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Turbine rotor blade of gas turbine

A technology for turbine rotors and gas turbines, which is applied in the direction of blade support components, mechanical equipment, engine components, etc., and can solve problems such as failure to effectively solve the problem of heat dissipation at the leading edge and trailing edge of the blade

Active Publication Date: 2019-11-05
HANGZHOU TURBINE POWER GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The utility model improves the aerodynamic performance and stable working range of the rotor blade by changing the structure of the top of the rotor blade, but still fails to effectively solve the heat dissipation problem of the leading edge and the trailing edge of the blade

Method used

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  • Turbine rotor blade of gas turbine
  • Turbine rotor blade of gas turbine
  • Turbine rotor blade of gas turbine

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Experimental program
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Effect test

Embodiment Construction

[0025] The present invention will be further described in conjunction with specific embodiment now.

[0026] figure 1 is a longitudinal sectional view of a gas turbine rotor blade, figure 2 yes figure 1 D-D cross-sectional view. Such as figure 1 , figure 2 As shown, the blade is mainly divided into three parts: the blade shape 1 , the blade root 3 , and the blade platform 5 , and the blade platform 5 plays the role of connecting the blade shape 1 and the blade root 3 .

[0027] The outer surface of the blade airfoil is composed of a pressure surface and a suction surface. The concave side of the airfoil outer surface is the pressure surface, and the convex side is the suction surface. The junction area between the suction surface and the pressure surface forms the leading edge 6 of the blade and the trailing edge 15 of the blade. ; There is at least one cooling air channel circuit inside the blade airfoil 1, each circuit has at least one cooling air channel and a coolin...

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Abstract

The invention relates to a turbine rotor blade of a gas turbine. The turbine rotor blade of the gas turbine comprises a blade profile, a blade platform, a blade top and a blade root, wherein a coolingair channel loop is arranged in the blade, a cooling air channel and a cooling air channel inlet are arranged in the loop, and ribs are arranged in the cooling air channel; and the blade surface is divided into a blade leading edge and a blade trail edge by a pressure surface and a suction surface. The blade tail edge is provided with a tail edge exhaust slot, a tail edge channel is provided witha guide groove structure, and at least one turbulence column is arranged in the guide groove structure; and the blade root cooling air channel is divided into at least two channels by a partition plate, and the partition plate is gradually bent towards the front edge side of the blade in the airflow direction. According to the turbine rotor blade of the gas turbine, the heat exchange effect of aleading edge channel, the tail edge exhaust slot and cooling air in the blade can be improved, and the leading edge metal temperature close to the blade platform and the metal temperature of the tailedge, the blade platform close to the tail edge and the blade root can be reduced.

Description

technical field [0001] The invention relates to a turbine rotor blade of a gas turbine, in particular to a rotor cooling blade with multiple cooling circuits and enhanced blade cooling effect. Background technique [0002] One of the keys to improving the efficiency of gas turbines is to increase the intake air temperature before the turbine, but the high-temperature mechanical properties of superalloy materials used to manufacture turbine blades cannot keep pace with the increase in gas temperature before the turbine. On the premise of significantly increasing the cooling air consumption, the blade cooling structure is continuously improved to improve the cooling efficiency. The internal cooling structure of the turbine rotor blades of the world's mainstream gas turbines adopts the form of multi-channels with loops. The cooling air is discharged from the trailing edge of the blades after passing through the channels and loops to exchange heat with the metal blades, so that ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18F01D5/14
CPCF01D5/188F01D5/141
Inventor 戴斌蓝吉兵隋永枫吴宏超魏佳明初鹏王博
Owner HANGZHOU TURBINE POWER GRP
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