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Structure for inhibiting horseshoe vortex at front edge of turbine blade of gas turbine

A technology for turbine blades and gas turbines, which is applied in the direction of blade support components, mechanical equipment, engine components, etc., can solve the problems of complex flow at the end of the turbine and increased secondary flow loss in the end area, and achieve weakening development and reduction Secondary flow loss, the effect of the obvious effect

Pending Publication Date: 2022-01-21
XIAN THERMAL POWER RES INST CO LTD
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to achieve the design goal of improving the aerodynamic performance of gas turbines, current gas turbines generally adopt the design method of increasing the blade load. The transverse flow in the turbine region is strengthened, the flow at the end of the turbine is more complicated, and the secondary flow loss in the end region is further increased

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  • Structure for inhibiting horseshoe vortex at front edge of turbine blade of gas turbine
  • Structure for inhibiting horseshoe vortex at front edge of turbine blade of gas turbine
  • Structure for inhibiting horseshoe vortex at front edge of turbine blade of gas turbine

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Embodiment Construction

[0019] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0020] like Figure 1 to Figure 3 As shown, the present invention provides a structure for suppressing the horseshoe vortex at the leading edge of the turbin...

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Abstract

The invention discloses a structure for inhibiting a horseshoe vortex at the front edge of a turbine blade of a gas turbine. The structure comprises a plurality of micro-scale groove structures arranged on the upstream end wall of the front edge of the turbine blade, and the micro-scale groove structures are the same in shape, axial position and adjacent distance. On the basis of the mechanism that the groove structures reduce flow resistance and absorb nearby wall surface flow, the overall performance of the turbine is improved by inhibiting front edge flow separation, reducing the strength of the horseshoe vortex in a channel and reducing secondary flow loss.

Description

technical field [0001] The invention relates to the field of gas turbine axial flow turbines, in particular to a structure for suppressing the horseshoe vortex at the leading edge of the turbine blade of the gas turbine. Background technique [0002] A turbine is a device that converts the thermal energy of high-temperature gas into mechanical energy and outputs mechanical work through rotation. It is one of the key components of a gas turbine. Due to the circumferential, radial and axial pressure gradients at the end of the turbine cascade, a secondary flow that is inconsistent with the main flow direction will be generated. The existence of the secondary flow causes a large secondary flow loss near the end wall, accounting for 30% to 50% of the total loss of the turbine channel. In order to achieve the design goal of improving the aerodynamic performance of gas turbines, current gas turbines generally adopt the design method of increasing the blade load. The transverse f...

Claims

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Application Information

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IPC IPC(8): F01D5/14
CPCF01D5/141F01D5/147
Inventor 肖俊峰段静瑶于飞龙刘战胜李园园高松上官博
Owner XIAN THERMAL POWER RES INST CO LTD