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Virtual turbomachine blade contact gap inspection

A turbine and blade technology, applied in the field of virtual turbine blade contact clearance inspection, can solve labor-intensive and time-consuming problems

Active Publication Date: 2017-02-22
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This inspection process presents challenges as loading the blades on the rotor wheel, filling all contact gaps, measuring contact gaps / shims and removing all blades is very labor intensive and time consuming

Method used

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  • Virtual turbomachine blade contact gap inspection
  • Virtual turbomachine blade contact gap inspection
  • Virtual turbomachine blade contact gap inspection

Examples

Experimental program
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Embodiment Construction

[0079] As indicated above, the present disclosure provides a virtual turbine blade contact clearance check. Embodiments of the invention may include computerized methods and systems for virtually inspecting contact clearances of blade stages of a turbomachine. The blade stage to be inspected has known dimensions, ie outer radius, circumference, inner radius, number of blades, etc.

[0080] now refer to figure 1 , shows a block diagram of an illustrative environment 100 for virtually inspecting contact clearances of blade stages of a turbomachine in accordance with an embodiment of the present disclosure. To this end, the environment 100 includes a computer infrastructure 102 capable of performing the various process steps described herein for virtually inspecting the contact gap of a blade stage of a turbomachine. In particular, a computer infrastructure 102 is shown that includes a computing device or system 104 that includes an inspection system 106 that enables the comput...

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PUM

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Abstract

A system and method for virtually inspecting contact gaps of a blade stage(140) of a turbomachine is disclosed. The system may include a digitizing device(130) for obtaining a three-dimensional model(132) of a shroud(134,152) of each blade(140) of the blade stage(140). A computer system may include at least one module configured to perform the following steps: extracting a geometric location data of a hard place plane of each shroud(134,152) from the three-dimensional model(132); generating a three-dimensional virtual rendering of the shrouds(134,152) of the blade stage(140) based on the geometric location data and the known dimensions of the blade stage(140), the three-dimensional virtual rendering including a rendering of contact gaps between adjacent shrouds(134,152); and inspecting the blade stage(140) using the three-dimensional virtual rendering(150).

Description

technical field [0001] The present disclosure relates generally to machine inspection, and more specifically to virtual turbine blade contact clearance inspection. Background technique [0002] In a turbine, blades are used to generate power from the flow of a working fluid. Specifically, a plurality of vanes may be coupled to the rotor such that flow of working fluid therefrom imparts rotational motion to the rotor. Turbine blades are initially shaped based on idealized models to create efficient blades. Each blade may include a shroud at its outer end that includes a hard surface that interacts with a mating hard surface of the shroud of an adjacent blade. Hardfaces are the portions of the sleeve that contain abrasive material and are in contact with each other at base load to damp vibration. During turbine engine operation, shrouded turbine blades are subject to substantial deformation and twisting. The contact gap between two adjacent blades is critical to ensure bla...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50G06T17/00
CPCG06T17/00G06F30/20G01B21/16G06T19/00F05D2260/80F01D5/005F01D5/225F05D2260/81G06F30/00G06T19/20
Inventor J.A.萨尔姆J.R.康诺尔J.D.埃尔诺
Owner GENERAL ELECTRIC CO