Performance Enhancement of a Transonic Axial Flow Compressor with Circumferential Casing Grooves to Improve the Stall Margin

Abstract

The stability range of the gas turbine engine compressors is being challenged in the modern days due to the intention of increasing per stage maximum loading. Casing treatment has been widely adopted as a realistic passive flow control means to improve the stall margin with a slight decrease of efficiency at the same time by various grooves of which shape (location, angles and so on) has a significant influence on controlling effect. However, the influence of some details in grooves is ignored in most of the case that may impact the specific flow field in the groove. A research on the impact of chamfer and fillet corners on the performance of casing treatment was proceeded by numerical simulation in this paper. The performance of different models of grooves on NASA Rotor 37 was investigated by discretizing 3D RANS based on finite volume method. Firstly, steady simulations were performed on NASA rotor 37 for validation. The CFD results and experimental data for adiabatic efficiency and pressure ratio were in good agreement. According to convergence criteria, the initiation of the stall was predicted. Few numbers of circumferential grooves casing treatment (CGCT) models have been proposed and tested numerically. Rectangular CGCT shape and smooth wall casing performances were analyzed. Moreover, the highest adiabatic efficiencies and stall margins of smooth wall casing, rectangular grooves and rectangular grooves with chamfer and fillet corners shapes models were compared to evaluate the influence of the shape of grooves on the stability and performance on axial flow compressor. The rectangular circumferential casing grooves and rectangular grooves with chamfer and fillet corners enhanced significantly stall margin and an operational range of the transonic axial flow compressor but adiabatic efficiency was slightly decreased.

The Influence of Different Blade Outlet Angle and Wedge Groove on the Performance of the Double Suction Pump

“…The wear of the impeller ring mainly includes impact wear and combined wear of cavitation and sediment [12,13]. The wedge grooves can increase the flow velocity near the impeller ring [14] and have a carrying effect on the fluid to sediment. Therefore, a circle of wedge grooves is set on the outside of the cover plate of the impeller to reduce the sediment concentration near the ring, as is shown in Fig.…”

Analysis and Optimization of the Performances of the Tandem Blade Radial Compressor Using the CFD

“…They stated that they reduced the deviation angle by using a diffuser with splitter blades for the high-pressure radial compressor and thus increased its performance [28]. Various numerical analysis studies have been carried out to improve the stall margin of the axial compressor [29][30][31].…”

Influence of Blade Lean on Performance and Shock Wave/Tip Leakage Flow Interaction in a Transonic Compressor Rotor

“…The unsteady results indicated that the shock/tip leakage vortex interaction generated the tip leakage vortex breakdown and caused a U-type vortex, whose periodic migration along blade pressure surface led to blade loading variation and flow unsteadiness near blade tip region; the shock oscillation was observed as indication of flow unsteadiness. Ahmad et al (2020) numerically investigated the shock/tip leakage vortex interaction and the performance enhancement based on NASA Rotor 37. Result showed that shock/tip leakage vortex interaction generated a stagnation zone near blade tip region, which caused flow instability and triggered the stall.…”