Flow Blockage in a Transonic Axial Flow Compressor: Simulation Analysis under Distorted Conditions

Srinivas, G and Raghunandana, K and Shenoy, Satish B (2017) Flow Blockage in a Transonic Axial Flow Compressor: Simulation Analysis under Distorted Conditions. In: CISCON 2013, 03/11/2017, MIT, Manipal.

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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 turbomachinery components like axial fan, axial flow compressor and axial flow turbine should function effectively. This paper is primarily dealing about one of the turbomachinery 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.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Compressor, blockage, distortion, simulation, analysis.
Subjects: Engineering > MIT Manipal > Aeronautical and Automobile
Engineering > MIT Manipal > Mechatronics
Depositing User: MIT Library
Date Deposited: 09 Dec 2017 10:14
Last Modified: 11 Dec 2017 10:06
URI: http://eprints.manipal.edu/id/eprint/150194

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