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

Abstract

The paper presents two-dimensional cascade results which have been obtained in transonic and supersonic cascade windtunnels. The upstream Mach number range is 1,0 ≤ M1 ≤ 1,4. Tests have been 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 has been 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.

Transonic Flow Along Arbitrary Stream Filament of Revolution Solved by Separate Computations With Shock Fitting

“…The effect of variation of stream filament of revolution has been investigated in the special case of linear cascade (either subsonic or transonic, see, for example, Refs. [19] and [20]), in terms of the flow variable axial velocity density ratio [2, which is related to the ratio of stream filament T at inlet to that at the exit as follows:…”

Utilization of Cascade Data in Axial-Flow Compressor Design and Analysis: A Critical Review

“…esting to note that, with the exception of work at Much of the recent work has been concentrated Braunschweig (38), two-dimensional cascade data on studies of blade profiles for high Mach number over a range of Reynolds number are very scarce. (transonic and supersonic) applications (28)(29)(30)(31)(32).…”