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Design Of Cooling Configuration For Military Aeroengine V-Gutter
[Full Text]
AUTHOR(S)
Batchu Suresh, S. Kishore Kumar
KEYWORDS
Adiabatic film cooling, Thermal barrier coating, Overall film cooing effectiveness, Thermal design of cooling configuration, CHT analysis.
ABSTRACT
Military aircraft engines employ afterburner system for increasing the thrust required during combat and take-off flight conditions. V-gutter is employed for stabilisation of the flame during reheat. For fifth generation aero engine the gas temperature at the start of the afterburner is be-yond the allowable material limits of the V-gutter so it is required to cool the V-gutter to obtain acceptable creep life. The design of cooling configuration for the given source pressure is worked out for different rib configurations to obtain the allowable metal temperature with minimum coolant mass flow.1D network analysis is used to estimate the cooling mass flow and metal temperature for design flight condition. CFD analysis is carried out for four cooling configurations with different rib orientations. Out of four configurations one configuration is selected for the best cooling configuration.
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