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International Conference on Computer Simulation in Physics and Beyond IOP Publishing IOP Conf. Series: Journal of Physics: Conf. Series 1163 (2019) 012022 doi:10.1088/1742-6596/1163/1/012022 2. Method of optimization In order to solve these tasks, a method of turbine geometrical characteristics correction is offered. The method makes possible to lower the stress that occurs in high loaded parts of impellers while preserving gasdynamic characteristics of prototype turbine flow range. Gas turbine engine turbine impeller optimization was conducted in several stages: cross-section estimation and prototype blade modification with profile input and output angle preservation; turbine impeller model creation according to the geometry of prototype flow range; turbine impeller strength calculation and comparison with prototype parameters; turbine impeller modification with consideration of greater demands in high-loaded parts; turbine gasdynamic calculation and comparison with prototype parameters. 3. Strength enhancement of turbine impeller As prototype turbine impeller a typical turbine impeller with cooled blades was taken. Using Ansys CFX [5], the stress loads for 96000 rpm frequency speed and 700°C of the prototype turbine impeller were acquired. Prototype turbine impeller FEM strength calculation data is displayed in figure 1. Maximum loads appear at blade and disc connection areas (980 MPa) and on impeller hub (878 MPa). The ultimate stress of the material used ChS88U-VI (ЧС88У-ВИ) at working temperature is equal to 960 MPa. Minimal safety factor is equal to 0.98 while allowed safety factor for continuous work is equal to 1.25 [6]. Prototype turbine impeller does not meet the strength requirement for micro-turbine rotor with nominal frequency speed. Figure1. Stress distribution in the prototype of turbine wheel High-stress loads in impeller hub are caused by substantial peripheral blade thickness, therefore, higher values of rotating mass and corresponding stress loads are present. High values of stress loads in blade and disc connection areas are caused by blade flexural strain that comes out of centrifugal forces. On impeller periphery, blades have a slope to the direction of rotation causing high-stress loads and deformation in disc and blade connection areas at high frequency speeds. On the first stage, to lower the centrifugal forces influence, the prototype turbine impeller blade profile is estimated with blade cross-section (perpendicular to rotation axis) analysis. The main task of the analysis is to define αav — an average angle of blades cross-section center-line deviation from a radial direction. Next, basic 2PDF Image | Development of radial turbines in low power Gas turbine engines
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