Energy efficient engine preliminary design and integration study
The technology and configurational requirements of an all new 1990's energy efficient turbofan engine having a twin spool arrangement with a directly coupled fan and low-pressure turbine, a mixed exhaust nacelle, and a high 38.6:1 overall pressure ratio were studied. Major advanced technology design features required to provide the overall benefits were a high pressure ratio compression system, a thermally actuated advanced clearance control system, lightweight shroudless fan blades, a low maintenance cost one-stage high pressure turbine, a short efficient mixer and structurally integrated engine and nacelle. A conceptual design analysis was followed by integration and performance analyses of geared and direct-drive fan engines with separate or mixed exhaust nacelles to refine previously designed engine cycles. Preliminary design and more detailed engine-aircraft integration analysis were then conducted on the more promising configurations. Engine and aircraft sizing, fuel burned, and airframe noise studies on projected 1990's domestic and international aircraft produced sufficient definition of configurational and advanced technology requirements to allow immediate initiation of component technology development.
- Research Organization:
- Pratt and Whitney Aircraft, East Hartford, CT (USA). Commercial Products Div.
- DOE Contract Number:
- NAS3-20628
- OSTI ID:
- 6010087
- Report Number(s):
- N-79-12084
- Country of Publication:
- United States
- Language:
- English
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33 ADVANCED PROPULSION SYSTEMS
TURBOJET ENGINES
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FUEL CONSUMPTION
CONTROL SYSTEMS
FUEL ECONOMY
NOISE
ENERGY CONSUMPTION
ENGINES
320201* - Energy Conservation
Consumption
& Utilization- Transportation- Air & Aerospace
330103 - Internal Combustion Engines- Turbine