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Cf6 jet engine performance improvement program: high pressure turbine aerodynamic performance improvement
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Fasching, W. A. |
| Copyright Year | 1980 |
| Description | The improved single shank high pressure turbine design was evaluated in component tests consisting of performance, heat transfer and mechanical tests, and in core engine tests. The instrumented core engine test verified the thermal, mechanical, and aeromechanical characteristics of the improved turbine design. An endurance test subjected the improved single shank turbine to 1000 simulated flight cycles, the equivalent of approximately 3000 hours of typical airline service. Initial back-to-back engine tests demonstrated an improvement in cruise sfc of 1.3% and a reduction in exhaust gas temperature of 10 C. An additional improvement of 0.3% in cruise sfc and 6 C in EGT is projected for long service engines. |
| File Size | 21546895 |
| Page Count | 155 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800017803 |
| Archival Resource Key | ark:/13960/t3cz81j3r |
| Language | English |
| Publisher Date | 1980-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Turbine Blades Aircraft Engines Engine Tests Gas Temperature High Pressure Stress-strain Relationships Exhaust Gases Trailing Edges Thermodynamic Properties Aerodynamic Characteristics Leading Edges Turbine Engines Heat Transfer 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 |
