Thrust augmentation of military aircraft engine is carried out during critical phases of flight with the help of an afterburner. In advanced aeroengines, afterburner entry temperatures are beyond material allowable temperature limits. Thus, it is vital to cool V-gutter even when afterburner is not in operation, to lower its metal temperatures and to achieve increased creep life. Present study is preliminary design of three cooling configurations for a given V-gutter geometry at design condition of operation of afterburner. 1D code is developed to arrive at geometry of each configuration after a parametric analysis. Effect of thermal barrier coating on the V-gutter metal temperature is studied. 3D conjugate heat transfer analysis (CHT) is carried out using FloEFD commercial software to study the local coolant flow field and its effect on metal temperatures.
Thermal Design of Cooling Configurations for an Afterburner V-Gutter of Advanced Aeroengine
Lect.Notes Mechanical Engineering
2022-07-24
17 pages
Article/Chapter (Book)
Electronic Resource
English
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