Blade verification plates and method of use

a technology of verification plate and blade, applied in the field of gas turbine engines, can solve the problems of time-consuming and expensive methods

Inactive Publication Date: 2010-03-18
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method suffers from obvious inherent inaccuracies associated with manual measurements and is time consuming.
However, this method is costly.

Method used

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  • Blade verification plates and method of use
  • Blade verification plates and method of use
  • Blade verification plates and method of use

Examples

Experimental program
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Embodiment Construction

[0013]Referring to FIGS. 1 and 2, there illustrated are three adjacent rotor stages 100, 102, 104 stacked together such that the stages 100-104 are adjacent one another, for example, in a final assembly condition. Each stage 100-104 includes a plurality of blades or airfoils 106 placed around the outer periphery of the corresponding rotor 100-104. Typically, in modern rotors the blades 106 are in a clocked relationship as between any two stages 100-104. The stages 100-104 may comprise those of a turbine engine, such as a steam turbine engine or those that are a part of a compressor of a gas turbine engine. For description purposes, the turbine engine herein will refer to a gas turbine engine, however this is merely for descriptive purposes, and is not intended to limit the invention.

[0014]In accordance with an embodiment of the invention, three blade verification plates 108, 110, 112 are provided wherein each plate 108-112 is placed over a corresponding single blade 106 in each of t...

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PUM

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Abstract

A first plate includes an opening configured to be placed over a blade of a first rotor. A second plate includes an opening configured to be placed over a blade of a second rotor. Each plate includes a first pin configured to contact a leading edge of a blade located on one side of the blade in the opening and a second pin configured to contact a leading edge of a blade located on an opposite side of the blade in the opening, and a third pin configured to contact a leading edge of the blade in the opening. An indicator line is marked on the first plate and a pair of boundary lines marked on the second plate are spaced apart a distance indicative of an acceptable range for blade clocking between the first and second rotors when the indicator line is located between the boundary lines.

Description

BACKGROUND OF THE INVENTION[0001]The subject matter disclosed herein relates to gas turbine engines and, more particularly, to blade verification plates that facilitate the location of the leading edge of the blades on a rotor within a turbine engine, such as a gas turbine engine or a steam turbine engine, and further provide an indication as to whether the blade clocking is within an acceptable tolerance range.[0002]Clocking of blades on rotating rotors or wheels is common in gas turbine engines, especially on modern rotors. Clocking generally refers to the relative positioning of two rows of blades or airfoils with respect to each other (e.g., the blades on two adjacent stages of a compressor), wherein such blade positioning can affect the efficiency of the gas turbine. Prior methods for determining whether the blade clocking is within an acceptable tolerance range involve manual measurements taken using a plum line and a ruler with two or more stages stacked on top of each other....

Claims

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Application Information

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IPC IPC(8): G01B5/25
CPCG01B5/25G01B5/205
InventorPETROSKIE, ROBERT MICHAELDEMPSEY, CRESTON LEWISNUNEZ, ROBERTO ANTHONY
OwnerGENERAL ELECTRIC CO