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Gas turbine blade comprising V rib-pit composite cooling structures

A composite cooling and gas turbine technology, applied in the direction of blade support components, mechanical equipment, engine components, etc., can solve the problem of air volume reduction and achieve the effects of reducing blocking ratio, enhancing disturbance, and enhancing cooling effect

Inactive Publication Date: 2020-01-17
HARBIN ENG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The reduction of air volume will bring challenges to the cooling structure design of the turbine

Method used

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  • Gas turbine blade comprising V rib-pit composite cooling structures
  • Gas turbine blade comprising V rib-pit composite cooling structures
  • Gas turbine blade comprising V rib-pit composite cooling structures

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Embodiment Construction

[0020] The present invention is described in more detail below in conjunction with accompanying drawing example:

[0021] combine Figure 1-4b , figure 1 It shows a schematic cross-sectional view at A (transverse) of the present invention. The V-rib-dimple composite structure 1 in the present invention is inside the upper wall surface 3 and the lower wall surface 2 in the serpentine cooling channel in the middle of the blade. The diagonal rib cooling structure and internal impingement cooling structure of the leading edge of the blade and the cylindrical rib cooling structure of the trailing edge of the blade are similar to the interior of the conventional blade.

[0022] figure 2 A schematic diagram of the longitudinal section at B of the present invention is shown, which is a section view of the inner side of the upper wall of the blade. The cooling air flows in from the root of the blade, and part of the gas enters the cooling channel at the leading edge of the blade. A...

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Abstract

The invention provides a gas turbine blade comprising V rib-pit composite cooling structures. The gas turbine blade comprises an upper wall and a lower wall, wherein the upper wall is a suction surface, the lower wall is a pressure surface, the V rib-pit composite cooling structures are arranged on the inner walls of the upper wall and the lower wall, each V rib-pit composite cooling structure comprises a composite cooling unit, wherein the composite cooling unit comprises a right-angle V-rib and a circular pit behind the right-angle V-rib. The gas turbine blade has the advantages that the heat exchange area of the whole structure is increased, the heat exchange effect is improved, a fracture between the adjacent V-shaped ribs enhances the turbulent flow generated by the gas flow, so thatthe gas flow is separated to a large extent, and then is attached to the wall surface, so that the boundary layer is damaged in a large extent, the turbulence degree of the fluid is greatly enhanced,the heat exchange is greatly enhanced, the rib are interrupted, so that the blockage ratio is reduced, the pressure loss is reduced, the disturbance is enhanced while the front and rear air pressure of the rib is balanced, and the heat exchange is greatly enhanced.

Description

technical field [0001] The present invention relates to a gas turbine, in particular to a gas turbine blade. Background technique [0002] Gas turbines have the characteristics of light weight, small size, high power per unit, fast start-up, less pollution, high thermal efficiency, and good economy. It can be seen from the simple cycle mode of the gas turbine that the specific power and performance can be improved by increasing the initial temperature of the gas. The position where the turbine blades are located has high temperature, complex stress, and harsh working environment, so whether the turbine blades can work safely and reliably is very important to the operation of the engine. Various performance indicators of the blades have become an important indicator to measure the development of the engine, especially the ability of the turbine blades to withstand high temperatures. In short, the development level of turbine blades has become an important symbol to measure ...

Claims

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Application Information

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IPC IPC(8): F01D5/18
CPCF01D5/18F05D2260/2212F05D2260/22141
Inventor 栾一刚符昊严蓝漪殷越孙海鸥
Owner HARBIN ENG UNIV
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