Preliminary study of optimum ductburning turbofan engine cycle design parameters for supersonic cruising
The effect of turbofan engine overall pressure ratio, fan pressure ratio, and ductburner temperature rise on the engine weight and cruise fuel consumption for a mach 2.4 supersonic transport was investigated. Design point engines, optimized purely for the supersonic cruising portion of the flight where the bulk of the fuel is consumed, are considered. Based on constant thrust requirements at cruise, fuel consumption considerations would favor medium by pass ratio engines (1.5 to 1.8) of overall pressure ratio of about 16. Engine weight considerations favor low bypass ratio (0.6 or less) and low overall pressure ratio (8). Combination of both effects results in bypass ratios of 0.6 to 0.8 and overall pressure ratio of 12 being the overall optimum.
- Research Organization:
- National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
- OSTI ID:
- 6202845
- Report Number(s):
- N-79-12083
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
320201* -- Energy Conservation
Consumption
& Utilization-- Transportation-- Air & Aerospace
33 ADVANCED PROPULSION SYSTEMS
330103 -- Internal Combustion Engines-- Turbine
AIR TRANSPORT
AIRCRAFT
DESIGN
ENERGY CONSUMPTION
ENGINES
FUEL CONSUMPTION
PRESSURE DEPENDENCE
SUPERSONIC TRANSPORT
TEMPERATURE DEPENDENCE
TRANSPORT
TURBOJET ENGINES
WEIGHT