To explain the effect of tip leakage flow on performance an axial-flow transonic compressor, compressors with different rotor clearances were studied numerically. The results show that as clearance increases, intensity is increased, shock wave position moved backward, and interaction between vortex intensified, while boundary layer weakened. Most all, stall mechanisms varying are different. mai...

The flow in a linear compressor cascade with tip gap is simulated using wall-resolved compressible Large-Eddy Simulation. based on the Virginia Tech Low Speed Cascade Wind Tunnel. Reynolds number chord 3.88 x 10? and Mach 0.07. considered this study 4.0 mm (2.9% of axial chord). An aerodynamic analysis tip-leakage allow us identifying main mechanisms responsible for development convection vorte...

In this paper non-synchronous vibration (NSV) of a GE axial compressor is simulated using a fully coupled fluid/strcuture interaction (FSI). Time accurate NavierStokes equations are solved with a system of 5 decoupled structure modal equations in a fully coupled manner. A 3rd order WENO scheme for the inviscid flux and a 2nd order central differencing for the viscous terms are used to resolve n...

A low-speed counter-rotating axial flow compressor (CRAC) with single circumferential grooved casing treatment (CT) was investigated numerically. Both steady and time-accurate numerical calculations were performed to study the effects of the single grooved CTs over the rear rotor on the stability enhancement and the unsteadiness of tip leakage flow (TLF) in the CRAC. Parametric studies indicate...

A four-blade-passage numerical model was developed for a two-stage axial-flow compressor with an inlet guide vane (IGV) the purpose of studying steady and dynamic characteristics approaching its stability limit. The flow-field information indicated that tip-leakage flow decreased more rapidly from blade’s leading edge to trailing edge, decreasing rate. leakage verified be driven via blade load ...