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AIRFOIL THICKNESS MEASUREMENT TOOL

IP.com Disclosure Number: IPCOM000247670D
Publication Date: 2016-Sep-26
Document File: 6 page(s) / 113K

Publishing Venue

The IP.com Prior Art Database

Abstract

A tool is configured to slide over or otherwise be attached to a turbine engine airfoil. The tool includes holes, slots, or other openings used to accurately guide an instrument in measuring a thickness of the airfoil.

This text was extracted from a PDF file.
This is the abbreviated version, containing approximately 51% of the total text.

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AIRFOIL THICKNESS MEASUREMENT TOOL

ABSTRACT


[0001] A tool is configured to slide over or otherwise be attached to a turbine engine airfoil. The tool includes holes, slots, or other openings used to accurately guide an instrument in measuring a thickness of the airfoil.

BACKGROUND


[0002] This disclosure relates generally to gas turbine engines and more particularly to internal airfoils of such engines.


[0003] A gas turbine engine includes multiple rotor and stator stages, each stage including a plurality of airfoils (i.e. blades and vanes). In operation, engine airfoils experience loss of material resulting in a reduction of the airfoil's thickness dimension ("thickness loss") due to wear from environmental factors. Understanding the amount of thickness loss is key to addressing efficiency concerns.


[0004] Existing methods for measuring thickness loss can be time-consuming and cannot always be performed at a higher level assembly or outside of a manufacturing environment.


[0005] Described herein is a tool for convenient measurement of airfoil thickness.

BRIEF DESCRIPTION OF THE DRAWINGS


[0006] The concept may be best understood by reference to the following description taken in conjunction with the accompanying drawing figures, in which:


[0007] FIG. 1 is a schematic side elevation view of a turbomachinery blade of a gas turbine engine;

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[0008] FIGS. 2-4 are schematic views of an airfoil thickness measurement tool constructed according to the concept described herein, from side elevation, top plan, and bottom plan directions, respectively;


[0009] FIG. 5 is a schematic side elevation view of the airfoil thickness measurement tool of FIGS. 2-4 with the airfoil of FIG. 1 inserted therein; and


[0010] FIG. 6 is a schematic top plan view of the airfoil thickness measurement tool of FIGS. 2-4 with the airfoil of FIG. 1 inserted therein and a measuring instrument engaging the airfoil.

DETAILED DESCRIPTION OF THE CONCEPT


[0011] Illustrated in FIG. 1 is an exemplary turbomachinery blade 10 for a gas turbine engine. The turbomachinery blade 10 includes a dovetail 12, a shank 14, a platform 16, and an airfoil 18. The airfoil 18 extends in span from a root 20 to a tip 22 and includes opposed pressure and suction sides 24, 26 respectively extending between a leading edge 28 and a trailing edge 30. A parameter referred to as the airfoil's "chord" is defined as the length of a straight line connecting the furthest extents of the leading edge 28 and the trailing edge 30. A thickness of the airfoil 18 is defined as the distance between the pressure and suction sides 24, 26.


[0012] FIG. 2 illustrates an exemplary thickness measurement tool 32 which may be u...