Numerical Analysis Of Internal Flow Field And Tip Clearance Leakage In Axial Compressor Rotor

The integral equations governing the three-dimensional viscous flow inside the turbo-machinery in the rotating coordinate system are presented in this paper, the viscous effects are simulated by the distributed body force described by Professor Denton J.D. The time-marching method and explicit finite volume difference scheme are employed to solve the flow inside the turbo-machinery. In order to accelerate the convergence, residual smoothing and local time stepping were employed. In the same time, By improving Prolongation Operator, a new multi-grid scheme which can combine well with the algorithm of this thesis. The calculation of the37# transonic compressor rotor shows that the simulation results of the author's multi-grid scheme fit fairly well with those of Professor Denton J.D.'s, however, the author's converging speed is faster.On the basis of above work, by using of "thin blade approximation", a 3D viscous code had been developed to calculate flow field in rotor with tip clearance. The flow field in the rotor tip of a compressor was numerical analyzed using the calculation method, the result compare well with experimental data. The influence of tip clearance on overall performance and detailed flow structure in tip region of an axial compressor rotor was investigated. It was found that the introduce of tip clearance deteriorate the overall performance of the compressor rotor. At the same time, tip leakage induced by pressure gradient and relative motion between the blade tip and the shroud wall is found to have a major influence on detailed flow properties in tip region of rotor passage.