Method and apparatus for determining engine part life usage

• US 20060265183A1
• Filed: 05/10/2005
• Published: 11/23/2006
• Est. Priority Date: 05/10/2005
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Butz, Mark Gerard, Van Stone, Robert Hugh, Hindle, Edmund Hall III, Jacques, Kenneth Willson
• Granted Patent: US 7,197,430 B2
• Time in Patent Office: Days
• US Class Current: 702/181
• CPC Class Codes: F02C 9/00 Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/11 to prolong engine life
• CPC Class Codes: F05D 2270/708 with comparison tables

Abstract

A method for determining an engine part life usage of a gas turbine engine life limited part used on an aircraft. The method includes operating a gas turbine engine that includes a plurality of rotating components and a plurality of sensors configured to monitor a plurality of gas turbine engine operating parameters, obtaining outputs from the plurality of sensors, and utilizing at least some of the outputs to calculate the life usage of at least one life limited part to facilitate tracking the life-usage of an individual life limited part on the gas turbine engine that is consumed on a flight by flight basis.

Claims

1. A method for determining an engine part life usage of a gas turbine engine life limited part used on an aircraft, said method comprising:

operating a gas turbine engine that includes a plurality of rotating components and a plurality of sensors configured to monitor a plurality of gas turbine engine operating parameters;

obtaining outputs from the plurality of sensors; and

utilizing at least some of the outputs to calculate the life usage of at least one life limited part to facilitate tracking the life-usage of an individual life limited part on the gas turbine engine that is consumed on a flight by flight basis.

2. A method in accordance with claim 1 further comprising:

acquiring at least one data snapshot during engine operation, wherein the data snapshot includes a plurality of engine parameters collected at a single time interval; and

storing the data snapshot within a computer that is coupled to the gas turbine engine.

3. A method in accordance with claim 2 further comprising

comparing at least one parameter within the data snapshot to a known value during the flight;

and

outputting a K-factor for each life limited part based on the at least one parameter.

4. A method in accordance with claim 3 wherein comparing at least one parameter within the data snapshot to a known value further comprises:

comparing the at least one parameter to a predetermined value stored within a matrix; and

outputting a K-factor based on the comparison on each flight.

5. A method in accordance with claim 3 further comprising:

summing a plurality of K-factors generated for a single life limited part; and

comparing the summed K-factors to a predetermined limit to facilitate tracking the life-usage of individual life limited parts.

6. A method in accordance with claim 1 further comprising:

determining a down select criteria;

filtering the plurality of outputs to determine if the down select criteria is true;

downloading the plurality of outputs into a computer that is coupled to the gas turbine engine if the down select criteria is true; and

compressing the downloaded plurality of outputs into a single data file that is stored within the computer that is installed on the aircraft.

7. A method in accordance with claim 6 further comprising:

inputting the plurality of outputs into a performance cycle model;

combining the performance model and the plurality of outputs into a single data file; and

compressing the performance model calculated data and the plurality of outputs into a single data file that is stored within the computer that is installed on the aircraft.

8. A method in accordance with claim 6 further comprising:

transferring the compressed file to a ground based facility; and

utilizing the compressed file to facilitate tracking the life usage of individual life limited parts on the gas turbine engine.

9. A method in accordance with claim 8 further comprising:

transferring the compressed file to a ground based facility; and

utilizing the compressed file to facilitate tracking the life usage of individual life limited parts on the gas turbine engine on a flight by flight basis.

10. A method in accordance with claim 9 further comprising:

generating a plurality of compressed files; and

providing the compressed files to a customer to facilitate assessing the cumulative life usage of a plurality of life limited parts.

11. A control system coupled to a gas turbine engine, wherein the gas turbine engine includes a plurality of life limited parts, and a plurality of sensors configured to monitor a plurality of gas turbine engine operating parameters, said control system is configured to:

operate the gas turbine engine;

obtain outputs from the plurality of sensors; and

utilize at least some of the outputs to calculate the life usage of at least one of said life limited parts to facilitate tracking the life-usage of an individual life limited part on the gas turbine engine that is consumed on a flight by flight basis.

12. A control system in accordance with claim 11, wherein said control system is further configured to:

acquire at least one data snapshot during engine operation, wherein said data snapshot includes a plurality of engine parameters collected at a single time interval; and

store said data snapshot within said control system.

13. A control system in accordance with claim 12, wherein said control system is further configured to:

compare at least one parameter within said data snapshot to a known value during the flight; and

output a K-factor for each life limited part based on the at least one parameter.

14. A control system in accordance with claim 13, wherein said control system is further configured to:

compare the at least one parameter to a predetermined value stored within a matrix; and

output a K-factor based on the comparison on each flight.

15. A control system in accordance with claim 13, wherein said control system is further configured to:

download a plurality of K-factors generated for a single life limited part such that a customer can sum the plurality of K-factors and compare the summed K-factors to a predetermined limit to facilitate tracking the life-usage of individual life limited parts.

16. A control system in accordance with claim 11, wherein said control system is further configured to:

receive a down select criteria;

filter the plurality of outputs to determine if the down select criteria is true;

download the plurality of outputs into a computer that is coupled to the gas turbine engine if the down select criteria is true; and

compress the downloaded plurality of outputs into a single data file that is stored within said computer that is installed on the aircraft.

17. A control system in accordance with claim 16, wherein said control system is further configured to:

input the plurality of outputs into a performance cycle model;

combine the performance model calculated data and the plurality of outputs into a single data file; and

compress the performance model calculated data and the plurality of outputs into a single data file that is stored within the computer that is installed on the aircraft.

18. A control system in accordance with claim 16, wherein said control system is further configured to:

transfer the compressed file to a ground based facility such that a customer can utilize the compressed file to facilitate tracking the life-usage of individual life limited parts on the gas turbine engine.

19. A control system in accordance with claim 16, wherein said control system is further configured to:

transfer the compressed file to a ground based facility such that a customer can utilize the compressed file to facilitate tracking the life usage of individual life limited parts on the gas turbine engine on a flight by flight basis.

20. A control system in accordance with claim 19, wherein said system is further configured to generate a plurality of compressed files to a customer assessing the cumulative life usage of a plurality of life limited parts.