Turbine Blade Construction Method And Optimization Analysis Of Blade Cooling Holes

With the canstant improvement of the turbine entrance temperature、pressure ratio、interstage enthalpy drop and load of the blade, now the content of the main research method of gas turbine design process was to optimize the jet of the cool air and improve the cooling system so that achieve the aim to increase the aerodynamic efficiency and decrease the temperature of blade surface.To ameliorate the design method of the turbine blade and increase the efficiency of blade design using the computer simulation technology,we should develope a simple and efficient design platform applying for constructure and heat transfer design of turbine passage and blade.This papaer carry out the research from below.(1) Study the Three-dimensional Non-Uniform Rational B-Spline(called NURBS) parameter turbine blade and passage construction method.Program the general blade surface construction code on Matlab. The turbine blade and passage constructure expressed by NURBS surface was more simple and direct.(2) Study the modification method of NURBS surface.Achieve the aim to enlarge and shrink any parts of the blade surface.Besides,the modification size and degree could be controled.(3) Using the program programed on MATLAB to construct the complex surface of blade including these special structure: local expanding contraction blade surface and end wall, non-axisymmetric endwall profiling, inflection diffusion area of suction surface and some specail structure that can improve the cascade flow.(4) Using MATLAB to model the structure of blade and runner passage. Developing their grid.Using CFX software to conduct the final treatment and analysing the typical schemes of NURBS surface for their flow distribution so that to master the CFX turbine blade design method and process.(5) Program the code on MATLAB that can control a line by five control points using NURBS technology.Chage the chordwise location of cooling holes near the stator stagnation line. Summarizing a cooling hole optimization method related with the Orthogonal implementation.Then oberve the temperature distribution on blade surface and analyse the influence of the position changes of the cooling holes to summarize the feature of the fine project.Making the effiency of aero-thermal coupling maximize.(6) Design and study the HTC turbine blade cooling structure(7 stages).The key of the design is the construction of the first-age including: designing the three-dimensional aero-thermal coupling of cool air at end wall, achieving the aim as attachment cooling which between the blade and wall using end wall cool air.