周向槽机匣处理对某跨音转子性能的影响

doi:10.7527/S1000-6893.2013.0546

Abstract

Abstract:

In order to investigate the influence of casing treatment on compressor stability and to study its flow mechanism, numerical investigations are conducted to study the influence of circumferential casing grooves on the transonic compressor performance in Rotor37. A series of circumferential grooves with different depths are studied. The simulations reveal that the tip leakage vortex breaks down due to the interaction with passage shock and forms a recirculation zone which is mainly responsible for the onset of rotating stall. Circumferential casing grooves are able to delay stalls significantly. As a function of groove depth, the stall margin increment has two peaks. The stall margin increases by 6.7% and 7.3% with optimum shallow grooves and deep grooves, respectively, while the former result in even less loss in efficiency.The flow mechanism of stall margin improvement is that the casing treatment is able to reduce or even eliminate the recirculation zone caused by the tip leakage vortex breakdown. An analysis from the angle of momentum theorem is then carried out to explain the mechanism for shallow and deep grooves,respectively.

Key words: compressor, transonic compressor, stall margin, casing treatment, circumferential groove, tip leakage flow

CLC Number:

V231.3
TK12

DUAN Zhenzhen, LIU Yangwei, LU Lipeng. Influence of Circumferential Casing Grooves on Transonic Compressor Rotor Performance[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(8): 2163-2173.

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Influence of Circumferential Casing Grooves on Transonic Compressor Rotor Performance

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