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Some aspects of inlet/engine flow compatibility

Published online by Cambridge University Press:  04 July 2016

D. D. Williams  and
J. O. Yost
D. D. Williams
Affiliation:
Rolls-Royce (1971) Limited, Bristol Engine Division
J. O. Yost
Affiliation:
Rolls-Royce (1971) Limited, Bristol Engine Division
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Extract

The aim of this paper is to contribute to the growing subject of inlet/engine compatibility a discussion of some of the more interesting results of research and development testing of rig compressors and engines carried out at the Bristol Engine Division of Rolls-Royce (1971) Ltd, and to discuss these against a now extensive background literature.

The effects of an inlet system on an axial flow gas turbine are principally on performance, stability and mechanical integrity. In this paper attention is focused on the effects of total pressure distortion on the compressor system's performance and stability.

Type
Supplementary Paper
Information
The Aeronautical Journal , Volume 77 , Issue 753 , September 1973 , pp. 483 - 492
Copyright
Copyright © Royal Aeronautical Society 1973 

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References

1. Schaub, U. W. and Bassett, R. W. Flow distortion and performance measurements on a 12in fan-in-wing model for a range of forward speeds and angle of attack settings. Paper 17, AGARD Conference Proceedings No 91 Inlets and nozzles for aerospace engines. September 1971. Sandefjord, Norway.Google Scholar
2. Tyson, B. I. Tests to establish flow distortion criteria for lift engines. AIAA Paper 64-608. August 1964. Seattle, Washington.Google Scholar
3. Plourde, G. A. and Brimelow, B. Pressure fluctuations cause compressor instability. Proceedings of the Air Force Airframe—Propulsion Compatibility Symposium AFAPL- TR-69-103. June 1970. Wright-Paterson AFB. Ohio.Google Scholar
4. Bowditch, D. N., Coltrin, R. E., Sanders, N. E., Sorensen, N. E., Wasserbauer, J. F. Supersonic cruise inlets. Paper IX, NASA Conference Proceedings SP-259. November 1970. Lewis Research Centre, Cleveland, Ohio.Google Scholar
5. Povolny, J. H., Burcham, F. W. Jr, Calogeras, J. E., Mayer, C. L., Rudey, R. A. Effects of engine inlet disturbance on engine stall performance. Paper X, NASA Conference Proceedings SP-259. November 1970. Lewis Research Centre, Cleveland, Ohio.Google Scholar
6. Ellis, S. H. Inlet-engine compatibility analysis. Paper 26, AGARD Conference Proceedings No 91 Inlets and Nozzles for Aerospace Engines. September 1971. Sandefjord, Norway.Google Scholar
7. Bellman, D. R. and Hughes, D. L. The flight investigation of pressure phenomena in the air intake of an F111 A airplane. AIAA Paper 69-488. June 1969. USAF Academy, Colorado.Google Scholar
8. Burcham, F. W. Jr, and Hughes, D. L. Analysis of in flight pressure fluctuations leading to engine compressor surge in an F111A airplane for mach numbers to 2.17. AIAA Paper 70-624. June 1970. San Diego, California.Google Scholar
9. Dunham, J. Non-axisymmetric flow in axial compressors. Mechanical Engineering Science, Monograph No 3. October 1965.Google Scholar
10. Plourde, G. A. and Stenning, A. H. The attenuation of circumferential inlet distortion in multi-stage axial compressors. J. Aircraft, Vol 5, No 3. May-June 1968.Google Scholar
11. Callahan, G. M. and Stenning, A. H. Attenuation of inlet flow distortion upstream of axial flow compressors. AIAA 69-485. June 1969. USAF Academy, Colorado.Google Scholar
12. Reid, C. The response of axial flow compressors to intake flow distortion. ASME Paper 69-GT-29. Gas Turbine Conference and Products Show. March 1969. Cleveland, Ohio.Google Scholar
13. Langston, C. E. Distortion tolerance by design instead of by accident. ASME Paper 69-GT-115. Gas Turbine Conference and Products Show. March 1969, Cleveland, Ohio.Google Scholar
14. Yost, J. O. Design of Olympus 593 for Concorde. Bristol Siddeley/SNECMA Olympus 593 Powerplant Presentation. May 1965.Google Scholar
15. Cotter, H. N. Integration of inlet and engine—an engine man's point of view. SAE Paper 680286. Air Transportation Meeting. April-May 1968. New York.Google Scholar
16. Calogeras, J. E., Mehalic, C. M., and Burstadt, P. L. Experimental investigation of the effect of screen-induced total-pressure distortion on turbojet stall margin. TMX- 2239. 1971. NASA, Cleveland, Ohio.Google Scholar
17. Campbell, J. L. and Ellis, S. H. Engine/inlet compatibility analysis procedure. AIAA Paper 70-941. June 1970.Google Scholar
18. Brunda, D. F. and Boytos, J. F. A steady-state circumferential inlet pressure distortion index for axial-flow compressors. Proceedings of the 10th National Conference on the Environmental Effects on Aircraft and Propulsion Systems. NATPC Paper 71-ENV-12. May 1971.Google Scholar
19. Sears, R. S. Some aspects of non-stationary airfoil theory and its practical application. Journal of the Aeronautical Sciences. October 1952.Google Scholar
20. Horlock, J. H. Fluctuating lift forces on aerofoils moving through transverse and chordwise gusts. Journal of Basic Engineering. December 1968.Google Scholar
21. Schorr, B. and Reddy, K. C. Inviscid flow through cascades in oscillatory and distorted flow. AIAA Paper 70-131. January 1970. 8th Aerospace Sciences Meeting, New York.Google Scholar
22. Tyler, R. D. One-dimensional treatment of non-uniform flow. R & M 2991. 1954.Google Scholar
23. De Marquis, , and Wyatt, D. Analysis of errors introduced by several methods of weighting non-uniform duct flows. NACA TN3400. Lewis Laboratory, Cleveland, Ohio. 1954.Google Scholar
24. Livesey, J. L. and Hugh, T. Suitable mean values in one-dimensional gas dynamics. Journal Mechanical Engineering Science, Vol 8, No 4. 1966.Google Scholar
25. Lubick, R. J. and Wallner, L. E. Stall prediction in gas turbine engines. Journal of Basic Engineering. September 1959.Google Scholar
26. Kuhlberg, J. F., Sheppard, D. E., King, E. O. and Baker, J. R. The dynamic simulation of turbine engine compressors. AIAA Paper 69-486. Fifth Propulsion Joint Specialist Conference, Colorado. June 1969.Google Scholar
27. Willoh, R. G. and Seldner, K. Multi-stage compressor simulation applied to the prediction of axial flow instabilities. TM-X-1880. 1969. NASA, Cleveland, Ohio.Google Scholar
28. Corbett, A. G. and Elder, R. L. The stability of some mathematical models of an axial flow compressor. University of Leicester—Rolls-Royce Research Study. 1970-72.Google Scholar