Accession Number : AD0715187

Title :   Some Experimental Results of Two-Dimensional Compressor Cascades at Supersonic Inlet Velocities,

Corporate Author : DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V PORZ-WAHN (WEST GERMANY)

Personal Author(s) : Starken,H. ; Lichtfusse,H. J.

Report Date : 08 DEC 1969

Pagination or Media Count : 9

Abstract : The paper presents two-dimensional cascade results which were obtained in transonic and supersonic cascade windtunnels. The upstream Mach number range is 1.0 < or = M < or = 1.4. Tests were carried out with three different blade shapes; these are double-circular-arc and wedge profiles. The influence of solidity on the performance of these cascades was investigated. A detailed analysis and calculation of the shock losses shows the great influence of profile shape on the total pressure loss coefficient. The profile losses are roughly constant in the investigated Mach number range. In addition, some measurements for different back pressures are presented. These results are analyzed with the aid of a simple calculation, which shows that the axial velocity-density ratio has to be considered as an important parameter in supersonic cascade measurements. (Author)

Descriptors :   (*AXIAL FLOW COMPRESSORS, CASCADE STRUCTURES), SUPERSONIC CHARACTERISTICS, TWO DIMENSIONAL FLOW, AXIAL FLOW COMPRESSOR BLADES, PRESSURE, WEST GERMANY

Subject Categories : Hydraulic and Pneumatic Equipment

Distribution Statement : APPROVED FOR PUBLIC RELEASE