Active regulation and control device for internal flow separation of high-load low-pressure turbine

Abstract

The invention discloses an active regulation and control device for internal flow separation of a high-load low-pressure turbine. The active regulation and control device is used for comprehensively controlling blade suction surface separation and end area secondary flow. A self-excitation jet flow type pulse vibration exciter is installed on a turbine blade suction surface by arranging a suctionsurface separation control unit. Pulse jet flow can promote momentum exchange between low-energy fluid in a boundary layer of the suction surface and main flow, energy of the boundary layer of the suction surface is increased, gas flow separation of the turbine blade suction surface can be remarkably inhibited, and blade profile loss is reduced. By arranging an end wall boundary layer suction unit, the low-energy fluid near the end wall of the turbine is removed through the end wall boundary layer suction technology, and formation of end area secondary flow is restrained. Finally, gas pumped from the end area is supplied to the self-excitation jet flow type pulse vibration exciter, the aims of suction and jet flow balance are achieved, the comprehensive regulation and control effect of theend area secondary flow and the suction surface boundary layer of the high-load low-pressure turbine is achieved, and the overall aerodynamic performance of the high-load low-pressure turbine is improved to a greater extent.

Description

technical field [0001] The invention belongs to the field of internal flow control of aero-engines / gas turbines, and relates to a low-pressure turbine internal flow separation control device, in particular to an active flow control device for comprehensively regulating the secondary flow in the end zone of a high-load low-pressure turbine and the boundary layer of a suction surface. By installing the self-exciting jet pulse vibrator on the suction surface of the turbine blade, the pulse jet can promote the momentum exchange between the low-energy fluid in the boundary layer of the suction surface and the main flow, increase the energy of the boundary layer of the suction surface, and significantly suppress The air flow on the suction surface of the turbine blade is separated to reduce the loss of the blade shape; then the low-energy fluid near the end wall of the turbine is removed by using the end wall boundary layer suction technology, and the formation of the secondary flow ...

AI Technical Summary

Problems solved by technology

[0005] In view of the above-mentioned defects and deficiencies of the prior art, the present invention aims at the increase of the lateral pressure difference in the channel and the increase of the reverse pressure gradient in the flow direction caused by the high-load low-pressure turbine blade design of the existing large bypass ratio turbofan engine, which easily leads to boundary layer separation , exacerbating the problems of airfoil loss and secondary flow loss in the end zone, by fully absorbing the advantages of the two active flow control technologies of self-excitation feedback jet vibration and end wall boundary layer suction, and overcoming the corresponding technical shortcomings, the present invention By installing the self-excited feedback jet exciter on the suction surface of the turbine blade, the gas extracted by the boundary layer of the end wall is supplied to the self-excited feedback jet exciter to achieve the flow balance of suction and jet flow, without the need The input and output of the external flow, and realize the comprehensive control effect of the secondary flow in the end zone and the boundary layer of the suction surface, and greatly improve the overall aerodynamic performance of the high-load low-pressure turbine

Images