An internal cooling structure of double-layer turbine blades based on steam cooling

A technology for turbine blades, steam cooling, applied in the direction of blade support elements, machines/engines, mechanical equipment, etc.

Active Publication Date: 2021-01-19
XI AN JIAOTONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In the existing gas turbine steam cooling technology, the external steam generator is an indispensable and important equipment, so it is only used in the combined combustion and steam cycle unit

Method used

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  • An internal cooling structure of double-layer turbine blades based on steam cooling
  • An internal cooling structure of double-layer turbine blades based on steam cooling
  • An internal cooling structure of double-layer turbine blades based on steam cooling

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Embodiment Construction

[0027] The present invention is described in further detail below in conjunction with accompanying drawing:

[0028] refer to figure 1 The steam-cooled double-layer turbine blade internal cooling structure of the present invention includes a turbine blade 1 and a porous medium layer 3; a cavity is provided in the turbine blade 1, and the porous medium layer 3 is located in the turbine blade 1. In the cavity, the porous medium layer 3 is provided with an internal chamber 4, an intermediate chamber 2 is formed between the outer wall of the porous medium layer 3 and the inner wall of the turbine blade 1, and the trailing edge or end of the turbine blade 1 is provided with steam Outlet 5, the inner chamber 4 is filled with saturated water, and the middle chamber 2 is filled with superheated steam; the size and shape of the porous medium layer 3 are determined according to the blade shape of the turbine blade 1, and the porous medium layer 3 is located on the turbine blade 1 at th...

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Abstract

The invention discloses a double-layer turbine blade interior cooling structure based on steam cooling. The double-layer turbine blade interior cooling structure comprises a turbine blade and a porousmedium layer, wherein a cavity is formed in the turbine blade; the porous medium layer is located in the cavity in the turbine blade; an inner chamber is formed in the porous medium layer; a middle chamber is formed between the outer wall of the porous medium layer and the inner wall of the turbine blade; a steam outlet is formed in the side wall of the turbine blade; the inner chamber is filledwith saturated water; and the middle chamber is filled with superheated steam. The structure is capable of cooling the interior of the turbine blade by using steam; meanwhile, an external steam generator is not needed.

Description

technical field [0001] The invention belongs to the field of impeller machinery, and relates to a steam cooling-based internal cooling structure of double-layer turbine blades. Background technique [0002] The gas turbine plays an important role in the national economy, and the inlet temperature of the turbine is one of the important parameters that determine the output power of the gas turbine. As the output of the gas turbine continues to increase, the inlet temperature of the turbine is also getting higher and higher. At present, the turbine inlet temperature of H-class advanced heavy-duty gas turbines has reached 1430°C-1600°C. Turbine blades directly bear the scour of high-temperature gas. In order to ensure the normal operation of the blades, efficient cooling measures must be used to cool the blades. [0003] At present, the commonly used blade cooling method is composite cooling composed of internal cooling and external cooling. Internal cooling includes impingem...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
CPCF01D5/18
Inventor 李亮李健武符阳春王杰枫
Owner XI AN JIAOTONG UNIV
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