A supercharged cooling structure for gas turbine moving blades using the rotation effect

Abstract

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...

AI Technical Summary

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

Images