed Civil Transport (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Six of the candidate propulsion systems for the High-Speed Civil Transport are the turbojet, turbine bypass engine, mixed flow turbofan, variable cycle engine, Flade engine, and the inverting flow valve engine. A comparison of these propulsion systems by NASA's Glenn Research Center, paralleling studies within the aircraft industry, is presented. This report describes the Glenn Aeropropulsion Analysis Office's contribution to the High-Speed Research Program's 1993 and 1994 propulsion system selections. A parametric investigation of each propulsion cycle's primary design variables is analytically performed. Performance, weight, and geometric data are calculated for each engine. The resulting engines are then evaluated on two airframer-derived supersonic commercial aircraft for a 5000 nautical mile, Mach 2.4 cruise design mission. The effects of takeoff noise, cruise emissions, and cycle design rules are examined.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2005-213414 , E-14934 , HSR007
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Engine Conceptual Design Studies for a Hybrid Wing Body Aircraft (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Worldwide concerns of air quality and climate change have made environmental protection one of the most critical issues in aviation today. NASA s current Fundamental Aeronautics Research program is directed at three generations of aircraft in the near, mid and far term, with initial operating capability around 2015, 2020, and 2030, respectively. Each generation has associated goals for fuel burn, NOx, noise, and field-length reductions relative to today s aircrafts. The research for the 2020 generation is directed at enabling a hybrid wing body (HWB) aircraft to meet NASA s aggressive technology goals. This paper presents the conceptual cycle and mechanical designs of the two engine concepts, podded and embedded systems, which were proposed for a HWB cargo freighter. They are expected to offer significant benefits in noise reductions without compromising the fuel burn.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215680 , GT2009-59568 , ARL-TR-4719 , E-16910-1 , ASME Turbo 2009; Jun 08, 2009 - Jun 12, 2009; Orlando, FL; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 6
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    Unknown
    Analysis of Turbofan Design Options for an Advanced Single-Aisle Transport Aircraft (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The desire for higher engine efficiency has resulted in the evolution of aircraft gas turbine engines from turbojets, to low bypass ratio, first generation turbofans, to today's high bypass ratio turbofans. It is possible that future designs will continue this trend, leading to very-high or ultra-high bypass ratio (UHB) engines. Although increased bypass ratio has clear benefits in terms of propulsion system metrics such as specific fuel consumption, these benefits may not translate into aircraft system level benefits due to integration penalties. In this study, the design trade space for advanced turbofan engines applied to a single-aisle transport (737/A320 class aircraft) is explored. The benefits of increased bypass ratio and associated enabling technologies such as geared fan drive are found to depend on the primary metrics of interest. For example, bypass ratios at which fuel consumption is minimized may not require geared fan technology. However, geared fan drive does enable higher bypass ratio designs which result in lower noise. Regardless of the engine architecture chosen, the results of this study indicate the potential for the advanced aircraft to realize substantial improvements in fuel efficiency, emissions, and noise compared to the current vehicles in this size class.
    Keywords: Aircraft Propulsion and Power
    Type: LF99-8327 , 9th AIAA Aviation Technology, Integration, and Operations Conference; Sep 21, 2009 - Sep 24, 2009; Hilton Head, SC; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Engine Concept Study for an Advanced Single-Aisle Transport (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The desire for higher engine efficiency has resulted in the evolution of aircraft gas turbine engines from turbojets, to low bypass ratio, first generation turbofans, to today's high bypass ratio turbofans. Although increased bypass ratio has clear benefits in terms of propulsion system metrics such as specific fuel consumption, these benefits may not translate into aircraft system level benefits due to integration penalties. In this study, the design trade space for advanced turbofan engines applied to a single aisle transport (737/A320 class aircraft) is explored. The benefits of increased bypass ratio and associated enabling technologies such as geared fan drive are found to depend on the primary metrics of interest. For example, bypass ratios at which mission fuel consumption is minimized may not require geared fan technology. However, geared fan drive does enable higher bypass ratio designs which result in lower noise. The results of this study indicate the potential for the advanced aircraft to realize substantial improvements in fuel efficiency, emissions, and noise compared to the current vehicles in this size class.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2009-215784 , L-19712 , LF-9138
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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