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Method for the dimensional inspection of a turbomachine component

A technology of turbine components and turbines, which is applied in the testing of mechanical components, testing of machine/structural components, and the use of mechanical devices, etc., which can solve the problems of lack of accuracy of control components

Active Publication Date: 2021-12-03
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This can lead to a lack of accuracy when controlling components
To fix this, the operator may have to change machine settings or manually move the component or palpation element until the correct reference point is found on the component to be controlled

Method used

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  • Method for the dimensional inspection of a turbomachine component
  • Method for the dimensional inspection of a turbomachine component
  • Method for the dimensional inspection of a turbomachine component

Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0034] figure 1 Illustrates a turbine component obtained using a lost wax casting operation and is to be controlled to check that its dimensions conform to a theoretical component or model by using software provided for this purpose obtained by computer-aided design or drafting (CAO / DAO).

[0035] Specifically, the turbine component is the movable blades 1 of a low pressure turbine. Of course, the blade may be a distributor blade, or alternatively a blade for equipping another component of the turbomachine.

[0036] A turbine (not shown), in particular a two-flow turbine with a longitudinal axis, usually comprises a gas generator with a fan mounted upstream. In the present invention, in general, the terms "upstream" and "downstream" are defined with respect to the fluid flow in the turbine, here along the longitudinal axis X. The gas generator includes a gas compressor assembly (which may include a low-pressure compressor and a high-pressure compressor), a combustor, and a ...

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PUM

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Abstract

The invention concerns a method for the dimensional inspection of a turbomachine component to be inspected comprising a first surface (10) delimited by a second peripheral surface (11) substantially transverse to the first surface and a profile defined by a numerical theoretical model with a theoretical surface (10T) corresponding to the first surface (10), the first surface (10) having larger dimensions than the second peripheral surface (11), the method comprising the following steps: - determining theoretical points (Pt; Pt 1) on the theoretical surface (10T) of the numerical theoretical model; - calibrating calibration points (Pe; Pe1) on the first surface (10) of the component to be inspected (1); - calculating an offset axis (AD) for each theoretical point (Pt; P1) with respect to a corresponding calibration point (Pe; Pe1), - acquiring inspection points (Pc, Pc1, Pc2) on the second peripheral surface of the component to be inspected from the offset axis.

Description

technical field [0001] The present invention relates to the manufacture of turbine components, and more particularly, to a method of dimensional control of turbine components such as turbine blades manufactured by casting or forging. Background technique [0002] Improving the performance of turbines requires the production of mechanical components, such as blades, with optimized aerodynamic profiles. A twin-body turbine comprises, for example, a ring of blades for a low-pressure turbine stage with dimensions (thickness or width) of a few millimeters. These blade rings are usually manufactured by casting and pouring metal into molds using a technique known as lost wax, which allows the desired blade shape to be obtained directly without the need to implement machining steps to obtain the finished component. [0003] However, casting techniques do not always allow specific parts of the blade ring to achieve the required level of refinement, therefore, additional machining is...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01B5/008G01B21/04
CPCG01B21/047G01B5/008G01B21/042G01M13/00
Inventor 罗杰·乔治·卡曾阿诺德·亚历山大·文森特
Owner SAFRAN AIRCRAFT ENGINES SAS