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Turbine stator vane, and gas turbine

A turbine and vane technology, applied in the cooling of turbines/propulsion devices, mechanical equipment, engine components, etc., can solve the problems of cooling medium flow rate reduction, heat transfer rate reduction, etc., and achieve the suppression of cooling efficiency reduction and thermal stress suppression Effect

Pending Publication Date: 2021-11-23
MITSUBISHI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At the above-mentioned turn-back portion, there is a possibility that the flow rate of the cooling medium decreases and the heat transfer rate decreases

Method used

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  • Turbine stator vane, and gas turbine
  • Turbine stator vane, and gas turbine
  • Turbine stator vane, and gas turbine

Examples

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Embodiment Construction

[0105] Hereinafter, several embodiments of the present invention will be described with reference to the drawings. However, dimensions, materials, shapes, relative arrangements, and the like of components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention thereto, but are merely illustrative examples.

[0106] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" indicating a relative or absolute arrangement not only mean strictly Arrangement also means a state in which there is a tolerance or is relatively displaced by an angle or a distance to the extent that the same function can be obtained.

[0107] For example, expressions such as "same", "equal", and "homogeneous" that indicate the state of equality of things not only indicate a state of strict equality but also a state of difference in the degree of tolerance or t...

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PUM

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Abstract

A turbine stator vane according to one embodiment of the present invention is provided with an airfoil portion which includes a plurality of cooling flow passages and a plurality of return flow passages, and in which at least one of the return flow passages is internally provided with a serpentine flow passage disposed toward the inside or the outside, in the vane height direction, relative to a gas path surface, a vane body including a shroud provided on at least one of a distal end side or a base end side, in the vane height direction, of the airfoil portion, and a lid portion which is fixed to an end portion on the distal end side or the base end side of the airfoil portion in the vane height direction, forms said at least one return flow passage, and is separate from the airfoil portion, wherein: the lid portion is formed such that in inner wall surface width forming a flow passage width of the return flow passage is greater than the flow passage width of the cooling flow passage formed in the airfoil portion; and the minimum value of the thickness of the lid portion is less than the thickness of the part of the shroud to which the lid portion is attached.

Description

technical field [0001] The invention relates to a turbine vane and a gas turbine. Background technique [0002] Turbine blades have a cooling structure because they are exposed to high-temperature fluids such as combustion gases. As a cooling structure of the turbine blade, for example, a structure in which the airfoil portion is cooled by allowing a cooling medium to flow through a detour flow path formed inside the airfoil portion. [0003] The detour flow path includes a plurality of cooling flow paths extending in the blade height direction inside the airfoil portion and partitioned by partition walls. For example, the cooling medium that flows from one side in the blade height direction to the other side in a certain cooling flow path flows into the cooling flow adjacent to the cooling flow path through the part turned back on the other side of the cooling flow path. way, so that it flows from the other side to one side. At the above-mentioned turn-back portion, ther...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F02C7/18
CPCF01D9/02F01D5/187F05D2240/81F05D2260/201F05D2240/12F01D9/023F02C7/18F05D2220/32
Inventor 小薮豪通羽田哲
Owner MITSUBISHI HEAVY IND LTD