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• W2008677237 abstract "This paper presents a RANS study of the hub clearance effects on the performance of a subsonic compressor stator. The inlet boundary conditions are from the calculation of inlet guide vanes. The k-ω SST turbulence model is adapted to resolve the Reynolds stresses. The present numerical results are compared with the experiment carried out at Technical University Berlin. The circumferentially averaged total pressure has a strong decrease in the lower span region from hub to nearly 50% channel height, while the tangential flow angle reduces from approximately 40% channel height to the hub, linearly. The above phenomenon indicates that the leakage flow in the gap between stator blade and the hub does not turn sufficiently. This leads to a smaller incidence angle of the flow to the stator, thus, the lower span of the stator works in smaller attack angle, 0 to 13 degrees lower than the higher span. Surface flow patterns on the hub and both side of the blade surfaces are compared with the oil flow visualization in the experiment. The compressor stator is shown to operate under large separation and strong back flow conditions. The hub leakage flow is studied together with the endwall flow phenomenon for full gap configuration. Two separation lines are observed on the hub. One is lying in front of the blade leading edge plane indicating the separation due to the leading edge leakage flow which spills out of the passage before the flow enters the passage. The other is caused by the interaction between the strong hub leakage flow and the incoming flow. This separation line undergoes an abrupt turning just after the flow leaving the stator passage. The effect of the hub gap size on the leakage flow and the whole flow passage in the stator, including the strength and location of the vortex structure, the location and size of the separation bubble, as well as the back flow behavior, is analyzed. With the help of a novel vortex identification method, the flow field of this subsonic compressor stator and the inlet guide vanes can be visualized illustrating the behavior at the operation point when rotating instability occurs. The parameter η4 can help identifying the stretching and relaxation of the vortex. This approach reveals significant flow details [1]. Combined with DPH (Dynamic Pressure Head) contour and streamlines, the detailed vortices structures and topology in a subsonic compressor can also be further elucidated. The study illustrates different vortices structures in the compressor, as well as their behavior in different gap size configurations." @default.
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• W2008677237 date "2012-06-11" @default.
• W2008677237 modified "2023-10-02" @default.
• W2008677237 title "Investigation of the Influence of Hub Gap Size to the Performance of a Subsonic Compressor Stator" @default.
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• W2008677237 doi "https://doi.org/10.1115/gt2012-68713" @default.
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