Inlet Flow Distortion Effects in Aircraft Gas Turbine Engine Compression Systems

Sivapragasam, M and Ramamurthy, S (2009) Inlet Flow Distortion Effects in Aircraft Gas Turbine Engine Compression Systems. Technical Report. NAL, NAL Bangalore.

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Abstract

The performance of an aircraft gas turbine engine is adversely affected by the non-uniform or distorted flow in the inlet duct.Inlet flow distortion lowers the surge margin of the engine's compression system with surge occurring at much lower pressure ratios at all speeds.In this document, the effects of inlet distortion on the performance and stability of aircraft gas turbine engine compression systems are reviewed .A brief discussion on the aerodynamic instabilities in axial compressors pertaining to inlet distortion is presented.The significant previous research work addressing the inlet distortion problem are highlighted.The document concludes with an overview of current promising research trends in compressor aerodynamics in inlet distorted conditions.

Item Type: Proj.Doc/Technical Report (Technical Report)
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aircraft Propulsion and Power
Division/Department: Other, Propulsion Division
Depositing User: Dr S Ramamurthy
Date Deposited: 25 Aug 2010 11:03
Last Modified: 25 Aug 2010 11:03
URI: http://nal-ir.nal.res.in/id/eprint/9025

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