Flow blockage in a transonic axial flow compressor: simulation analysis under distorted conditions

Abstract

Today the aircraft industry is looking for faster and safer engines for both civil and military applications. The performance of all different types of air breathing engines depends on the amount of mass flow rate of air entering and hot gas ejecting out from the engine. Thrust is the key role for any engine performance. To achieve more thrust all the turbo machinery components like axial fan, axial flow compressor and axial flow turbine should function effectively. This paper is primarily dealing about one of the turbo machinery component, axial flow compressor performance where the study is more focused on flow blockage formation under distorted phenomena. The complete blade boundary layer formation and related flow numerical theory are discussed in detail, accordingly the boundary conditions were set to have better numerical simulations using ANSYS tool. To find the flow blockage formation suitable turbulence model was coded using the well know compressible equations. The flow blockage between the rotor and stator of the compressor stage was calculated and also validated with that of experimental data effectively. The flow simulation results also revealed that the performance parameters under the modern engine transonic speed from Mach 0.8 to 1.2 under the distorted conditions are better for aeromechanical features.

In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines

“…Li et al developed an experimental setup in order to estimate the modern turbofan supersonic engine inlet during takeoff and landing conditions. The experiment was suitable for these two conditions, therefore one can go for further research in other phases of flight envelop [42], [57], [58].…”

Performance Evaluation of Transonic Axial Flow Compressor under Distorted Conditions by Groove Casing Technique with Tip Injection and Surface Roughness Effects

“…All modern transonic aircraft engines are using high loaded axial flow compressors, but they are not able to give maximum performance and high-pressure ratio because of its airflow blockage between the stage blades. The flow blockage is mainly caused due to distorted effect, and flow blockage calculations are studied [1]. Compressor operating at higher Mach speed (i.e., transonic speed 0.8 to 1.3) causes high aerodynamic loading; therefore, maintaining high efficiency within the safe margin is quite a difficult task [2].…”