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Preliminary study of optimum ductburning turbofan engine cycle design parameters for supersonic cruising
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Fishbach, L. H. |
| Copyright Year | 1978 |
| Description | 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 wverall 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. |
| File Size | 2078352 |
| Page Count | 30 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790003912 |
| Archival Resource Key | ark:/13960/t6256dw0p |
| Language | English |
| Publisher Date | 1978-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Variable Cycle Engines Pressure Effects Supersonic Combustion Supersonic Aircraft Engine Design Engine Inlets Fuel Consumption Turbofan Engines Propulsion System Configurations Optimization Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
