Transonic guide blade grid design method of high-pressure turbine

A cascade design and guide vane technology, which is applied to mechanical equipment, stators, engine components, etc., can solve the problems of inability to suppress shock wave loss, large cascade, and loss, and achieve the effect of low-loss transonic cascade design

Active Publication Date: 2016-04-20
AECC SHENYANG ENGINE RES INST
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Problems solved by technology

[0003] The purpose of the present invention is to provide a high-pressure turbine transonic guide vane cascade design method, at least to solve t

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  • Transonic guide blade grid design method of high-pressure turbine
  • Transonic guide blade grid design method of high-pressure turbine
  • Transonic guide blade grid design method of high-pressure turbine

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[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to design of a high-pressure turbine blade grid, in particular to a transonic guide blade grid design method of a high-pressure turbine, and at least solves the problem of higher loss of the blade grid caused by a traditional blade grid design method. The transonic guide blade grid design method of the high-pressure turbine comprises the following steps: the load of an area from an inlet of a blade grid channel to the front part of a geometric throat part of the blade grid channel is reinforced; the blade grid is divided into a front part area, a throat part area and a diffusion area; the airflow acceleration performance of the front part area is improved, and the length of the diffusion area is increased; the expansion acceleration of transoic airflow in the throat part area is weakened; the acceleration performance of airflow in the diffusion area is reduced; a compression wave is formed in the diffusion area near an outlet of the channel for reducing speed; and the blade grid design is finished according to a blade grid 11 parameter shaping method. The transonic guide blade grid design method of the high-pressure turbine can control the multishock loss in the blade grid design, realizes low-loss transonic blade grid design, and lays foundation for pneumatic design of the high-pressure turbine.

Description

technical field [0001] The invention relates to the design of a high-pressure turbine cascade, in particular to a design method for a high-pressure turbine transonic guide vane cascade. Background technique [0002] In order to achieve the goals of high turbine power, compact structure and low cost, aero turbine engines and gas turbine high-pressure turbines generally adopt high expansion ratio designs. Due to the increase of stage load, the flow in the turbine guide vane cascade changes from subsonic flow to transonic flow, and the exit Mach number also reaches supersonic level. Therefore, the shock wave loss generated by the airflow under supersonic conditions during the turning process of the cascade replaces the friction loss of the cascade and becomes the main loss in the transonic guide vane cascade. The existing cascade design methods are mainly based on the subsonic cascade environment. Under the transonic condition, the shock wave loss cannot be suppressed, resulti...

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Application Information

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IPC IPC(8): F01D9/02
CPCF01D9/02F05D2220/80
Inventor 李孝堂李鑫陈云马广健王雷黄玉娟
Owner AECC SHENYANG ENGINE RES INST
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