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Future trends in aero gas turbine design—Unconventional engines

Published online by Cambridge University Press:  04 July 2016

R. M. Denning
Affiliation:
Rolls-Royce (1971) Limited, Aero Division
S. C. Miller
Affiliation:
Rolls-Royce (1971) Limited, Aero Division
G. H. Wright
Affiliation:
Rolls-Royce (1971) Limited, Aero Division

Extract

The first part of this paper was concerned with the evaluation of the now classic form of low noise, single stage front fan engine as used on all contemporary designs of large subsonic civil aircraft.

This second part deals with other forms of the aircraft gas turbine which we have categorised as unconventional in the sense that they seek to achieve one or more of the following objectives:

  1. (a) a superior performance by moving towards more extreme constant pressure gas turbine cycles;

  2. (b) a superior performance by use of a different thermo-dynamic/propulsive system;

  3. (c) a performance which requires an ability to modify the thermodynamic cycle at different flight conditions;

  4. (d) uses for the engine which are additional to the normal propulsive role.

In the main, these engines are, as their title suggests, not generally adopted as powerplants for production aircraft and their often specialist role must detract from their wide use in a range of aircraft. However, it could be argued that the classic design of engine will soon be approaching a plateau of achievement and therefore some degree of unconventional form will be required in future to advance aircraft performance.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 1976 

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References

1. Rohrbach, C. and Metzger, F. B. The prop-fan—a new look in propulsors. AIAA Paper No 75-1208.Google Scholar
2. Gatzen, B. S. and Hudson, S. M. General characteristics of fuel conservative prop-fan propulsion system. SAE Paper 751085.Google Scholar
3. Young, P. H. The heat exchanger cycle—Has its time come? AIAA Paper 75-961.Google Scholar
4. Kraft, G. and Stack, W. Preliminary study of advanced turboprops for low energy consumption. NASA TMX-71740.Google Scholar
5. Povinelli, F. P., Klinebery, J. M. and Kramer, J. J. Improving aircraft energy efficiency. Astronautics and Aeronautics, February 1976.Google Scholar
6. Calder, P. H. and Gupta, P. C. Future SST engines with particular reference to Olympus 593 evolution and Concorde experience. SAE Paper 751056.Google Scholar
7. Goldsmith, H. A. and Leyman, C. S. Aircraft considerations for advanced SST propulsion systems. 3rd International Symposium on Air Breathing Engines. (ICAS) Paper 76-035, March 1976.Google Scholar
8. Swan, W. C. Performance problems related to installation of future engines in both subsonic and supersonic transport aircraft. 2nd International Symposium on Air Breathing Engines, (ICAS), Sheffield, March 1974.Google Scholar
9. Whitley, D. C. The augmentor wing. Powered lift STOL —a proven concept. De Havilland Aircraft Canada Ltd. Interavia 2/1974. Used to produce Fig. 23.Google Scholar