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首页> 美国政府科技报告 >Investigation of the Surge Behavior of a High-Speed Ten-Stage Axial Flow Compressor.
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Investigation of the Surge Behavior of a High-Speed Ten-Stage Axial Flow Compressor.

机译：高速十级轴流压气机喘振行为的研究。

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摘要

During a ten-stage compressor rig test conducted at Wright-Patterson AFB, several instances of compressor surge were observed. While surge is known to occur in high-speed multi-stage compressors, very little transient data pertaining to such events exists in the open literature, exclusive of engine data. In an attempt to make more data of this type available to researchers, surge data from this test are presented in this report. The predictions of a computer-based transient compressor model are compared to the data for study. Furthermore, an unexplained instability phenomenon is investigated: a constant surge/rotating stall boundary. During the test, it was found that the speed boundary between surge and rotating stall occurred between 80% and 81% rotor speed. This boundary did not change when the compressor discharge volume was changed. This seemed to contradict accepted theory, which predicts a shift in the surge/rotating stall boundary. An investigation into the possible causes of this phenomenon is conducted as part of this report. Several theories are explored, including the possibility of excess volume communicating with the compressor during instability. Although the excess volume theory is not proven, it remains the most likely cause of the unusual surge/rotating stall boundary behavior. Compressor Surge, Axial Compressor, Surge Performance, Aircraft Turbine Engine, Discharge Volume Effects.

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