Turbine blades that reduce cooling degradation by regulating the location of internal dust deposits

Abstract

The invention relates to a turbine blade which slows down the degradation of cooling effect by regulating the internal dust deposition position, and belongs to the technical field of gas turbines. The turbine blade has a double-wall structure, and a shielding structure is connected to the inner wall of the existing double-wall. The turbine blade of the present invention regulates the internal dust deposition position through the shielding structure to slow down the degradation of the cooling effect of the turbine blade, and the dust deposited on the double wall can be reduced by 10% to 13%, thereby slowing down the cooling effect of the blade by 20% to 23%. The degradation time is relatively simple, and the shape of the shielding structure is relatively simple, easy to process, and strong in realizability.

Description

technical field [0001] The invention belongs to the technical field of gas turbines, and in particular relates to a turbine blade which slows down the degradation of cooling effect by regulating the internal dust deposition position. Background technique [0002] With the development of gas turbine technology, the temperature in front of the turbine is further increased, which puts forward higher requirements for the cooling of turbine blades. At present, in the prior art, the cooling methods inside the blade mainly include convection cooling and impingement cooling, among which impingement cooling is the most effective method to enhance the local cooling effect. Impingement cooling mainly uses high-speed airflow to scour the surface to be cooled to achieve the purpose of cooling. The cooling air enters the double-walled structure with spoiler columns through the jet hole, and the airflow direction is as follows: figure 1 As shown, impact the surface to be cooled to achieve...

AI Technical Summary

Problems solved by technology

[0003] When the aircraft takes off, lands or passes through the volcanic ash cloud, the engine will inevitably inhale dust, and the cooling air with dust enters the double-wall structure through the jet hole, and the dust will form deposits inside the double-wall structure. The conductivity is relatively small, which is equivalent to adding a large thermal resistance during the heat transfer process, which seriously affects the heat transfer capacity and cooling effect of the blade

Especially the deposition on the impact target surface greatly weakens the effect of impact cooling, resulting in attenuation of cooling performance of blades

[0004] The current turbine blades have no effective measures to suppress internal dust deposition, and the problem of dust deposition has become increasingly prominent. Solving the problem of dust deposition inside the blades is crucial to the stable operation of high-performance gas turbines

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