Internal cooling structure of turbine movable vane

Abstract

The invention discloses an internal cooling structure of a turbine movable vane. The internal cooling structure of the turbine movable vane comprises a U-shaped channel and a trapezoidal channel. TheU-shaped channel comprises a U-shaped channel inlet section, a U-shaped channel outlet section and a U-shaped channel top turn area which are formed in an integrated manner. The U-shaped channel inletsection and the U-shaped channel outlet section communicate through a plurality of connection bridges. The U-shaped channel outlet section communicates with the trapezoidal channel through a plurality of jet flow holes. A plurality of oval pits are arranged at the bottom face of the U-shaped channel. A plurality of fins are arranged in the trapezoidal channel. In work, a cooling working medium firstly enters the U-shaped channel inlet section to conduct heat exchange with the channel surface, then the cooling working medium flows into the U-shaped channel outlet section via the U-shaped channel top turn area and the connection bridges, after completing heat exchange with the wall face of the U-shaped channel, the cooling working medium is sprayed into the trapezoidal channel through the jet flow holes, and after conducting heat exchange with the wall face of the trapezoidal channel, the cooling working medium is discharged in a lateral direction. The internal cooling structure of theturbine movable vane achieves the advantage of high heat conductivity, low resistance, high adaptability and the like through coupling of multiple structures.

Description

technical field [0001] The invention belongs to the technical field of turbine cooling, in particular to a cooling structure inside a turbine moving blade. Background technique [0002] The development level of aero-engines and heavy-duty gas turbines is an important manifestation of a country's industrial strength. Their design and manufacturing process involves a large number of key technologies, and has a remarkable multi-disciplinary integration feature. It is a huge system engineering. Therefore, all major countries in the world will The development of "two machines" has been promoted to the height of national strategy. [0003] Increasing the gas temperature in the combustor is an important way to improve the power and efficiency of aero-engines and heavy-duty gas turbines. Therefore, gas turbines continue to develop along with the increase in gas temperature before the turbine. When the gas turbine is running, the turbine blades are directly in contact with the high-...

AI Technical Summary

Problems solved by technology

At the same time, due to the special shape of the turbine blades, the design of the internal cooling structure must match the shape of the blades, and the rotating effect of the rotor blades will significantly affect the internal heat transfer performance, which brings great challenges to the design of the internal cooling structure of the turbine rotor blades. challenge

[0005] For the internal cooling of turbine blades, relevant researchers and designers have proposed a large number of cooling structures, but most of the cooling structures are designed based on independent cooling units, without considering the interaction between different cooling units and the rotation In addition, in order to adapt to the development of a new generation of gas turbines, it is necessary to further improve the enhanced heat transfer capacity of the internal cooling channel

Images