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COMPRESSOR STALL PROBLEMS IN GAS-TURBINE-TYPE AIRCRAFT ENGINES
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Abstract
This paper was presented at the SAE National Aeronautic Meeting, New York, April 12, 1956.
STALL of axial-flow-type compressors limits the flexibility of operation of 1- and 2-spool aircraft turbojet engines. Complete compressor stall or surge is a problem with regard to engine acceleration as well as low-and high-Mach-number flight at high altitudes.
Deterioration of compressor performance due to low Reynolds numbers at extreme altitudes aggravates the stall problem. Inlet-flow distortions increase the severity of this problem, particularly for supersonic flight.
Rotating stall at low values of equivalent rotative speed is a serious source of blade vibrational failure. This latter problem is also aggravated by inlet-flow distortions.
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Benser, W. and Finger, H., "COMPRESSOR STALL PROBLEMS IN GAS-TURBINE-TYPE AIRCRAFT ENGINES," SAE Technical Paper 570020, 1957, https://doi.org/10.4271/570020.Also In
References
- “Inlet-Duct Engine-Flow Compatibility,” Alford J. S. Paper presented at Fifth International Aeronautical Conference June 1955
- “Turbine-Engine Stall from Design Point of View,” Alford J. S. Paper presented at SAE National Aeronautic Meeting April 12 1956
- “Control Approaches to Solution of Compressor Stall,” Gebhardt W. A. and Bodemuller P. Paper presented at SAE National Aeronautic Meeting April 12 1956
- “A Customer's View on Turbine-Engine Stall,” Jones Major K. L. Paper presented at SAE National Aeronautic Meeting April 12 1956
- “Compressor Surge and Stall Propagation,” Emmons, H. W. Pearson, C. E. and Grant H. P. Paper presented at ASME Meeting 1953
- Journal of Aeronautical Sciences, Vol. 20 December 1953 835 845 “Some Stall and Surge Phenomena in Axial-Flow Compressors,” Huppert M. C. and Benser W. A.
- NACA TN 1941 September 1949 “Attainable Circulation of Airfoils in Cascade,” Goldstein A. W. and Mager A.