Modified reduced model for rapid analysis of tip clearance of high pressure turbine

Considering the effects of temperature, rotating speed and pressure difference in engine operating conditions for predicting changes in turbine tip clearance, a modified reduced model was presented. In the process of designing structures for high pressure turbine in an aircraft engine, tip clearance was predicted using this modified model, and results show that the modified model can predict tip clearance changes into engine operating conditions more accurately. By simply inputting geometric, heat transfer, material and population parameters in this model, the variation of tip clearances can be obtaine quickly, and the conditions when the maximum and minimum tip clearance happened can be determined. Therefore, this method can be a way to evaluate tip clearance efficiently during the preliminary design of an aircraft engine.