Advanced turbine cooling method based on porous media and super-critical state fluid circulation

A technology of porous media and fluid circulation, applied in the direction of blade support components, engine components, machines/engines, etc., can solve the problems of reducing engine efficiency and small heat exchange area, and achieve high efficiency, high heat exchange intensity, and large efficiency The effect of the heat transfer area

Active Publication Date: 2014-10-22
BEIHANG UNIV
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

The disadvantage of this cooling method is that the heat transfer area is small, and it can only be used in such as figure 1 The cooling channel shown in (b)① performs heat exchange around, and the effective heat exchange area is small; in addition, since the cold air comes from the air in the compressor, this will inevitably reduce the efficiency of the engine

Method used

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  • Advanced turbine cooling method based on porous media and super-critical state fluid circulation
  • Advanced turbine cooling method based on porous media and super-critical state fluid circulation
  • Advanced turbine cooling method based on porous media and super-critical state fluid circulation

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Embodiment 1

[0031] like Figure 4 As shown in a high-pressure turbine rotor blade, the shape of the blade has been aerodynamically designed to meet the overall performance requirements of the engine for the turbine components. The internal cooling channel of the turbine blade is designed as a single channel (such as Figure 4 As shown in ①), a rib is arranged inside the blade (such as Figure 4 ② in), and the structural form of this cooling channel is called a single-channel single-rib form. The porous medium is completely filled in the cooling channel in the blade. The pores of the porous medium are designed to be circular, with an average diameter of 300 microns, and the arrangement adopts sandstone-like accumulations. The supercritical fluid flows radially from the front end of the blade into the cooling channel and enters the porous medium, moves to the rear end in the form of seepage, and flows out of the blade with a flow rate of 80kg / s. Through this cooling method, the surface t...

Embodiment 2

[0034] A kind of advanced turbine blade cooling method based on porous medium and supercritical state fluid circulation in embodiment 1, wherein the cooling channel in the turbine is Figure 5 The single channel shown ( Figure 5 In ①) three ribs ( Figure 5 ②) in the structural form.

Embodiment 3

[0036] A kind of advanced turbine blade cooling method based on porous medium and supercritical state fluid circulation in embodiment 1, wherein the cooling channel in the turbine is Figure 6 The dual channel shown ( Figure 6 ①② in the three ribs ( Figure 6 ③) in the structural form.

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Abstract

The invention discloses an advanced turbine cooling method based on porous media and super-critical state fluid circulation. According to the method, cooling channels in turbine blades are filled with porous media materials to increase the effective heat exchange area, and the effective heat exchange area depends on the shape, size and arraying direction of micro-pore structures; super-critical state fluid which is small in flowing resistance and high in heat exchange capacity serves as heat exchange media, so that the actual heat exchange amount is larger than the heat exchange amount in a conventional heat exchange model according to actual heat exchange requirements, and the number of cooling channels in the blades and the number of rib plates in the blades can be designed; according to the actual heat exchange requirements, the size, shape and arraying direction of the porous media can be designed; the blades can be machined integrally through a laser rapid forming technology or other high-energy-beam rapid forming technologies. The advanced turbine cooling method achieves direct and rapid forming, the technology is simple, and the structure, shape and position designability is high.

Description

technical field [0001] The invention relates to an advanced turbine cooling method based on porous media and supercritical state fluid circulation, which is mainly used to reduce the heat load of turbine blades and improve the working life of the turbine, and belongs to the technical field of aeroengines and high-speed rotating machinery. Background technique [0002] The temperature before the turbine determines the thermal efficiency of the aero-engine. The increase in the temperature before the turbine can improve the efficiency of the aero-engine, which can reduce the fuel consumption rate for civil aircraft and bring economic benefits, and can increase the thrust per unit area for military aircraft to obtain better maneuverability. However, the temperature in front of the turbine cannot increase infinitely, which is mainly limited by the material of the turbine. Excessive temperature will affect the strength, toughness and service life of the material. At present, the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
Inventor 陈懋章邹正平刘火星丁超
Owner BEIHANG UNIV
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