The report describes experimental research conducted with a linear, stationary, supersonic compressor cascade with blades of constant spanwise geometry and contoured sidewalls. The cascade incorporated splitter vanes midway between blades in the latter half of each blade passage. A prior investigation with this cascade was conducted without splitter vanes and was reported previously. The principal objective of that program was to obtain cascade-type data for a selected blade element from a compressor configuration resulting from the Aerospace Research Laboratories in-house program of research on supersonic axial compressors. Splitter vanes, designed in a manner similar to those used in the rotor, were incorporated in the supersonic compressor cascade. Additional work was conducted and the primary objective was to obtain cascade-type data for the particular compressor blade-splitter vane combination. (Modified author abstract)
Test of a Supersonic Compressor Cascade with Splitter Vanes
1973
471 pages
Report
No indication
English