Авіаційно-космічна техніка та технологія (Aug 2017)
TO THE OPTIMUM DESIGN OF THE AXIAL MULTI-STAGE COMPRESSOR
Abstract
The work is devoted to the development of an integrated approach to the aerodynamic improvement of the blade vanes of multistage axial compressors of gas turbine engines. One of the features of the studies carried out to optimize the blade vanes was to take into account the mixing effects by various sources of losses. Thus, minimization of losses sources in compressor blade vanes during their profiling is achieved due to the account of the complex three-dimensional vortex nature of the flow and the use of modern software systems for solving the Navier-Stokes equations. Calculations of the three-dimensional viscous flow in the work are performed with ANSYS software. The profiling of the multi-stage compressor blades is carried out with “Kompress 2.0” software package, the feature of which is the use of parametric models of rotor and stator blade vanes, adapted for their aerodynamic optimization, as well as taking into account the radial unevenness of the incident flow when selecting the tangential blades shape of the stator vanes. As a result, a complex methodology for the optimal design of the blades of a multi-stage compressor with the use of "controlled" diffusivity, S-shaped profiles, lean, and chord variation is developed, with simultaneous variation of geometric parameters according to special plans and the use of the compressor efficiency as an integral efficiency criterion, “Kompress 2.0” for the blades profiling, ANSYS for the calculation of threedimensional viscous flow. Multi-stage axial compressors have been designed, numerically and experimentally investigated. Based on the results of experimental studies of multistage axial compressors, new generalizing relationships are established, that establish a relationship between the geometric parameters of the profiles and their gas dynamic characteristics to take into account the features of the spatial shape of the flow at the stage when solving the inverse design problem. The results of the research were used in the design and improvement of the elements of the flow paths of the ZM multistage compressors. Test aerodynamic optimization of the blade systems of experimentally studied multistage compressors with the use of the proposed approaches made it possible to obtain the efficiency of high-pressure compressor stages at the level of 0.92 ... 0.93 and to increase the efficiency of multistage axial compressors by 1.0-2.4%. The efficiency of the 10-stage compressor is 0.8% (to the level of 0.853), the efficiency of the 6-stage compressor is 1.1% (to the level of 0.825), the efficiency of the 3-stage compressor is 2.4% (to the level of 0.885), and the efficiency of an 8-stage axial compressor is 1.6% (to the level of 0.879).
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