Cold flow analysis of an aero-engine gas turbine combustor configuration 13; 13;

Muralidhara, HS and Shembharkar, TR and Pai, BR and Ramanujam, PS and Jayaprakash, GN and Pandey, PK (2001) Cold flow analysis of an aero-engine gas turbine combustor configuration 13; 13;. In: International Symposium on Air Breathing Engines, 3-7 Sept 2001, Bangalore, India.

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The present work is related to the computation of cold flow in a typical air-engine gas turbine annular combustor and validation of the predictions with the experimental results. The primary motivation of the study was to simulate the complex 3D turbulent flow in the complete combustor system, starting from the compressor exit to the turbine inlet, in a coupled manner. A general-purpose CFD code, PHOENICS, was employed for this purpose. A structured BFC grid was generated for the combustor configuration. Three-dimensional Reynolds averaged Navier-Stokes equations were solved with the standard k-epsilon turbulence model. Computations were carried out for three flow conditions for the combustor, and the predictions were compared with experimental results like mass flow distribution and total pressure loss. Around 2.5 percent deviation from experimental values was observed for mass flow splits along outer annulus, core, and inner annulus. Deviation in total pressure loss was found to be less than 1 per cent.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Mathematical models;Computational fluid dynamics;Mass flow;Gas turbine engines;Computation;Cold flow;Joining; Compressors;Turbulent flow;Inlets;Stress concentration; Aerospace engines;Turbulence;Turbines;Engines;Standards; Cold flow tests;Aircraft engines;Gas turbine engines
Subjects: ENGINEERING > Fluid Mechanics and Thermodynamics
AERONAUTICS > Aircraft Design, Testing & Performance
Depositing User: M/S ICAST NAL
Date Deposited: 06 Sep 2006
Last Modified: 24 May 2010 04:20

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