Research On Numerical Calculation And Analysis Of HPT Tip Clearance

Tip clearance has much effect on the properties of aero-engine. As the reference of the project design, the numerical computation of tip clearance can improve the aero-engine performance, reliability and to reduce the specific fuel consumption (SFC).In this paper, the status quo of the tip clearance of aero-engine is surveyed, the theory and the method of the numerical computation of tip clearance are introduced, the simple tip clearance calculation program is modified and refined and the computation method of the turbine temperature field is improved. At last, software is developed. The software is easy to operate by the interface dialogs of variable display and modification, program control and the outcome display.The parametric method is used in the process of turbine parts modeling and tip clearance analysis. Due to the complexity of the turbine parts, some characters are predigested. A simplify high pressure turbine (HPT) tip clearance model is analyzed with the cyclic symmetry method.Research on the flow, heat and structure integration analyses is achieved in this paper. Flow/heat analysis is done by FLUENT software, and heat/structure analysis is done by ANSYS software. An interpolation program is used to convert the FLUENT result data to the ANSYS load data. It is a new method to analyze turbine tip clearance.In this paper, some research of the numerical computation of the tip clearance of aero-engine is done, the parametric method is used and the research on the flow, heat and structure integration analyses is accomplished. Research finding about the tip clearance of engine in the paper is basal; they can be used as reference of aero-engine design and the tip clearance control.