Integrated Blade-endwall Optimization Design Of Axial Flow Compressor

Compressor cascade of three-dimensional flow, the angular separation zonevanes and secondary flow affects not only the loss of the cascade flow separation,the scope of work also affects the stability of the compressor. Many studies haveshown that the application of non-axisymmetric end wall modeling techniques forboundary layer flow has a significant role in controlling the impact of the lossdistribution within the cascade and cascade efficiency.Parallel to the development ofcomputer technology, axial compressor design also played a considerable role.Consequent requirement for compressor is getting high on the designer made morestringent design basics. In this paper, a low Mach number axial compressor inlet tothe static gate leaf to optimize the design of three-dimensional optimization baseddesign platform NUMECA Design3D, in order to optimize the neural grid combinedwith artificial neural grid, respectively, non-axisymmetric end wall shape andoptimize the design of different ways and non-axisymmetric curved end wall stylingcombine to explore non-axisymmetric end wall shape affect the structure of thevortex flow field, are introduced in a non-axisymmetric curved blade end wallmodeling to explore the lower total pressure loss principle. In this paper, thefollowing aspects:Firstly, the selected axial compressor with high load static angle of60degreesoff the gate leaf three-dimensional numerical simulation and comparison withexperimental data prove FINE/TURBO business computing software can predictthe cascade flow field to verify the reliability of the calculations.Secondly, the paper carried a compressor stator leaf gate parametric modeling,the end wall of the airfoil shape parameterization methods described herein,methods and applications, in21different leaf height of the suction and pressuresurfaces intended to be parameterized type line together, the21cross-section of theleaf by leaf type to generate a three-dimensional stacking line. Guarantee a smoothbend in the blade, continuous excessive. The end walls arranged in the shape of theflow along the radial perturbations point to generate surface modeling. By providinggood design variables to optimize the design parameters of the blades and end wallscan be fitted later.Finally, the optimization results for each non-axisymmetric shape of the end wallof the bend in different ways and with non-axisymmetric shape of the end wall ofthe combination of the analysis. Found in large turning angle cascadenon-axisymmetric end walls and non-axisymmetric modeling technology combined with the end wall curved blade separation structure modeling technology changecascades, reducing the boundary layer separation, and separation of the flow field inthe form of separated by a closed turn open separation. Under non-axisymmetricshape its end wall outlet section to reduce the total pressure loss of10.9%,combined with curved blades under non-axisymmetric end wall shape its peak totalpressure loss reduced by17%and total pressure loss reduced by13.5%exitsection.