Method for measuring the deformation of a turbo-machine blade during operation of the turbo-machine

Patent metadata

Field	Value
Publication number	US-9366599-B2
Application number	US-201313767056-A
Country	US
Kind code	B2
Filing date	Feb 14, 2013
Priority date	Feb 14, 2012
Publication date	Jun 14, 2016
Grant date	Jun 14, 2016

Abstract

A method for measuring the deformation of a turbo-machine blade including:
a step of positioning at least one accelerometer onto a local point of the turbo-machine blade; a first step of measuring the centrifugal force, by the accelerometer, at the local point of the turbo-machine blade along the given measurement direction at a first predetermined speed; a second step of measuring the centrifugal, at a second predetermined speed; a step of determining the angular displacement of the measurement direction of the accelerometer relative to the centrifugal direction as a function of the first acceleration measurement and the second acceleration measurement, said angular displacement corresponding to an angular deformation of the local point of the turbo-machine blade.

First claim

The invention claimed is:

1. A method for measuring the deformation of a turbo-machine blade comprising:
positioning an accelerometer onto a local point of the turbo-machine blade, the accelerometer being capable of measuring an acceleration at the local point of the turbo-machine blade along a first given measurement direction;
rotating the turbo-machine blade at a first predetermined speed such that the accelerometer is subjected to a first centrifugal force having a determined direction;
obtaining a first value of the first centrifugal force at the first predetermined rotation speed;
measuring the first centrifugal force, by the accelerometer, at the local point of the turbo-machine blade along the first given measurement direction;
rotating the turbo-machine blade at a second predetermined speed, different from the first predetermined speed, so as to cause an angular displacement of the measurement direction of the accelerometer relative to the centrifugal direction and the accelerometer is subjected to a second centrifugal force;
obtaining a second value of the second centrifugal force at the second predetermined rotation speed;
measuring the second centrifugal force, by the accelerometer, at the local point of the turbo-machine blade along the first given measurement direction displaced by the angular displacement; and
determining the angular displacement as a function of the measured centrifugal forces at the first predetermined speed and the measured centrifugal forces at the second predetermined speed, said angular displacement corresponding to an angular deformation of the local point of the turbo-machine blade,
wherein the angular displacement is determined by the following formula:

α
x

=

arccos
⁡

(

Gx
G

)

-

arccos
⁡

(

Gx
′

G
′

)

in which α x at is the angular displacement, Gx is the first centrifugal force measured along the first given measurement direction, G is the first centrifugal force, Gx′ is the second centrifugal force measured along the first given measurement direction displaced by the angular displacement, and G′ is the second centrifugal force.

2. The method according to claim 1 , wherein the accelerometer being capable of measuring the acceleration at the local point of the turbo-machine blade along first and second given measurement directions, the method comprises:
measuring the first centrifugal force, by the accelerometer, at the local point of the turbo-machine blade along the first and second given measurement directions at the first predetermined speed;
rotating the turbo-machine blade at the second predetermined speed different from the first predetermined speed, so as to cause the angular displacement of the first and second given measurement directions relative to the centrifugal direction;
measuring the second centrifugal force, by the accelerometer, at the local point of the turbo-machine blade along the first and second given measurement directions displaced by the angular displacement at the second predetermined speed; and
determining the angular displacement as a function of the measured centrifugal forces at the first predetermined speed and the measured centrifugal forces at the second predetermined speed, said angular displacement corresponding to the angular deformation of the local point of the turbo-machine blade.

3. The method according to claim 2 , wherein the first and second measurement directions are orthogonal, the angular displacement being determined by the following formula:

α
x

=

arccos
⁡

(

Gx
G

)

-

arccos
⁡

(

Gx
′

G
′

)

in which α x is the angular displacement, Gy is the first centrifugal force measured along the second given measurement direction, Gx is the first centrifugal force measured along the first given measurement direction, Gy′ is the second centrifugal force measured along the second given measurement direction displaced by the angular displacement, and Gx′ is the second centrifugal force measured along the first given measurement direction displaced by the angular displacement.

4. The method according to claim 1 , wherein the accelerometer is capable of measuring the acceleration at the local point of the turbo-machine blade along at least three different given measurement directions forming an orthogonal trihedron.

5. The method according to claim 1 , wherein the accelerometer is a microelectromechanical system.

6. The method according to claim 1 , wherein the accelerometer has a mass in the order of 0.1 g.

7. The method according to claim 1 , wherein at least one accelerometer is positioned at the surface of the turbo-machine blade.

8. The method according to claim 1 , wherein at least one accelerometer is positioned in the thickness direction of the turbo-machine blade.

9. The method according to claim 1 , wherein the accelerometer is positioned on a turbo-machine blade of composite material.

10. The method according to claim 5 , wherein, the accelerometer is a piezoresistive sensor.

Assignees

• Snecma

Inventors

• Leroux Andre

Classifications

• F01D17/06

  responsive to speed · CPC title

• G01M5/0041

  by determining deflection or stress · CPC title

• G01M5/0016

  of aircraft wings or blades · CPC title

• G01M15/14 Primary

  Testing gas-turbine engines or jet-propulsion engines · CPC title

• G01H1/006

  of the rotor of turbo machines · CPC title