Numerical loss analysis on slot-type casing treatment in a transonic compressor stage

• Autorzy: Zhu M.-M. , Qiang X.-Q. , Teng J.-F.

Identyfikatory

DOI

10.15632/jtam-pl.55.1.293

• Języki publikacji: EN

Abstrakty

EN

To understand the loss mechanism of slot-type casing treatment, a numerical loss analysis has been carried out in a 1.5 axial transonic compressor stage with various slots. Spanwise and streamwise distribution curves of pitch-averaged entropy have been presented to survey the development of loss generation. Further, detailed entropy distributions at eight axial cuts, which have been taken through the blade row and slots, have been further analyzed to interpret the loss mechanism. The most dramatic loss growth occurred above 95% span, which directly resulted from slots injection flow upstream the leading edge. Loss generations with smooth casing have been primarily ascribed to low-momentum tip leakage flow/vortex and suction surface separation at the leading edge. CU0 slot, the arc-curved slots with 50% rotor tip exposure, has been capable of suppressing the suction surface separation loss. Meanwhile, accelerated tip leakage flow brought about additional loss near the casing and pressure surface. Upstream high entropy flow would be absorbed into the rear portion of slots repeatedly, which resulted in further loss.

Słowa kluczowe

EN

axial compressor; numerical simulation; slot-type casing treatment; loss mechanism; tip leakage flow

• Wydawca: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
• Czasopismo: Journal of Theoretical and Applied Mechanics
• Rocznik: 2017
• Tom: Vol. 55 nr 1
• Strony: 293--306
• Opis fizyczny: Bibliogr. 13 poz., rys., tab.

Twórcy

autor

Zhu M.-M.

• School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China

autor

Qiang X.-Q.

• School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China

autor

Teng J.-F.

• School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China

Bibliografia

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• 9. Reid L., Moore D., 1978, Performance of a single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio 1.82, NASA TP-1338
• 10. Takata H., Tsukuda Y., 1977, Stall margin improvement by casing treatment – its mechanism and effectiveness, Journal of Engineering for Power, 99, 1, 121-133
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• 12. Yu Q., Li Q., Li L., 2002, The experimental researches on improving operating stability of a single stage transonic fan, ASME, GT2002-30640
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Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017)