Accession Number : AD0860339

Title :   Study of Supersonic Compressors,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH

Personal Author(s) : Conrad, O. ; Pleiss, J. ; Weber, T.

Report Date : 18 FEB 1969

Pagination or Media Count : 38

Abstract : Based on measuring data for a number of supersonic cascades, assumptions were made on presumably obtainable total pressure ratios in shock-in rotors, impulse rotors and guide vanes. Starting from these assumptions, the stage efficiencies and the stage pressure ratios were calculated and compared for supersonic compressors with shock-in rotors and impulse rotors. According to these calculations, the impulse compressors are better for smaller ratios, whereas the shock-in compressors are better for high pressure ratios. Furthermore, it is clearly shown that there exists an obvious connection between the diffusion factor and the loss coefficient for a very carefully measured high-deflection supersonic rotor, and that the calculated loss coefficient coincides fairly accurately with the measured value, when separate calculations are made for the supersonic and the subsonic friction, and when calculating the shock losses with the maximum Mach number on the suction surface, and also when taking the radial streamline displacement into consideration. The calculated losses are above the measured values when the ratio of the static pressures at the cascade exit and in front of the shock is below that pressure ratio, at which, with an oblique shock on flat plane, separation occurs. (Author)

Descriptors :   (*AXIAL FLOW COMPRESSORS, SUPERSONIC CHARACTERISTICS), PRESSURE, CASCADE STRUCTURES, SHOCK WAVES, EFFICIENCY, WEST GERMANY.

Subject Categories : Hydraulic and Pneumatic Equipment
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE