Gas turbine engine health determination

Patent metadata

Field	Value
Publication number	US-10822996-B2
Application number	US-201815918266-A
Country	US
Kind code	B2
Filing date	Mar 12, 2018
Priority date	Mar 12, 2018
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A method for determining an engine heath of an aircraft engine includes determining, by one or more control devices, the aircraft engine is operating in a bleed off condition; determining, by the one or more control devices, a first engine health modifier value while the aircraft engine is operating in the bleed off condition, the first of engine health modifier value including a compressor leakage flow value; determining, by the one or more control devices, a second plurality of engine health modifier values while the aircraft engine is operating in a bleed on condition; and determining, by the one or more control devices, an engine health parameter using at least one of the second plurality of engine health modifier values determined while the aircraft engine is operating in the bleed on condition and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

First claim

What is claimed is:

1. A method for determining an engine heath of an aircraft engine comprising:
determining, by one or more control devices, the aircraft engine is operating in a bleed off condition;
determining, by the one or more control devices, a first engine health modifier value while the aircraft engine is operating in the bleed off condition, the first of engine health modifier value including a compressor leakage flow value;
determining, by the one or more control devices, a second plurality of engine health modifier values while the aircraft engine is operating in a bleed on condition; and
determining, by the one or more control devices, an engine health parameter using at least one of the second plurality of engine health modifier values determined while the aircraft engine is operating in the bleed on condition and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

2. The method of claim 1 , wherein determining, by the one or more control devices, the engine health parameter comprises determining, by the one or more control devices, the engine health parameter using a component level engine model tuned using at least one of the second plurality of engine health modifier values and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

3. The method of claim 1 , wherein determining, by the one or more control devices, the first engine health modifier value comprises receiving, by the one or more control devices, data indicative of the first engine health modifier value from one or more sensors.

4. The method of claim 1 , wherein determining, by the one or more control devices, the second plurality of engine health modifier values comprises receiving, by the one or more control devices, data indicative of the second plurality of engine health modifier values from one or more sensors.

5. The method of claim 1 , wherein the first engine health modifier value is one of a first plurality of engine health modifier values, and wherein the first plurality of engine health modifier values additionally includes a first compressor component efficiency value and a first compressor flow scaler value.

6. The method of claim 1 , wherein the second plurality of engine health modifier values includes a second compressor component efficiency value and a second compressor flow scaler value.

7. The method of claim 6 , wherein determining, by the one or more control devices, the engine health parameter comprises determining, by the one or more control devices, the engine health parameter using the second compressor component efficiency value, the second compressor flow scaler value, and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

8. The method of claim 1 , wherein the bleed on condition is a flight operating condition of the aircraft engine.

9. The method of claim 8 , wherein determining, by the one or more control devices, the engine health parameter comprises determining, by the one or more control devices, the engine health parameter continuously during the flight operating condition.

10. The method of claim 1 , wherein determining, by the one or more computing devices, the engine health parameter comprises determining, by the one or more computing devices, an engine performance factor for the aircraft engine.

11. The method of claim 1 , wherein determining, by the one or more computing devices, the engine health parameter further comprises:
receiving, by the one or more computing devices, data indicative of an operating condition of the aircraft engine while the aircraft engine is operating in the bleed on condition; and
determining, by the one or more computing devices, the engine health parameter further using the received data indicative of the operating condition of the aircraft engine while the aircraft engine is operating in the bleed on condition.

12. The method of claim 11 , wherein the data indicative of the operating condition of the aircraft engine includes data indicative of a fuel flow to a combustion section of the aircraft engine, data indicative of one or more ambient conditions of the aircraft engine, or both.

13. The method of claim 1 , further comprising:
determining, by the one or more computing devices, the aircraft engine is operating in the bleed on condition.

14. The method of claim 1 , wherein the aircraft engine is a turboshaft engine for a helicopter.

15. The method of claim 1 , further comprising:
providing, by the one or more computing devices, data to an operator indicative of the determined engine health parameter.

16. The method of claim 1 , further comprising:
controlling, by the one or more computing devices, the aircraft engine based at least in part on the determined engine health parameter.

17. A computing device comprising a one or more processors and at least one tangible non-transitory computer-readable medium, the computer-readable medium storing instructions that when executed by the processor perform operations, the operations comprising:
determining the aircraft engine is operating in a bleed off condition;
determining a first engine health modifier value while the aircraft engine is operating in the bleed off condition, the first of engine health modifier value including a compressor leakage flow value;
determining a second plurality of engine health modifier values while the aircraft engine is operating in a bleed on condition; and
determining an engine health parameter using at least one of the second plurality of engine health modifier values determined while the aircraft engine is operating in the bleed on condition and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

18. The computing device of claim 17 , wherein determining the engine health parameter comprises determining the engine health parameter using a component level engine model tuned using at least one of the second plurality of engine health modifier values and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.

19. The computing device of claim 17 , wherein determining the first engine health modifier value comprises receiving data indicative of the first engine health modifier value from one or more sensors.

20. The computing device of claim 17 , wherein determining the second plurality of engine health modifier values comprises receiving data indicative of the second plurality of engine health modifier values from one or more sensors.

Assignees

• Gen Electric

Inventors

• Dowdell Charles William
• Paul Jacques
• Morrison Paul J

Classifications

• B64U50/12

  using turbine engines, e.g. turbojets or turbofans · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F05D2270/313

  Air temperature · CPC title

• F05D2270/3011

  Inlet pressure · CPC title

• F01D21/003 Primary

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title