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Gas turbine guide vane

A technology of guide vanes and gas turbines, applied in climate sustainability, sustainable transportation, machines/engines, etc., can solve problems such as poor cooling effect and difficult casting

Active Publication Date: 2021-09-10
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The invention provides a gas turbine guide vane to solve the technical problems of the existing guide vanes such as high casting difficulty and poor cooling effect

Method used

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Embodiment Construction

[0035] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.

[0036] refer to figure 2, the preferred embodiment of the present invention provides a gas turbine guide vane, comprising a blade airfoil, the blade airfoil has an airfoil leading edge 10, a trailing edge 20, a blade pot 30 and a blade back 40, and a single inner cavity is also provided in the blade airfoil 50. An impact tube 60 communicating with the cold air circuit is installed in the inner cavity 50. The front edge of the impact tube 60 is provided with a jet slit 601 that runs through the front edge. The jet slit 601 is used for the cold air flow in the inner cavity 50. Jet impingement cooling is performed on the inner wall surface of the airfoil leading edge 10 after piercing. The outer wall surface of the airfoil leading edge 10 is also provided with mult...

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Abstract

The invention discloses a gas turbine guide vane. The gas turbine guide vane comprises a vane body, a single inner cavity is further formed in the vane body, an impact pipe communicating with a cold air loop is installed in the inner cavity, a jet flow slit penetrating through the front edge of the impact pipe is formed in the front edge of the impact pipe, and the jet flow slit is used for allowing cold airflow in the inner cavity to penetrate through and then conducting jet flow impact cooling on the inner wall face of the blade-shaped front edge. The outer wall face of the blade-shaped front edge is further provided with a plurality of crossed air film hole sets penetrating through the blade-shaped front edge, first air film holes in the crossed air film hole sets are perpendicular to the outer wall face of the blade-shaped front edge in the blade-shaped section, and included angles of 30-60 degrees are formed between the first air film holes and the blade-shaped section. According to the gas turbine guide vane, the casting difficulty of the guide vane can be greatly reduced, the cooling effect is better, the temperature field is more uniform, and the diffusion of cold airflow can be reduced, so that under the condition of the same gas amount and cold air amount, the covering effect of a gas film formed by the cold airflow on the outer wall face of the blade-shaped front edge is better, and the cooling effect is better.

Description

technical field [0001] The invention relates to the field of gas turbine engines, in particular to a gas turbine guide vane. Background technique [0002] In order to improve the thermal efficiency and power output level of the gas turbine engine, the gas turbine inlet temperature is continuously increased. The gas turbine inlet temperature of the advanced aero-engine currently in service has reached 1500K-1800K, which is far beyond the allowable temperature of the turbine blade material. Therefore, it is necessary to limit the temperature of the turbine blade. The temperature level and distribution within the material (causing thermal stresses) to ensure a reasonable lifetime for the turbine blades. [0003] In order to ensure the operation of gas turbine guide vanes under extreme heat load conditions, reliable and effective thermal protection measures must be adopted. The current main technical measures are advanced cooling design technology and high temperature resistant ...

Claims

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Application Information

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IPC IPC(8): F01D9/02F01D25/12
CPCF01D9/02F01D25/12Y02T50/60
Inventor 邓丽君赵尊盛杨琴余毅邓维
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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