Casing Treatment for Desensitization of Compressor Performance and Stability to Tip Clearance

Author:

Cevik Mert1,Duc Vo Huu2,Yu Hong3

Affiliation:

1. Department of Mechanical Engineering, École Polytechnique de Montréal, 2900 boulevard Edouard-Montpetit, 2500 chemin de Polytechnique, Montreal, QC H3T 1J4, Canada e-mail:

2. Mem. ASME Department of Mechanical Engineering, École Polytechnique de Montréal, 2900 boulevard Edouard-Montpetit, 2500 chemin de Polytechnique, Montreal, QC H3T 1J4, Canada e-mail:

3. Pratt and Whitney Canadal, 1801 Courtneypark Drive East, Mississauga, ON L5T 1J3, Canada e-mail:

Abstract

This paper presents the development of a novel casing treatment to reduce compressor performance and stall margin sensitivities to tip clearance increase. A linked research project on blade design strategies for desensitization had discovered two flow features that reduce sensitivity to tip clearance, namely increased incoming meridional momentum in the rotor tip region and reduction/elimination of double tip leakage flow. Double tip leakage flow is the flow that exits one tip clearance and enters the tip clearance of the circumferentially adjacent blade instead of convecting downstream out of the blade passage. A new and practical casing treatment was developed and analyzed through Reynolds-averaged Navier–Stokes (RANS) computational fluid dynamics (CFD) simulations to decrease double tip leakage and reduce or even eliminate performance and stall margin sensitivity to tip clearance size. The casing treatment design consists of sawtooth-shaped circumferential indentations placed on the shroud over the rotor with a depth on the order of the tip clearance size. A detailed analysis of the flow field allowed for the elucidation of the flow mechanism associated with this casing treatment. A computational parametric study gave preliminary design rules for minimizing both performance/stall margin sensitivity to tip clearance and nominal performance loss. An improved casing indentation design was produced for which CFD simulations showed a complete desensitization of pressure ratio and stall margin while reducing efficiency sensitivity significantly for the tip clearance range studied with only a very small penalty in nominal pressure ratio. Further simulations showed that this casing treatment can be combined with desensitizing blade design strategies to further reduce tip sensitivity and reduce/eliminate/reverse nominal performance penalty. Lastly, preliminary CFD simulations on an axial compressor stage indicate that this shallow indentations' casing treatment strategy remains effective in a stage environment.

Publisher

ASME International

Subject

Mechanical Engineering

Reference30 articles.

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2. Effect of Tip Clearance Flow on Compressor Stability and Engine Performance,1985

3. Tip Clearance Effect on High-Pressure Compressor Stage Matching;Proc. Inst. Mech. Eng., Part A: J. Power Energy,2007

4. The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading Part I: University Research and Methods Development;ASME J. Turbomach.,2002

5. Effect of Forward Sweep in a Transonic Compressor Rotor;Proc. Inst. Mech. Eng.: J. Power Energy,2003

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