IGTC-64 RESEARCH ON SUPERSONIC DIFFUSERS OF CENTRIFUGAL COMPRESSOR BY MEANS OF SWIRL FLOW (1ST REPORT) : FLOW IN A DIFFUSER AT VARIOUS MACH NUMBERS(Session B-7 Aerodynamics V (Radial Flow))

概要

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To investigate supersonic diffusers of centrifugal compressors a test rig was built where the swirl flow was induced by inward swirl nozzles. Test diffusers demonstrated reasonably high pressure recovery coefficient even at very high Mach numbers. However, the stall limits of diffusers at positive and negative incidence angles were not clarified because it was not possible to change the flow angle in a wide range. The influence of the inlet velocity distribution on the pressure recovery of a diffuser was quite significant. Therefore, the quantitative results of a diffuser obtained in a test rig is not directly applicable to the diffuser in a different rig where distortion of the inlet velocity distribution is somewhat different. However, the present test rig is suitable to compare the performances of different diffusers which are designed for the same application and to choose the best design. Also presented are many problems which have to be overcome to make a test rig for supersonic diffusers of centrifugal compressors.
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