Transient Thermal Analysis of Aero Engine Static Structures

International Journal of Mechanical Engineering
© 2018 by SSRG - IJME Journal
Volume 5 Issue 10
Year of Publication : 2018
Authors : Dileep T, Dr. Manjunath H
How to Cite?

Dileep T, Dr. Manjunath H, "Transient Thermal Analysis of Aero Engine Static Structures," SSRG International Journal of Mechanical Engineering, vol. 5,  no. 10, pp. 14-21, 2018. Crossref,


Advanced gas turbines used for present day military aircrafts require higher thrust and lower specific fuel consumption. The thrust of the gas turbine engine can be increased by increasing the turbine entry gas temperature. The specific fuel consumption can be reduced by increasing the component efficiency. Compressor and turbine are the major components of the gas turbine engine. The relative movements that exist between rotor and stator components are responsible for varying tip clearance. The temperature prediction of the static structure and rotating parts is a vital input for estimation of clearances. This contradicting requirement of the tip clearance makes it important for estimation of static structure temperature. Hence this article deals with estimation of steady state and transient thermal responses of complete static structures such as fan casing, compressor casing, combustor casing and turbine casing. The casing temperatures are measured during engine test with help of thermocouples. Validation of temperature prediction for combustor casing has been carried out at steady state and transient cycle at three locations. There is good agreement between the measurements and predictions for both steady state and transient condition. Study of thermal response during steady state and transient analysis has done and observed that thermal response at rotor section is more compared to stator section and also difference between steady state temperature and transient temperature is less at rotor section. Parametric analysis carried out to study the effects of casing temperatures by varying heat transfer co-efficient on gas side and coolant side and temperatures on gas side and coolant side and the study shows that gas temperature is affecting more compared to other parameters.


Tip clearance, thermal response, steady state, transient


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