Marble, Frank E. (1955) Propagation of stall in a compressor blade row. Journal of the Aeronautical Sciences, 22 (8). pp. 541-554. ISSN 1936-9956 http://resolver.caltech.edu/CaltechAUTHORS:20110119-110427631
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Recent experimental observations on compressors, in particular those of Rannie and Iura, have clarified some features of the phenomenon of stall propagation. Using these observations as a guide, the process of stall in an airfoil cascade has been characterized by a static pressure loss across the cascade which increases discontinuously at the stall angle, the turning angle being affected in only a minor way. Deductions from this simple model yield the essential features of stall propagation such as dependence of the extent of stalled region upon operating conditions, the pressure loss associated with stall, and the angular velocity of stall propagation. Using two-dimensional approximation for a stationary or rotating blade row, free from interference of adjacent blade rows, extent of the stalled region, the total pressure loss and stall propagation speed are discussed in detail for a general cascade characteristic. Employing these results, the effect of stall propagation upon the performance of a single-stage axial compressor is illustrated and the mechanism of entering the regime of stall propagation is discussed. The essential points of the results seem to agree with experimental evidence.
|Additional Information:||© 1955 Institute of the Aeronautical Sciences. Received April 7, 1954. This work was performed, in part, under the financial support of the Office of Scientific Research, United States Air Force|
|Group:||Guggenheim Jet Propulsion Center|
|Other Numbering System:|
|Official Citation:||Propagation of Stall in a Compressor Blade Row pages 541-554 Frank E. Marble Journal of the Aeronautical Sciences (1936-9956) 1955 vol. 22 no. 8|
|Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Ruth Sustaita|
|Deposited On:||26 Jan 2011 17:53|
|Last Modified:||26 Dec 2012 12:51|
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