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A method for measuring the size of transition section of gas turbine combustor

A gas turbine, size detection technology, applied in the direction of combustion method, combustion chamber, continuous combustion chamber, etc., can solve the problems of narrowing the processing size tolerance range of parts in the transition section of the combustion chamber, design reference deviation, affecting the characteristic size of parts, etc., and achieve the detection results Intuitive, improve detection efficiency, facilitate production and processing size adjustment and fitter repair effect

Active Publication Date: 2019-03-05
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage of this detection method is that it narrows the machining dimension tolerance range of parts in the transition section of the combustion chamber, and judges qualified parts as out-of-tolerance parts
This is because the measurement datum established by the three-coordinate CMM inspection is formed according to the end face of the part to be inspected or the inner and outer contours of the end face, which leads to a deviation between the measurement datum of the inspected part and the design datum of the part, which affects the judgment of the feature size of the part

Method used

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  • A method for measuring the size of transition section of gas turbine combustor
  • A method for measuring the size of transition section of gas turbine combustor
  • A method for measuring the size of transition section of gas turbine combustor

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Embodiment 1

[0018] The invention provides a method for detecting the size of the transition section of the gas turbine combustor, which is characterized in that: the method for detecting the size of the transition section of the gas turbine combustor, the function of the parts of the transition section of the gas turbine combustor in the combustion chamber components It is the transfer transition, which transfers the high-temperature gas from the air inlet, that is, the round mouth end, to the gas outlet end through the profile transfer, to achieve the purpose of rectification; in order to meet the assembly requirements of the transition section of the combustion chamber, the processing of the transition section of the combustion chamber In the process, it is enough to ensure its relative assembly size requirements in the lower-level components. By simulating the assembly state of the transition section of the combustion chamber, a comprehensive measuring tool is designed and manufactured ...

Embodiment 2

[0024] The invention provides a method for detecting the size of the transition section of the gas turbine combustor, which is characterized in that: the method for detecting the size of the transition section of the gas turbine combustor, the function of the parts of the transition section of the gas turbine combustor in the combustion chamber components It is the transfer transition, which transfers the high-temperature gas from the air inlet, that is, the round mouth end, to the gas outlet end through the profile transfer, to achieve the purpose of rectification; in order to meet the assembly requirements of the transition section of the combustion chamber, the processing of the transition section of the combustion chamber In the process, it is enough to ensure its relative assembly size requirements in the lower-level components. By simulating the assembly state of the transition section of the combustion chamber, a comprehensive measuring tool is designed and manufactured ...

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Abstract

The invention provides a method for size detection of a transition section of a gas-turbine combustion chamber. The length dimension D2 of the transition section of the combustion chamber is detected. The length dimension is the horizontal distance D2 and the vertical distance D1 between an air inlet, i.e., the round opening end face center, and an air outlet end face center of transition section of the combustion chamber. Thus, when a comprehensive measurement tool is designed, the vertical distance D1 is set as a theoretical value. When the air inlet, i.e., the round opening end face center is fixed through natural expansion, a scratch awl mechanism fixed on the air inlet, i.e., the round opening end center on the measurement tool is used for detecting the relative height dimension of the air inlet, i.e., the round opening end face, and judging the length dimension of the transition section of the combustion chamber. The method is characterized in that a coordinate measurement machine is prevented for reducing the detection tolerance range; the part detection efficiency is improved by 50% or more; the detection results are direct and specific; production, processing, dimension adjustment and repairing by bench workers are facilitated; and reference and basis are provided for processing detection of other similar parts.

Description

technical field [0001] The invention relates to the field of processing parts of a transition section of a combustion chamber of a gas turbine, in particular to a method for detecting the size of a transition section of a combustion chamber of a gas turbine. Background technique [0002] The transition section of the combustion chamber of the subcontracted gas turbine product is a medium-thick plate sheet metal welded part, which is a special-shaped cylinder part. The difference is made of 13 to 24 smooth sections. In order to detect the distance between the center of the air inlet (round mouth) and the center of the air outlet (square fan) in the transition section, the left and right deviation between the center of the air outlet (square fan) and the center of the air inlet (round mouth), the air outlet ( The flatness and other dimensions of the end face of fan-shaped square mouth), the traditional detection method is to use three-coordinate CMM to establish a coordinate ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01B21/02F23R3/60
CPCF23R3/60G01B21/02
Inventor 杨海钢杨树余李塞川
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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