This paper describes the first part of the global work done by the authors aimed at finding the best settings for a numerical model for the calculations of axial uncooled turbines using RANS approach. The authors studied more than 80 papers published over the past 5 years in the examined field. Their analysis did not allow to identify unified recommendations for the creation of numerical models. The selection of model parameters is usually motivated by general considerations of numerical simulation, which follow from the method. In none of the papers the selection of parameters is correlated with the structure of the flow in the turbine. Many specific simulation issues were not covered at all. For the research, more than 1000 models of full-size axial turbines (including multistage turbines) and their elements were created. They differed in the number, size, parameters of the elements of finite volume meshes, in turbulence models, in the degree of simplification. The results were compared with the experimental data. As a result, the following was obtained: 1. A method for developing and optimizing the working process of turbines using numerical simulation based on the RANS approach is proposed. The search for the optimal turbine configuration is carried out using light computational models, which are based on the simplified channel geometry and the finite volume mesh. Their application makes it possible to reliably find the optimal turbine configuration 2.8 times faster. The characteristics of the selected variants are verified with the help of verification models that consider the real geometry of the channels and have a minimum error. 2. Recommendations are given on the selection of parameters for finite volume meshes and the selection of turbulence models for numerical models of the working process of axial turbines designed to perform optimization and verification calculations.
Abstract. The article presents optimization method for improving of the working process of axial compressors of gas turbine engines. Developed method allows to perform search for the best geometry of compressor blades automatically by using optimization software IOSO and CFD software NUMECA Fine/Turbo. The calculation of the compressor parameters was performed for work and stall point of its performance map on each optimization step. Study was carried out for seven-stage high-pressure compressor and three-stage low-pressure compressors. As a result of optimization, improvement of efficiency was achieved for all investigated compressors. IntroductionUsing CFD during the axial compressor design can reduce cash costs, but the search for the best version of the flow channel geometry takes a lot of time. The main reason is that the flow channel geometry of axial compressor stages is described by large number of variables. At least two sections, each of which is determined by dozens of independent variables, must be determined to describe the shape of one blade. Furthermore, it is necessary to describe the relative position of the sections relative to each other, shape of meridional section of the flow part, etc. As a result, the number of independent variables for a complete description of one stage reaches several tens which affect contradictory compressor characteristics. Man is not capable physiologically to analyse the problem of such dimension. The problem becomes proportionally larger if it is necessary to investigate the operation of multistage compressor.In this case, the optimization program can help the engineer. Their use allows the automatization of the search for the optimal combination of independent variables by their automatic variation and analysis of the results based on optimization algorithms.This article shows the technique for improving of the working process of axial compressor using optimization software IOSO and CFD software NUMECA Fine/Turbo and shows examples of the application of this technique on real seven-stage high-pressure compressor and three-stage lowpressure compressors of NK36-ST gas turbine engine (figure 1). The aim of optimization was to investigate which maximum efficiency is possible to obtain in each compressor [1]. The criteria and constraints for the optimization problems of each compressor have been selected on the basis of thermodynamic calculations of the engine NK36-ST [2].
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