The effect of tip clearance flow on compressor performance

Shih-Hsiung Chen, Chwei Ru Tsai

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Complex turbomachinery tip clearance flow field was investigated using a finite volume computational method which solves three-dimensional Reynoldsaveraged Navier-Stokes equations. Compressor vanes with NACA65-1810 blade section and tip clearances were tested. The formation of the leakage vortex flow caused by pressure gradient across blades and its interactions with blade passage secondary vortex flow were examined. The solutions were compared with known data. Very good agreements were achieved in predicting the flow structures in both the blade channel and the tip clearance region. It was found that the mechanism of the tip clearance effect on compressor performance is due to the interactions between the passage vortex of lower energy loss and the tip leakage vortex of higher energy loss. At certain tip clearance, the two vortices closely interact with each other and the overall vorticity strength is reduced. The total energy loss is thus a minimum and it can be considered as an optimum tip clearance.

Original languageEnglish
Title of host publication34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Publication statusPublished - 1998
Event34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998 - Cleveland, United States
Duration: 1998 Jul 131998 Jul 15

Other

Other34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
CountryUnited States
CityCleveland
Period98-07-1398-07-15

Fingerprint

Compressors
Vortex flow
Energy dissipation
Turbomachinery
Flow structure
Computational methods
Vorticity
Pressure gradient
Navier Stokes equations
Turbomachine blades
Flow fields

All Science Journal Classification (ASJC) codes

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

Cite this

Chen, S-H., & Tsai, C. R. (1998). The effect of tip clearance flow on compressor performance. In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit American Institute of Aeronautics and Astronautics Inc, AIAA.
Chen, Shih-Hsiung ; Tsai, Chwei Ru. / The effect of tip clearance flow on compressor performance. 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1998.
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author = "Shih-Hsiung Chen and Tsai, {Chwei Ru}",
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Chen, S-H & Tsai, CR 1998, The effect of tip clearance flow on compressor performance. in 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States, 98-07-13.

The effect of tip clearance flow on compressor performance. / Chen, Shih-Hsiung; Tsai, Chwei Ru.

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1998.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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Chen S-H, Tsai CR. The effect of tip clearance flow on compressor performance. In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA. 1998