Numerical Analysis of the Tip Leakage Flow Field in a Transonic Axial Compressor with Circumferential Casing Treatment

被引：22

作者：

Legras, G. ^{[1
]}

Gourdain, N. ^{[2
]}

Trebinjac, I. ^{[1
]}

机构：

[1] Univ Lyon 1, INSA, Ecole Cent Lyon, CNRS,LMFA UMR 5509, F-69134 Ecully, France

[2] CERFACS, Computat Fluid Dynam Team, F-31057 Toulouse, France

来源：

JOURNAL OF THERMAL SCIENCE | 2010年 / 19卷 / 03期

关键词：

transonic axial compressor; casing treatment; circumferential groove; tip leakage vortex;

D O I：

10.1007/s11630-010-0198-y

中图分类号：

O414.1 [热力学];

学科分类号：

摘要：

This paper reports on numerical investigations aimed at understanding the influence of circumferential casing grooves on the tip leakage flow and its resulting vortical structures. The results and conclusions are based on steady state 3D numerical simulations of the well-known transonic axial compressor NASA Rotor 37 near stall operating conditions. The calculations carried out on the casing treatment configuration reveal an important modification of the vortex topology at the rotor tip clearance. Circumferential grooves limit the expansion of the tip leakage vortex in the direction perpendicular to the blade chord, but generate a set of secondary tip leakage vortices due to the interaction with the leakage mass flow. Finally, a deeper investigation of the tip leakage flow is proposed.

引用

页码：198 / 205

页数：8