Research On Turbine Performance Prediction Method Based On Loss Model

In this thesis, traditional prediction method and loss models are combined to prediction the performance of a self-developed turbine and E3 high pressure turbine. At the same time verified the accuracy of the prediction method used in this article by contrast the calculated results with experimental data and the results of numerical simulation.In terms of non-cooling turbine, this paper expounds 7 kinds of turbo-loss models widely used by foreing scholars in the past six decades and developed a set of calculation software by C++. This paper researched the prediction accuracy of loss models in by changing the turbine inlet conditions. The analysis shows that: the Ainley&Mathieson model, Stewart model and the theo-exp model get the closest output power data with the experimental data, the relative errors with the experimental results based on the three loss models are 3.88% ~ 1.99%, 3.74% ~ 2.41% and 0.14% ~ 3.29%, those loss models can obtain enough precision. The relative errors based on Balje&Binsley model and Traupel model obtained is close to 10.0%, and those models are not fit to the turbine researched in this article. The aerodynamic parameters distribution along the blade height are also caculated after predicting the turbine output power, and the results agree well with the CFD results. Therefore, the results of this prediction method can be used as a reference for turbine blade preliminary design.In terms of cooling turbine, this paper study the mixing loss in the turbine guide vane by velocity coefficient increment method, this method is advanced by the former Soviet Union scholars, we can get the following conclusion by compared the calculated results and the CFD results: the results based on the velocity coefficient increment method and the CFD results are in good agreement. With the jet cooling flow rate in guide vane increased from 2.50% to 6.25%, the relative error varying from-2.41% to-3.24%, the results can reflect the regularity of turbine performance with changing cooling air flow rate to some extent. Above, it can be applied to some engineering projects.