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  • 1
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    Aircraft Energy Efficiency (ACEE) status report (1979)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: Fuel efficiency in aeronautics, for fuel conservation in general as well as for its effect on commercial aircraft operating economics is considered. Projects of the Aircraft Energy Efficiency Program related to propulsion are emphasized. These include: (1) engine component improvement, directed at performance improvement and engine diagnostics for prolonged service life; (2) energy efficient engine, directed at proving the technology base for the next generation of turbofan engines; and (3) advanced turboprop, directed at advancing the technology of turboprop powered aircraft to a point suitable for commercial airline service. Progress in these technology areas is reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 1-58
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Launch operations (1969)
    In:  CASI
    Details
    Publication Date: 2006-08-29
    Description: Launch operations at Eastern Test Range for Lunar Orbiter 3, 4, and 5 missions
    Keywords: SPACE VEHICLES
    Type: GHT PERFORMANCE OF ATLAS-AGENA LAUNCH VEHICLES IN SUPPORT OF LUNAR ORBITER MISSIONS 3, 4, AND 5 AUG. 1969; P 95-99
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of performance deterioration of the CF6/JT9D high bypass ratio turbofan engines (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The extent and magnitude of performance deterioration of the Pratt and Whitney JT9D, and the General Electric CF6 engine models is presented. Overall engine and contributing module performance deterioration with respect to flight cycles and/or time are analyzed. The overall engine performance deterioration analyses are based on data obtained from historical records, special engine tests, and tests for specific effects. Hardware inspection data from overhaul shops and special module tests are the basis for the modular performance deterioration data used in the analyses. Various damage mechanisms such as seal rubs, erosion, surface roughness and thermal distortion, and how they contribute to performance deterioration are included in the modular analyses. Results indicate that early performance deterioration occurring within the first few flights of these engines is less than 1 percent in cruise specific fuel consumption (SFC), that it is event oriented, and that it is the result of increased blade tip clearances. This performance deterioration gradually increases to about 2.5 to 3.0 percent (including the initial short term deterioration) after 2500 to 3000 flights where increased blade tip clearances, airfoil quality degradation, and thermal distortion are the contributing causes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Turbine Engine Testing; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Performance deterioration of commercial high-bypass ratio turbofan engines (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of engine performance deterioration investigations based on historical data, special engine tests, and specific tests to define the influence of flight loads and component clearances on performance are presented. The results of analyses of several damage mechanisms that contribute to performance deterioration such as blade tip rubs, airfoil surface roughness and erosion, and thermal distortion are also included. The significance of these damage mechanisms on component and overall engine performance is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81552-REV , E-511-REV , SAE Aerospace Congr.; Oct 13, 1980 - Oct 16, 1980; Los Angeles|AGARD Propulsion and Energetics Symp. on Turbine Engine Testing; Sep 29, 1980 - Oct 03, 1980; Turin
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Performance deterioration of commercial high-bypass ratio turbofan engines (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: NASA programs for improving aircraft engine fuel efficiency include the Engine Component Improvement Project of which the Engine Diagnostics section is to identify performance deterioration factors for the JT9D and CF6 high-bypass ratio turbofan engines and to develop technology for fuel consumption reduction. The program tests and inspects engines, examines deteriorated elements, formulates deterioration trends and models, identifies specific causative events or modules and determines mechanisms. Results show that short-term performance deterioration is less than 1% of cruise specific fuel consumption and is caused by flight loads or thermal damage due to rubbing of turbine blade tips against shrouds. Long-term deterioration is 2.5-3% of cruise specific fuel consumption after 2500-3000 flights and mechanisms are thermal damage to blade tips with rubbing and damaged airfoils and parts.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 801118 , Aerospace Congress and Exposition; Oct 13, 1980 - Oct 16, 1980; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Investigation of performance deterioration of the CF6/JT9D, high-bypass ratio turbofan engines (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The aircraft energy efficiency program within NASA is developing technology required to improve the fuel efficiency of commercial subsonic transport aricraft. One segment of this program includes engine diagnostics which is directed toward determining the sources and causes of performance deterioration in the Pratt and Whitney Aircraft JT9D and General Electric CF6 high-bypass ratio turbofan engines and developing technology for minimizing the performance losses. Results of engine performance deterioration investigations based on historical data, special engine tests, and specific tests to define the influence of flight loads and component clearances on performance are presented. The results of analysis of several damage mechanisms that contribute to performance deterioration such as blade tip rubs, airfoil surface roughness and erosion, and thermal distortion are also included. The significance of these damage mechanisms on component and overall engine performance is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81552 , E-511 , AGARD Propulsion and Energetics Symp. on Turbine Engine Testing; Sep 29, 1980 - Oct 03, 1980; Turin|Oct 13, 1980 - Oct 16, 1980; Los Angeles
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    NASA/General Electric Engine Component Improvement Program (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Engine Component Improvement (ECI) Program has been initiated in connection with projects designed to reduce the impact of the world-wide energy crisis in the area of aviation. The two parts of the ECI program have the overall objective to identify and quantify the sources and causes of CF6 engine performance deterioration, and to reduce the fuel consumption of CF6 engines through the development and the incorporation of various performance improvement concepts. The CF6 high-bypass turbofan engine was selected as a basis for this effort, since it is expected to be a significant fuel user in commercial revenue service for the next 15 to 20 years. The first part of the ECI program represents the initial step in an effort to achieve a goal of five percent reduction in fuel usage for CF6 engines in the 1979-82 time period. The first performance improvement concept selected is an improved efficiency fan blade. Other improvements are related to a short core exhaust system and an improved high pressure turbine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-929 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Fuel consumption improvement in current transport engines (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A review is conducted of improvements which can be made with respect to the fuel consumption of current engines and new production versions of current engines. A description is presented of an engine diagnostics program which has the objective to identify and quantify the causes and sources of performance deterioration in the JT9D turbofan engine and to develop basic data which will be applied to minimize performance degradation of current and future engines. General areas where performance losses occur are examined, taking into account seals, blades and vanes, and cases. Potential performance improvement concepts are related to improved component aerodynamics, improved flowpath sealing, blade tip clearance control, improved turbine cooling effectiveness, improved turbine materials and coatings, duct and nozzle aerodynamic refinements, nacelle aerodynamic refinements, forced exhaust mixers, advanced nacelle materials, and advanced fuel control.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-930 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
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