Airfoil prognosis for turbine engines

• US 7,824,147 B2
• Filed: 05/16/2006
• Issued: 11/02/2010
• Est. Priority Date: 05/16/2006
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Tulpule, Sharayu, Littles, Jerrol W., Morris, Robert J.
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): EASTMAN, AARON ROBERT
• Application Number:
  US11/435,171
• Publication Number:
  US 20070271023A1
• Time in Patent Office: 1,631 Days
• Field of Search: 415/1, 415/17, 415/118, 415/9, 415/14, 701/99, 701/100, 701/101, 416/2, 416/61, 737/87, 702/81
• US Class Current: 415/1
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F05D 2270/11 to prolong engine life
• CPC Class Codes: F05D 2270/708 with comparison tables

Abstract

A method and control for predicting the remaining useful life of an airfoil for a gas turbine engine includes the steps of monitoring conditions of the blade such as flutter, leaning, etc. A measured amount of deflection of the airfoil is compared to tabulated data to predict an expected crack length which is likely causing the deflection, etc. Once a predicted crack length has been identified, the amount of accumulated damage to the airfoil at the crack is monitored and stored. The amount of useful life for the blade can be predicted by compiling the accumulated damage over time. The useful life remaining can be displayed such that flight plans or maintenance schedules for the aircraft can be modified as appropriate.

Claims

1. A turbine engine rotor section comprising:

a rotor carrying a plurality of blades; and

a sensor positioned relative to said rotor, said sensor for sensing a condition of a plurality of said blades, as said blades move past said sensor, said sensor transmitting information to a computer, said information being monitored at said computer to predict damage in a blade within said rotor, and said predicted damage being utilized to predict an expected life of said blade, and said information including deformation of the blade as said rotor rotates.

2. The turbine engine rotor section of claim 1 wherein the predicted damage is a predicted length of a crack in said blade.

3. The turbine engine rotor section of claim 1 wherein the predicted damage is predicted utilizing a formula.

4. The turbine engine rotor section of claim 1 wherein said expected life of said blades is associated with an amount of continued operation of the blade.

5. The turbine engine rotor section of claim 4 wherein the amount of continued operation of the blades is expressed in terms of flights.

6. A method of operating a rotor for a turbine engine including the steps of:

(a) providing a rotor including a plurality of blades; and

(b) sensing a condition of one of said blades, and said sensing including utilizing a sensor positioned off of said blades to sense the condition of a plurality of said blades as said plurality of said blades move past said sensor, and transmitting sensed information to be utilized to determine predicted damage in a blade within said rotor, said predicted damage being utilized to predict an expected life of said blade, and said information including deformation of a blade as said rotor rotates.

7. The method of claim 6 wherein the predicted damage is a predicted length of a crack in said blade.

8. The method of claim 6 further including that a rotational speed of the rotor is utilized to predict an expected life of said blade.