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Auxiliary fixture for gas turbine primary guide vanes and film hole measuring method

A technology of guide vanes and gas turbines, applied in the direction of measuring devices, manufacturing tools, workpiece clamping devices, etc., can solve the problems of inconvenient measurement of tiny air film holes and difficulty in determining the measurement coordinate system, so as to facilitate the determination of the coordinate system and the convenience of measurement , The effect of easy positioning

Active Publication Date: 2015-12-23
CHINA HANGFA SOUTH IND CO LTD
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides an auxiliary fixture and a measuring method for the air film hole of the first-stage guide vane of a gas turbine to solve the technical problems that the measurement coordinate system of the first-stage guide vane of the gas turbine is difficult to determine and the measurement of tiny air film holes is inconvenient

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  • Auxiliary fixture for gas turbine primary guide vanes and film hole measuring method
  • Auxiliary fixture for gas turbine primary guide vanes and film hole measuring method

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Embodiment Construction

[0037] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.

[0038] The shape, position and size of the first-stage guide vanes of the gas turbine are designed based on the stacking axis, including the angle of the gas film hole and the structure of the inner cavity. However, it is difficult to directly determine the center of the stacking axis. The positioning reference is complex, and currently only a compound optical coordinate machine can be used to detect whether the blade size meets the requirements of the drawing. However, the air film hole structure of the gas turbine first-stage guide vane is complex, the hole diameter is small, and there are spatial positions and angles. If the contact probe of the three-coordinate machine is used alone, there will be interference when measuring tiny shapes. Even if...

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Abstract

The invention discloses an auxiliary fixture for gas turbine primary guide vanes and a film hole measuring method. The auxiliary fixture is used for auxiliary positioning when a gas turbine primary guide vane is measured. The auxiliary fixture comprises a support disk used for assembling a gas turbine primary guide vane and a clamp holder used for clamping the gas turbine primary guide vane. The support disk comprises a flat top face and an end face fitting the outer edge plate of the gas turbine primary guide vane, and one end of the clamp holder is connected to the opposite face of the end face. On one hand, the auxiliary fixture is used as an assembling tool to guide the gas turbine primary guide vane into a composite optical coordinate machine. On the other hand, the clamp holder indicates the center of the stacking shaft of the gas turbine primary guide vane to enable the composite optical coordinate machine to easily find the center of the stacking shaft of the gas turbine primary guide vane and establish a coordinate system and assist the composite optical coordinate machine in positioning. The auxiliary fixture makes a gas turbine primary guide vane positioned easily, facilitates determination of a coordinate system, and makes measurement more convenient.

Description

technical field [0001] The invention relates to the field of engines, in particular to an auxiliary clamp for a first-stage guide vane of a gas turbine. In addition, the present invention also relates to a method for measuring the air film hole of the first-stage guide vane of the gas turbine using the above-mentioned auxiliary fixture of the first-stage guide vane of the gas turbine. Background technique [0002] The first-stage guide vane of a gas turbine is subjected to the impact of high-temperature and high-pressure gas after combustion, and its combustion temperature will exceed the melting point of the blade material. In order to ensure that the first-stage guide vane of the gas turbine can still work normally when it exceeds the melting point of the material, it is necessary to rely on film cooling technology. The main structural feature of the film cooling technology is to design a large number of film holes (also called cooling holes) on the leading edge and blade...

Claims

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Application Information

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IPC IPC(8): G01B11/26G01B11/27B25B11/00
Inventor 陈芳林建辉
Owner CHINA HANGFA SOUTH IND CO LTD
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