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THE INNER WORKINGS OF AXIAL CASING GROOVES IN A ONE AND A HALF STAGE AXIAL COMPRESSOR WITH A LARGE ROTOR TIP GAP: CHANGES IN STALL MARGIN AND EFFICIENCY

[+] Author and Article Information
Chunill Hah

NASA Glenn Research Center, MS 5-10, Cleveland, Ohio
chunill.hah-1@nasa.gov

1Corresponding author.

ASME doi:10.1115/1.4041133 History: Received July 10, 2018; Revised August 06, 2018

Abstract

Effects of axial casing grooves (ACGs) on the stall margin and efficiency of a one and a half stage low-speed axial compressor with a large rotor tip gap are investigated in detail. The primary focus of the current paper is to identify the flow mechanisms behind the changes in stall margin and on the efficiency of the compressor stage with a large rotor tip gap. Semicircular axial grooves installed in the rotor's leading edge area are investigated. A large eddy simulation (LES) is applied to calculate the unsteady flow field in a compressor stage with ACGs. The calculated flow fields are first validated with previously reported flow visualizations and stereo PIV (SPIV) measurements. An in-depth examination of the calculated flow field indicates that the primary mechanism of the ACG is the prevention of full tip leakage vortex (TLV) formation when the rotor blade passes under the axial grooves periodically.

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