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Altitude Evaluation of a Variable Cycle Turbofan Engine
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Abstract
This paper presents the results of an altitude test evaluation of a variable-cycle turbofan engine. The test engine was a medium-bypass, two-spool turbofan engine modified to incorporate variable inlet guide vanes and first-stage stators in the low-pressure compressor, variable first-stage stator vanes in the low-pressure turbine, and variable area fan and primary exhaust nozzles. The results of the testing indicated that these variable-geometry components offer potential improvements to the following problem areas in multimission aircraft at off-design conditions: inlet spillage drag and exhaust-system boattail drag, compressor surge-margin control, airframe bleed-air extraction effects on engine performance, and performance limited by engine operating limits.
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Citation
Stephenson, D., Davenport, W., and Topping, R., "Altitude Evaluation of a Variable Cycle Turbofan Engine," SAE Technical Paper 740806, 1974, https://doi.org/10.4271/740806.Also In
References
- Brimelow Brian “Performance Matching of the Propulsion System.” SAE Transactions 77 1968 Paper 680712
- Ramsey J. W. Oates G. C. “Potential Operating Advantages of a Variable Area Turbine Turbojet.” ASME Paper 72 WA/AERO-4 1972
- May, R. J. Jr. Zavatsky W. F. “Influence of Variable Turbine Geometry on Engine Installation Losses and Cycle Selection.” Proc. of 1972 JANNAF Propulsion Meeting (Aircraft Propulsion Session) 1972
- Steele M. C. Roberts F. L. “Highlights of the Design and Development of a Modern Geared-Fan Jet Engine.” Paper 720351 presented at SAE National Business Aircraft Meeting Wichita March 1972
- Davenport W. R. Dixon G. J. “The Garrett-AiResearch Variable-Cycle TFE731 Turbofan Engine.” Paper 730918 presented at SAE National Aerospace Engineering Meeting Los Angeles October 1973