Numerical Research On Aerodynamic Performance Of Highly-Loaded Turbine Blade Under Different Inlet Mach Numbers

Because of further to know and understand large-enthalpy drop blade in the flow characteristics and aerodynamic performance is significant for designing and developing the next generation gas turbine and advancer steam turbine, this paper investigates and analyzes the influence on the aerodynamic performance of the large-enthalpy drop blades as the Inlet Mach number is increasing.In order to investigate and analyze meticulously the influence on the aerodynamic performance of the large-enthalpy drop blades under different inlet Mach numbers, detailed experimental data large-enthalpy drop static blades and rotor blades are chosen as the models for the numerical simulation, and are simulated by CFD software ANSYS numerical calculation CFX in experimental conditions. By means of comparing the numerical calculation results and experimental results this paper tests the CFD software, it is found the test results show highly consistent.Through the CFX software , this paper makes respectively numerical simulations the large-enthalpy drop static blades and rotor blades, under the conditions of the 0°, 10°,-10°incidences for 0.1 to 0.8 Mach number eight inlet Mach numbers. In the end, The paper analyzes the numerical calculation results and the simulation results show that inlet Mach number influences on the aerodynamic performance of the large-enthalpy drop blade. This paper, from the position and size of the vortex area of annular-cascade, the shape of the pressure side leg and the suction side leg of the horseshoe vortex,the pressure isoline distribution of the blade surface, the distribution of pressure loss coefficients along the blade, the distribution of total pressure loss coefficients along the relative blade height and the flow loss axial distribution six aspects, analyze and research the increasing inlet Mach number on the aerodynamic performance influence of the large-enthalpy drop blade. On the pressure surface and suction surface,three dimensional flow area of the large-enthalpy drop static blades and rotor blades have certain extent decreases as the inlet Mach number is increasing, which restrains the annular-cascade secondary flow in a certain extent. The vortex area of the pressure face and the suction face and axial flow loss curve from 0.3 Mach number began to be weaken, then after 0.4 Mach number the trend is obvious. This fits the critical sound velocity area produced in the blade channels when the inlet Mach number is 0.3, and shows the shock wave structure in the blade channels can help wall three dimensional flow area improved. The different Mach numbers show a little influence on the end walls and the vortex core position of horseshoe vortex,but influence significantly on the meeting place of the pressure side leg and the suction side leg of horseshoe vortex and the position entranced into suction face. The increasing inlet mach number has no the visible influence on the pressure contour and pressure loss coefficients along the blade. With the same incidence, as Mach number is increasing the total pressure loss of large-enthalpy drop blades is decreased; At the same mach number, along with the incidence Angle increases total pressure loss coefficients rises.