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|
Dileep T, Dr. Manjunath H, "Transient Thermal Analysis of Aero Engine Static Structures" SSRG International Journal of Mechanical Engineering 5.10 (2018): 14-21.
Dileep T, Dr. Manjunath H,(2018). Transient Thermal Analysis of Aero Engine Static Structures. SSRG International Journal of Mechanical Engineering 5(10), 14-21.
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.
 Harish Agarwal and Srikanth Akkaram, “ Reduced Order Clearance Models For Gas Turbine Applications” 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Material Conference 7-10 April 2008, Schaumburg, IL
 Alexander N. Arkhipov, Vladimir V. Karaban, Igor V. Putchkov “The Whole Engine Model For Clearance Evaluation” Proceedings of ASME Turbo Expo 2009.
 Power for Land, Sea and Air GT2009 June 8-12,2009, Orlando, Florida, USA
 P. Pilidis and N. R. L. Maccallum “The Effect of Heat Transfer on Gas Turbine Transients” International Gas Turbine Conference and Exhibit, Dusseldorf, West Germany – June 8-12,1986
 D. K. Hennecke and K. Trappmann “Turbine Tip Clearance Control in Gas Turbines” MTU Motoren and Turbinen – Union Munchen GmbH Postfach 500640 Munich, Germany
 B. Glezer “Turbine Blade Tip Clearance Improvement” International Gas Turbine and Aero engine Congress and Exposition, Orlando, FL June 3-6, 1991
 Scott B. Lattime and Bruce M. Steinetz “ Turbine Engine Clearance Control Systems: Current Practices and Future Decisions” 38th Joint Propulsion Conference and Exhibit cosponsored by AIAA,ASME,SAE, and ASEE Indianapolis, Indiana, July 7-10, 2002
 “General Requirements for Measurement of Engine and Component Transients” AGARD-AD.320
 P. Pilidis and N. R. L. Maccalum “A Study of The Prediction of Tip and Seal Clearances and their Effects in Gas Turbine Transients” The American Society of Mechanical Engineers St., New York, N.Y. 10017
 P F Neal “Mechanical and Thermal Effects on the Transient and Steady State Component Performance of Gas Turbines” Technical Design group, Rolls Royce Limited.
Tip clearance, thermal response, steady state, transient