Methods of analysing apparatus

• US 10,352,823 B2
• Filed: 07/05/2013
• Issued: 07/16/2019
• Est. Priority Date: 12/21/2005
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Anuzis, Paul, Gelman, Leonid Moiseevich
• Primary Examiner(s): Nghiem, Michael P
• Application Number:
  US13/935,924
• Publication Number:
  US 20140180606A1
• Time in Patent Office: 2,202 Days
• Field of Search: 702 36, 702 39
• CPC Class Codes: G01H 1/006 of the rotor of turbo machines
• CPC Class Codes: G01M 15/14 Testing gas-turbine engines or jet-propulsion engines
• CPC Class Codes: G01M 5/0066 by exciting or detecting vibration or acceleration vibration testing of structures G01M7/00

Abstract

Engine health monitoring is used to assess the health of an engine, such as a gas turbine engine. Blades mounted on a shaft produce a modal response when excited. The shaft has an order related component that varies with the rotational velocity of the shaft. Modal responses are increased when the natural frequency range of the selected blade mode intersects with one of the order related components. By applying a short time chirp-Fourier transform with a frequency speed that is a function of a rate of change in the rotational velocity of the shaft a selected signal can be isolated. Cracks in the blades can be detected from the isolated signal.

Claims

1. A method for determining an artifact in a component, the method comprising:

a) exciting the component to induce a resonance response;

b) calculating real and imaginary components of bi-coherence b of the resonance response at pk0 and qk0, where p and q are integers and k0 is a component resonant frequency;

c) determining a position or area of the calculated real and imaginary components in two-dimensional space; and

d) determining the presence of the artifact in the component from the position or area of the calculated real and imaginary components;

wherein the component is a blade;

wherein the blade is mounted on a shaft; and

wherein the blade is excited by rotating the shaft at a selected rotational velocity such that an order related component of the shaft intersects with the natural frequency range of the blade.

2. The method according to claim 1, wherein

the shaft is operated between a first rotational velocity and a second rotational velocity different from the first rotational velocity with a rate of change of shaft velocity to provide a signal that comprises a plurality of periodic responses,

the signal is transformed using a short-time chirp Fourier transform, thereby isolating a selected periodic response, and

a frequency speed of the short-time chirp Fourier transform is a function of the rate of change of the shaft velocity.

3. The method according to claim 2, wherein the varying rotational velocity occurs during acceleration of the engine.

4. A method for determining an artifact in a component, the method comprising:

a) exciting the component to induce a resonance response;

b) calculating real and imaginary components of bi-coherence b of the resonance response at pk0 and qk0, where p and q are integers and k0 is a component resonant frequency;

c) determining a position or area of the calculated real and imaginary components in two-dimensional space;

d) determining the presence of the artifact in the component from the position or area of the calculated real and imaginary components; and

e) correcting the artifact in the component.