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turbine blades

A technology of blades and turbines, applied in the field of gas turbines, which can solve the problems of gas temperature drop and thermal efficiency reduction of gas turbines, and achieve the effects of improving thermal efficiency, improving performance, and reducing the cross-sectional area of ​​the flow path

Active Publication Date: 2016-03-09
MITSUBISHI POWER LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As a result, low-temperature cooling air is blown out from the film cooling holes, the gas temperature of the gas turbine decreases, and the thermal efficiency of the gas turbine may decrease.

Method used

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Embodiment Construction

[0028] Below, refer to figure 1 and figure 2 One embodiment of the turbine blade according to the present invention will be described.

[0029] figure 1 It is a schematic perspective view showing a gas turbine 1 provided with a turbine blade 10 according to the present invention, showing a state where the upper half of the wheel house is removed, figure 2 It is a cross-sectional view of a main part of the turbine blade 10 according to the present embodiment, when the substantially central portion is cut along a plane substantially perpendicular to the axis in the direction in which it is erected.

[0030] Such as figure 1 As shown, the gas turbine 1 mainly includes: a compression part 2 that compresses combustion air, a combustion part 3 that injects fuel into the high-pressure air sent from the compression part 2 and burns it to generate high-temperature combustion gas, and is located in the combustion part. The turbine part 4 is driven by the combustion gas blown out ...

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Abstract

The invention provides a vane for a turbine. The vane can reduce the amount of cooling air, namely cooling media, and can prevent low temperature cooling air from being blown out of film cooling holes. Turbulent flow cooling is carried out on an inner circumferential face (17) on the belly side of a vane body (11), turbulent flow cooling is further conducted on an inner circumferential face (17) on the back side of the vane body (11) by a part of cooling media, and the part of cooling media is blown out of film cooling holes (13) in the back side of the vane body (11).

Description

[0001] This application is a divisional application of an invention patent application with an application date of November 7, 2008, an application number of 200880129918.9 (international application number of PCT / JP2008 / 070271), and an invention title of "turbine blade". technical field [0002] The present invention relates to a gas turbine, and more specifically relates to turbine blades (stationary blades, moving blades) of the gas turbine. Background technique [0003] As a turbine blade (for example, a second-stage stator blade) in a turbine section of a gas turbine, a turbine blade disclosed in Patent Document 1, for example, is known. [0004] Patent Document 1 Japanese Patent Application Laid-Open No. 3-253701 [0005] However, in the turbine blade disclosed in Patent Document 1, in order to efficiently cool the inner wall surface (inner peripheral surface) of the blade body, it is necessary to locate the turbulent flow holes as close as possible to the inner wall s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18F01D9/02
Inventor 羽田哲桥本朋子由里雅则桑原正光
Owner MITSUBISHI POWER LTD