Novel trailing edge cooling structure with Y-shaped jet holes of turbine blade

Abstract

The invention discloses a novel trailing edge cooling structure with Y-shaped jet holes of a turbine blade. The trailing edge of an integral trapezoidal structure is internally provided with a coolingworking medium supply cavity, a first cooling cavity, a second cooling cavity and an outlet section successively, wherein a first partition plate is arranged between the cooling working medium supplycavity and the first cooling cavity; a second partition plate is arranged between the first cooling cavity and the second cooling cavity; the plurality of uniformly distributed first Y-shaped jet holes are formed in the first partition plate; and the plurality of uniformly distributed second Y-shaped jet holes are formed in the second partition plate. During work, a working medium enters the second cooling cavity successively through the cooling working medium supply cavity and the first cooling cavity, and the working medium after heat exchange is recovered through the outlet section connected to the second cooling cavity. According to the novel trailing edge cooling structure with Y-shaped jet holes of the turbine blade provided by the invention, the trailing edge cooling effect can beenhanced obviously and the pressure loss is reduced.

Description

technical field [0001] The invention belongs to the technical field of turbine cooling for gas turbines, and in particular relates to a novel turbine blade trailing edge cooling structure with Y-shaped jet holes. Background technique [0002] With the continuous advancement of my country's modern industry, the efficient use of energy has become an increasingly critical issue. Compared with other energy conversion equipment, gas turbines have a series of advantages such as small size, light weight, and fast start-up, and play an important role in the pillar industries of the national economy such as aviation, ships, and electric power. Studies have shown that for every 55°C increase in the turbine inlet temperature, the power and efficiency of the gas turbine can increase by 10%. Therefore, continuously increasing the inlet temperature has become an inevitable requirement for the development of gas turbines. At present, the theoretical combustion temperature of hydrocarbon f...

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Problems solved by technology

[0003] The external flow at the trailing edge of the blade is relatively complex, and it is often subjected to a high thermal load due to the combined effects of factors such as shedding vortices, wakes, and fluid pulsations; on the other hand, the thinner trailing edge structure makes the internal cooling channel relatively Narrow and complex cooling structures cannot be arranged, which puts higher requirements on the design of internal cooling structures

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