Accession Number : AD0668110

Title :   SLIPPING STALL,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Pryadilov,A. I.

Report Date : 18 AUG 1967

Pagination or Media Count : 17

Abstract : Phenomena are described of a 'slipping' blade-tip stall in an axial 100%-reaction compressor. The slipping stall is defined as a series of adjacent local stalls that arise when dP/d alpha becomes negative, where P is the lift force and alpha is the angle of attack. A gas leakage scheme in the stalling zone is considered, and formulas that describe the stall are developed. It is found that: (1) The rotating slipping stall is a self-oscillatory process whose energy is taken from the compressed gas; (2) The stall is caused by a sudden change in gas-flow conditions at the runner blades; (3) The analysis presented in the article permits evaluating, in the first approximation, the effect of runner rpm upon the speed of stalling and upon the flow-pulsation amplitude with a constant throttle resistance. (Author)

Descriptors :   (*AXIAL FLOW COMPRESSORS, *STALLING), AXIAL FLOW COMPRESSOR BLADES, PERFORMANCE(ENGINEERING), ANGLE OF ATTACK, LIFT, ROTATION, GAS FLOW, VELOCITY, AERODYNAMIC CHARACTERISTICS, USSR

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE