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International Conference on Computer Simulation in Physics and Beyond IOP Conf. Series: Journal of Physics: Conf. Series 1163 (2019) 012022 IOP Publishing doi:10.1088/1742-6596/1163/1/012022 (a) (b) (c) (d) Figure 3. Blade modifications and stress distribution in the modifications of turbine impeller: variant 1 with a radius of the fillet increased to 5·10-3 m in joint of a blade and a wheel (a), variant 2 with a triangular support (b), enhancement of a blade back surface (c), variant 3 with a parabolic support (d). Variant of a wheel joint modification, which is based on parabolic support, satisfies strength requirements and doesn’t affect on a turbine flow section. 4. Evaluation of gasdynamic efficiency in turbine impeller On the last stage it’s necessary to evaluate an efficiency of a modified prototype impeller. To achieve that, using Ansys CFX (licence number 339001) research of gasdynamic parameters (gas flow rate, capability, efficiency) in a flow section considered in initial and modified impellers and comparison of obtained results are carried out. Computational domain (figure 4) involves: inlet section 1, nozzle assembly 2, turbine computational domain 3, outlet section (to the recuperator) 4, recuperator section 5, the arrows show circular interfaces. Each domain consists of segment, which is closed in circumferential direction. Turbine computational domain doesn’t consider radial split between a blade and a stator, configuration of a blade joint with a wheel and a split from the side of the wheel. The mathematical model for calculating the parameters of the stationary gas flow in the selected region is based on the following dependencies: (u u) p 2u 1 ( u) g 3 (1) (u) 0 (2) div(cpTu) div(gradT) f (3) p RT (4) This is the Navier–Stokes equations (1), the continuity equation (2), the energy equation (3) and equation of state (4). They contain the value of u is the vector velocity of the working medium, μ is dynamic viscosity, ρ – density, p – pressure, g is vector of gravitational acceleration, cp is heat capacity at constant pressure, T – temperature, λ – thermal conductivity coefficient, R is the gas constant, f is a term of heat source. The mathematical model is supplemented by the equations of SST turbulence model. Boundary conditions of this analysis are: inlet full pressure (inlet surface) is 350.8 kPa, full temperature is 1000K. On the outlet surface averaged static pressure is defined: 101.3 kPa. Computational turbine (domain 3) rotation speed is 96000 rpm. 4PDF Image | Development of radial turbines in low power Gas turbine engines
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