System and method for lightoff detection in turbine engines

• US 7,216,489 B2
• Filed: 05/26/2004
• Issued: 05/15/2007
• Est. Priority Date: 05/26/2004
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Uluyol, Onder, Mukavetz, Dale, Menon, Sunil K.
• Primary Examiner(s): CASAREGOLA, LOUIS J
• Application Number:
  US10/855,477
• Publication Number:
  US 20070051111A1
• Time in Patent Office: 1,084 Days
• Field of Search: 607/78, 607/86, 607/87, 607/90, 608/00, 431/14, 701/100
• US Class Current: 60/778
• CPC Class Codes: F02C 7/26 Starting; Ignition
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: F05D 2270/304 Spool rotational speed
• CPC Class Codes: F05D 2270/309 Rate of change of parameters
• CPC Class Codes: F05D 2270/44 active, predictive, or anticipative

Abstract

A system and method is provided for lightoff detection in a turbine engine that provides improved accuracy and consistency. The system and method use engine temperature and engine rotation speed sensor data to determine a first time interval during which the lightoff is estimated to have occurred. A peak gradient in the temperature sensor data within the first time interval and a peak gradient in the engine rotation sensor data within the first time interval are then determined. The temperature peak gradient time and the engine rotation peak gradient time are then used as boundaries to determine a narrowed time interval within the first time interval. The minimum gradient in the engine rotation sensor data in the narrowed time interval is determined, with the minimum gradient time in the engine rotation sensor data comprising an accurate estimate of lightoff time for the turbine engine.

Claims

1. A method of detecting combustion system lightoff in a turbine engine, the method comprising the steps of:

a) receiving engine temperature sensor data and engine speed sensor data for the turbine engine during startup;

b) determining a first time interval before a threshold time when the engine temperature sensor data reaches a threshold value;

c) determining a peak gradient of the engine temperature sensor data in the first time interval;

d) determining a peak gradient of the engine speed sensor data in the first time interval;

e) determining a second time interval between the peak gradient of the engine temperature sensor data and the peak gradient of the engine speed sensor data; and

f) determining a minimum gradient time of the engine speed sensor data in the second time interval, the minimum gradient time comprising an estimated lightoff time for the turbine engine.

2. The method of claim 1 wherein the step of determining a first time interval before a threshold time comprises determining the first time interval between an initial start time of the turbine engine and the threshold time.

3. The method of claim 2 wherein the initial start time comprises a time when an engine Starter begins to operate.

4. The method of claim 1 wherein the engine temperature sensor data comprises hot section temperature data.

5. The method of claim 1 wherein the engine temperature sensor data comprises exhaust gas temperature data.

6. The method of claim 1 wherein the engine speed data comprises engine rotational speed data N.

7. The method of claim 1 wherein the engine speed data comprises engine rotational speed data N2.

8. The method of claim 1 wherein the step of determining a peak gradient of the engine temperature sensor data in the first time interval comprises computing numerical derivatives using a central difference formula.

9. The method of claim 8 wherein the step of determining a peak gradient of the engine temperature sensor data in the first time interval further comprises and smoothing the numerical derivatives using a zero phase filter.

10. The method of claim 1 wherein the step of determining a peak gradient of the engine speed sensor data in the first time interval comprises computing numerical derivatives using a central difference formula.

11. The method of claim 10 wherein the step of determining a peak gradient of the engine speed sensor data in the first time interval further comprises and smoothing the numerical derivatives using a zero phase filter.

12. The method of claim 1 wherein the step of determining a minimum gradient time of the engine speed sensor data in the second time interval comprises computing numerical derivatives using a central difference formula further comprises and smoothing the numerical derivatives using a zero phase filter.

13. A method of detecting combustion system lightoff in a turbine engine, the method comprising the steps of:

a) receiving engine temperature sensor data and engine speed sensor data for the turbine engine during startup;

b) deter a peak gradient of the engine speed sensor data; and

c) determining a minimum gradient time of the engine speed sensor data after the peak gradient of the engine speed sensor data, the minimum gradient time comprising an estimated lightoff time for the turbine engine.

14. The method of claim 13 further comprising the step of determining a peak gradient of the engine temperature sensor data after the minimum gradient time of the engine speed sensor data to confirm that the lightoff has occurred.

15. The method of claim 14 wherein the engine temperature sensor data comprises exhaust gas temperature data.

16. The method of claim 13 wherein the engine speed data comprises engine rotational speed data N.

17. The method of claim 13 wherein the engine speed data comprises engine rotational speed data N2.

18. The method of claim 13 wherein the step of determining a peak gradient of the engine speed sensor data comprises computing numerical derivates using a central difference formula and smoothing the numerical derivatives using a zero phase filter.

19. The method of claim 13 wherein the step of determining a minimum gradient time of the engine speed sensor data comprises computing numerical derivatives using a central difference formula and smoothing the numerical derivatives using a zero phase filter.

20. The method of claim 13 wherein the steps are performed in real time during startup of the turbine engine.