Turbine guide vane structure with rib upper through seam on trailing edge

Abstract

The invention provides a turbine guide vane structure with a rib upper through seam on a trailing edge. The through seam is formed in a separation rib; after cooling airflow passes through an outflow seam, part of cooling air can cool the interiors of the separation rib through the through seam in the separation rib, so that under the condition that the cold air flow is not increased, the convection heat exchange intensity of the inner wall surface and the side wall surface of the separation rib is enhanced, and the comprehensive cooling effect of the trailing edge is improved; preferably, the through seam is an inclined seam, when cooling airflow passes through the separation rib, the strength of cold air vortexes generated under the influence of the separation rib can be weakened, so that the interaction between lip plate falling vortexes and the cold air vortexes can be weakened, and the air film cooling efficiency of the surface of the separation rib is improved. The structure is reasonable in design and simple in structure, and the inclined seam is formed in the side wall surface of the separation rib, so that the heat exchanger has good heat transfer and cooling characteristics, has good machining integrity and is more practicable.

Description

technical field [0001] The invention belongs to the technical field of cooling the turbine blades of gas turbines, and in particular relates to a turbine guide vane structure with through-slots on the ribs on the trailing edge. Background technique [0002] Aeroengines work under harsh conditions of high temperature and high pressure for a long time. In order to make them work continuously, reliably and with a long life, in addition to accelerating the development of new materials, it is necessary to effectively cool their hot end components such as turbine blades. The trailing edge is a typical high-temperature part of the blade. Due to the requirements of aerodynamic design, the trailing edge is usually designed to be very thin. How to efficiently cool it in a very small space is the main problem in its cooling design. Therefore, the trailing edge is also the most vulnerable to thermal corrosion. and damaged parts. The research on the film cooling characteristics of the t...

AI Technical Summary

Problems solved by technology

[0006] Aiming at the problem that the cooling of the partition rib is neglected in the design stage of the trailing edge cooling structure in the prior art, and the cooling of the side near the suction surface of the trailing edge is not perfect, resulting in a low cooling efficiency on the surface of the partition rib, the present invention proposes a trailing edge strip Turbine guide vane structure with ribs running through oblique slots

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