JT8D high pressure compressor performance improvement
Technical Report
·
OSTI ID:5316684
An improved performance high pressure compressor with potential application to all models of the JT8D engine was designed. The concept consisted of a trenched abradable rubstrip which mates with the blade tips for each of the even rotor stages. This feature allows tip clearances to be set so blade tips run at or near the optimum radius relative to the flowpath wall, without the danger of damaging the blades during transients and maneuvers. The improved compressor demonstrated thrust-specific fuel consumption and exhaust gas temperature improvements of 1.0% and at least 10/sup 0/C over the takeoff and climb power range at sea level static conditions, compared to a bill-of-material high pressure compressor. Surge margin also improved 4 percentage points over the high power operating range. A thrust-specific fuel consumption improvement of 0.7% at typical cruise conditions was calculated based on the sea level test results.
- Research Organization:
- Pratt and Whitney Aircraft, East Hartford, CT (USA)
- OSTI ID:
- 5316684
- Report Number(s):
- NASA-CR-165531
- Country of Publication:
- United States
- Language:
- English
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