Performance Evaluation of Transonic Axial Flow Compressor under Distorted Conditions by Groove Casing Technique with Tip Injection and Surface Roughness Effects
نویسندگان
چکیده
Abstract The aerodynamic performance and pressure ratio of modern aircraft engine compressor are degrading due to unsteady flow distorted loads complex phenomena in the blade tip. This paper attempts improve axial transonic stage under conditions by incorporating combination groove casing, tip injection technique with surface roughness effects. is performed for Mach number ranging between 0.8 1.3. obtained numerical results compared experimental studies found be good agreement. Through analysis, interaction shock waves as well vortex formation boundary layer separation studied detail. While evaluating compressor, more emphasis given properties like pressure, density, temperature, velocity, etc. improvement observed at a particular specified property.
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ژورنال
عنوان ژورنال: Journal Of The Institution Of Engineers (india): Series C
سال: 2022
ISSN: ['2250-0553', '2250-0545']
DOI: https://doi.org/10.1007/s40032-022-00851-7