A supercharged cooling structure for gas turbine moving blades using the rotation effect
A cooling structure, gas turbine technology, applied in engine components, climate sustainability, machines/engines, etc., can solve problems such as large pressure gradients, and achieve the effect of enhancing the supercharging effect and reducing the pressure demand
Active Publication Date: 2022-07-12
XI AN JIAOTONG UNIV
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Problems solved by technology
[0004] The purpose of the present invention is to provide a gas turbine moving blade pressurized cooling structure utilizing the rotation effect, and improve the strength of the blade through the Z-shaped rotary pressurized cavity with a triangular structure; The separation makes the rotating Coriolis force always point to the impact-convection series cooling laminates when the cooling air flow in the air supply chamber moves radially, which not only improves the air supply pressure of the impact-convection series cooling laminates, but also effectively solves the high speed condition Excessive pressure gradient between downforce side and suction side cooling airflow
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[0036] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While 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 so that the present disclosure will be more thoroughly understood, and will fully convey the scope of the present disclosure to those skilled in the art. It should be noted that the embodiments of the present invention and the features of the embodiments may be combined with each other under the condition of no conflict. The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
[0037] In order to make the objectives, technical effects and technical solutions of the present invention clearer, t...
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The invention discloses a supercharging cooling structure for a gas turbine moving blade by utilizing the rotation effect. The structure is specifically composed of a flow-to-intermediate partition plate, a multi-stage Z-shaped rotary booster cavity, and an impact-convection series cooling layer, all of which are located inside the gas turbine moving blades, and the Z-shaped rotary booster cavity passes through the separation pressure. The surface and suction surface supply air to the cavity and organize the radial flow direction in the air supply cavity, and use the rotating Coriolis force to increase the air supply pressure of the shock-convective series cooling layer and reduce the air supply pressure gradient between the suction and pressure surfaces; shock- The convection series cooling layer plate increases the Reynolds number by collecting the impinging cooling air flow, and adopts the radial guide baffle with the guide slit to enhance the transverse vortex formed by the rotating Coriolis force in the radial convection heat exchange chamber, which effectively improves the heat transfer rate. thermal coefficient. The invention can utilize the rotation effect to reduce the demand for the cooling air extraction pressure and air extraction volume, and effectively enhance the cooling performance.
Description
technical field [0001] The invention belongs to the technical field of gas turbine turbine cooling, and in particular relates to a supercharging cooling structure for gas turbine moving blades utilizing a rotation effect. Background technique [0002] Due to its compact size, light weight, high power, and fast start-up, gas turbines are widely used in aerospace, ship power and other industrial fields, and play an important role in the national economic life. In extremely high temperature gas, the inlet temperature even exceeds the melting point of the superalloy. In order to ensure the safe operation and working life of the gas turbine and improve the overall performance, it is necessary to effectively cool the gas turbine blades. [0003] The traditional blade cooling structure is usually designed and tested according to the aerodynamic process under static conditions, but the rotating effect of high-speed rotation when the gas turbine is working has a significant impact on...
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IPC IPC(8): F01D5/18F01D25/00
CPCF01D5/186F01D25/00Y02T50/60
Inventor 张荻杨立克杜秋晚谢永慧
Owner XI AN JIAOTONG UNIV
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