Rotary cooling channel turbine blade adopting T-shaped partition wall

Abstract

The invention belongs to the technical field of turbine blades, and relates to a rotary cooling channel turbine blade adopting a T-shaped partition wall. The interior of the blade structure is divided into four cooling channels in the direction from the leading air inlet edge to the trailing air outlet edge, and the rotary T-shaped partition walls are adopted in the second cooling channel and the third cooling channel; chordwise partition walls extending in the chordwise direction and sub-channel partition walls approximately perpendicular to the blade chordwise direction are arranged in the channels; and in the top view of the blade, the two partition walls are approximately vertically arranged and form a T-shaped partition wall, and each cooling channel is further divided into three cooling cavities by the T-shaped partition wall, namely a back side front cavity, a back side rear cavity and a basin side cavity. According to the rotary cooling channel turbine blade, the internal space of the blade is subdivided through the multiple partition walls, the cold air flowing distance can be prolonged, the rich inner cavity heat exchange area is formed on the side surfaces of the partition walls, and the heat exchange area is increased by about 30% compared with a conventional rotation structure.

Description

technical field

[0001] The invention belongs to the technical field of turbine blades, and relates to a rotary cooling channel turbine blade using a T-shaped partition wall. Background technique

[0002] Turbine blades, as the main parts of aero-engines, work in high-temperature, high-pressure, and high-velocity gas environments. The cooling problem is very prominent, which directly affects the efficiency and safety of the whole machine. In order to ensure the reliable operation of the turbine blades, the main solution is to adopt a hollow design, use cold air to enhance convection heat transfer inside the blades to remove heat, and form a covering gas film to isolate the heating of the gas when the blades are discharged. The focus and goal of blade cooling design are "larger internal heat transfer area", "smaller cold air flow resistance", "higher heat transfer efficiency", "larger air film coverage area", "impact on structural strength". Less damage", "lower processing an...

Images