Method and system for detecting high turbine temperature operations

Patent metadata

Field	Value
Publication number	US-11280683-B2
Application number	US-201715609633-A
Country	US
Kind code	B2
Filing date	May 31, 2017
Priority date	May 31, 2017
Publication date	Mar 22, 2022
Grant date	Mar 22, 2022

Abstract

Herein provided are methods and systems for detecting a high temperature condition of a gas turbine engine. A fuel flow to a combustor of the engine and a compressor outlet pressure of the engine are obtained. A ratio of the fuel flow to the compressor outlet pressure is determined. The ratio is compared to a threshold and a high temperature condition of the engine is detected when the ratio exceeds the threshold.

First claim

The invention claimed is:

1. A method for detecting a high temperature condition of a gas turbine engine, the method comprising:
obtaining a fuel flow to a combustor of the engine and a compressor outlet pressure of the engine;
modeling a temperature of the engine by determining a ratio of the fuel flow to the compressor outlet pressure, the ratio replacing a measured temperature of the engine;
comparing the ratio to a threshold that varies as a function of engine rotational speed; and
detecting a high temperature condition of the engine when the ratio exceeds the threshold, wherein the high temperature condition is detected in absence of the measured temperature of the engine.

2. The method of claim 1 , wherein the threshold increases with increasing engine rotational speed for a first range of engine rotational speeds.

3. The method of claim 2 , wherein the threshold is constant for a second range of engine rotational speeds, the second range following the first range.

4. The method of claim 3 , wherein the first range of engine rotational speeds corresponds to the engine idling and the second range of engine rotational speeds corresponds to the engine accelerating.

5. The method of claim 1 , further comprising determining a current engine rotational speed and wherein comparing the ratio to the threshold comprises comparing the ratio to the threshold based on the current engine rotational speed.

6. The method of claim 1 , wherein the threshold corresponds to an engine temperature limit while the engine is operating under at least one steady state condition.

7. The method of claim 6 , further comprising selecting the threshold from a plurality of thresholds as a function of a current operating state of the engine.

8. The method of claim 1 , wherein obtaining the fuel flow and the compressor outlet pressure comprises measuring the fuel flow and the compressor outlet pressure.

9. The method of claim 1 , further comprising selecting the threshold from a plurality of thresholds depending on one or more of engine rotational speed, altitude, ambient temperature and aircraft bypass door position.

10. A system for detecting a high temperature condition of a gas turbine engine, the system comprising:
a processing unit; and
a non-transitory computer-readable memory having stored thereon program instructions executable by the processing unit for:
obtaining a fuel flow to a combustor of the engine and a compressor outlet pressure of the engine;
modeling a temperature of the engine by determining a ratio of the fuel flow to the compressor outlet pressure, the ratio replacing a measured temperature of the engine;

comparing the ratio to a threshold that varies as a function of engine rotational speed; and
detecting a high temperature condition of the engine when the ratio exceeds the threshold, wherein the high temperature condition is detected in absence of the measured temperature of the engine.

11. The system of claim 10 , wherein the threshold increases with increasing engine rotational speed for a first range of engine rotational speeds.

12. The system of claim 11 , wherein the threshold is constant for a second range of engine rotational speeds, the second range following the first range.

13. The system of claim 12 , wherein the first range of engine rotational speeds corresponds to the engine idling and the second range of engine rotational speeds corresponds to the engine accelerating.

14. The system of claim 10 , wherein the program instructions are further executable by the processing unit for determining a current engine rotational speed and wherein comparing the ratio to the threshold comprises comparing the ratio to the threshold based on the current engine rotational speed.

15. The system of claim 10 , wherein the threshold corresponds to an engine temperature limit while the engine is operating under at least one steady state condition.

16. The system of claim 15 , wherein the program instructions are further executable by the processing unit for selecting the threshold from a plurality of thresholds as a function of a current operating state of the engine.

17. The system of claim 10 , wherein obtaining the fuel flow and the compressor outlet pressure comprises measuring the fuel flow and the compressor outlet pressure.

18. The system of claim 10 , wherein the program instructions are further executable by the processing unit for selecting the threshold from a plurality of thresholds depending on one or more of engine rotational speed, altitude, ambient temperature and aircraft bypass door position.

Assignees

• Pratt & Whitney Canada

Inventors

• Lamarre Sylvain
• Charest Alexandre
• Des Roches-Dionne Nicolas

Classifications

• F02C9/00 Primary

  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 title

• F05D2270/112

  by limiting temperatures · CPC title

• G01K13/024

  of moving gases · CPC title

• G01K13/08

  in rotary movement · CPC title

• G01K2205/04

  for measuring exhaust gas temperature · CPC title