Accession Number : AD0673943

Title :   CONCERNING THE FLOW STALL BOUNDARY IN COMPRESSOR VANE SYSTEMS (O GRANITSE SRYVA POTOKA V KOMPRESSORNYKH RESHETKAKH),

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Fedorov,R. M.

Report Date : 30 AUG 1967

Pagination or Media Count : 14

Abstract : The choice of parameters and the design of axial compressor stages are closely related to the determination of the critical angle of attack corresponding to the limit of disruptionless flow around compressor grids. Various researchers are trying to select the pertinent parameters and determine the discontinuity limits on the basis of the theory of the boundary layer. The paper discusses, on the basis of the analysis of the disruption condition (for a typical velocity distribution over the upper surface of the profile), the approximate solution of the problem of determination of the limit of disruptionless flow around plane compressor grids of differing densities and staggers. It is shown that the degree of attenuation of the flow along the upper surface of the profile may serve as the quantitative criterion of the flow discontinuity. The results of the calculations are in very good agreement with experimental data concerning the flows through compressor grids at low M numbers of the incident current. (Author)

Descriptors :   (*AXIAL FLOW COMPRESSORS, STALLING), BOUNDARY LAYER, ANGLE OF ATTACK, COMPRESSOR BLADES, ATTENUATION, SURFACE PROPERTIES, FLOW SEPARATION, USSR

Subject Categories : Hydraulic and Pneumatic Equipment

Distribution Statement : APPROVED FOR PUBLIC RELEASE