Aerodynamic Design On Microturbine System And The Impats Of Variable Tip Clearance

It is of great significance for the design and development of the next generation of micro gas turbine to deeply understand and understand the aerodynamic performance and internal flow characteristics of micro gas turbine. Parking preheating microturbine systems is an important function of the conversion component of a distributed energy system. It can be at a high temperature, high speed, very high leaflets poor working environment and efficient work under minimal flow, efficient use of thermal power generation bear the task. In order to design advanced aerodynamic performance matching miniature radial centrifugal compressor and micro-turbines, this paper carried out research on the following aspects of geometry:The one-dimensional and CFturbo 3D shape of geometry modeling software design the tip clearance of the micro centrifugal compressor and micro radial inflow turbine cascade, micro centrifugal compressor and micro radial inflow turbine flow field are calculated numerically by using the ANSYS CFX software, evaluated the cascade flow field aerodynamic performance, determined without considering the tip clearances to match the performance of the micro centrifugal compressor and micro radial inflow turbine designFor the safety assessment of the preliminary standard micro centrifugal compressor and micro radial inflow turbine design strength and material, to gas aerodynamic performance based by ANSYS Workbench software platform of advanced solid strength calculation software of the static structural, respectively to carry out the steady state conditions under centrifugal compressor and centripetal turbine blades of maximum deformation and maximum equivalent stress calculations to evaluate the meet the gas dynamic strength properties of the design requirements of the blade, with allowable stress. It is proved that the safety of the shape design of scheme.Based on the aerodynamic performance of the non gap micro gas turbine, the influence of leakage flow on the aerodynamic performance of the centrifugal compressor and the radial turbine cascade was studied. The nonlinear effect of tip clearance leakage flow on the flow field of micro centrifugal compressor is pointed out, and the flow field of the centrifugal compressor is of Shuangfeng value with the increase of the input power and efficiency. The law of tip clearance leakage flow on micro radial turbine flow field effect is with the increase of the tip clearance, turbine mass flow, input power and efficiency monotonously decreasing trend% leaf top clearance centrifugal compressor scheme as the compliance of the centrifugal compressor design case, in order to match the performance of the compressor and need to further improve 2% blade tip clearance of the r adial inflow turbine aerodynamic performance.This paper by adjusting centripetal turbine static vane inlet flow angle, control of static blade exit flow velocity and flow angle, from 3D CFD flow angle to find the best move leaves the inlet parameters, and improve the power of the turbine to 569.5W. Therefore all parking preheats aerodynamic performance parameters of the micro gas turbine system is designed to meet the design requirements.