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.