The Turbine Tip Clearance Numerical Analysis And Cold And Hot-size Conversion Method

In order of improving the performance and stabilization of aeroengine, it is needed to control the tip clearance of engine. Tip clearance numerical analysis is an important content of researching tip clearance control and improving performance of engine.In this paper, the simple method which is used in analyzing the tip clearance of turbine is refined, and the functions of the program are added, using the perfected program, analyzed the tip clearance of a certain high-pressure turbine. The result of the calculation for tip clearance is reasonable when it is compared with theory. Two ways are put forward for convention of dimension of the turbine components from high temperature to low one, which is related with tip clearance, a simple example is used to illuminate that the two ways are useful, using the method of design optimization, axiisk and a blade of a certain turhine is analysed, it showes that the method of design optimization is feasible to be used for convertion of dimension of the turbine components. finally, ANSYS software is used to analyzed the variation of tip clearance with the method of cyclic symmetry analysis when engine works under the conditions of temperature and rotational speed, AM using a new method to deal with thermal contact resistance in the calculation.Research findings about the tip clearance of engine in the paper are basal, they can be used as reference of control the tip clearance.