Flame monitoring of a gas turbine combustor using multiple dynamic pressure sensors in multiple combustors

Patent metadata

Field	Value
Publication number	US-9612016-B2
Application number	US-201414513373-A
Country	US
Kind code	B2
Filing date	Oct 14, 2014
Priority date	Apr 12, 2013
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

The state of a flame in a subject combustor of a gas turbine engine is acoustically monitored using a dynamic pressure sensor within the subject combustor and one or more additional sensors in nearby combustors. Dynamic pressure sensor output signals from the sensors are cross correlated to identify acoustic oscillations generated by a flame in the subject combustor and received by the sensors. The cross correlation may be constrained by a maximum time delay between correlated components of the signals, based on physical characteristics.

First claim

What is claimed is:

1. A flame monitoring method for a plurality of gas turbine engine combustors arranged for combusting fuel in a gas turbine engine, comprising:
receiving a first dynamic sensor output signal from a first acoustic sensor positioned in a first gas turbine engine combustor, the first dynamic sensor output signal containing components indicative of first acoustic oscillations generated by a first flame within the first gas turbine engine combustor;
receiving a second dynamic sensor output signal from a second acoustic sensor positioned in a second gas turbine engine combustor, the second dynamic sensor output signal containing components indicative of second acoustic oscillations generated by the first flame within the first gas turbine engine combustor and propagated to the second acoustic sensor positioned in the second gas turbine engine combustor;
performing a cross-correlation operation on the first and second dynamic sensor output signals to determine a cross-correlation value between the first and second acoustic oscillations, the cross-correlation operation being constrained by a maximum time delay between correlated components of the first and second acoustic oscillations; and
based on the cross-correlation value, determining whether the first flame is present within the first gas turbine engine combustor.

2. The flame monitoring method of claim 1 , further comprising:
filtering the first and second dynamic sensor output signals to exclude frequencies outside an expected frequency range emitted by the first flame within the first gas turbine engine combustor.

3. The flame monitoring method of claim 1 , wherein the maximum time delay is based on a physical geometry of the gas turbine engine combustors and a maximum expected speed of sound in the gas turbine engine combustors.

4. The flame monitoring method of claim 1 , further comprising:
receiving a third dynamic sensor output signal from the first acoustic sensor positioned in the first gas turbine engine combustor, the third dynamic sensor output signal containing components indicative of third acoustic oscillations generated by a second flame within the second gas turbine engine combustor and propagated to the first acoustic sensor positioned in the first gas turbine engine combustor;
receiving a fourth dynamic sensor output signal from the second acoustic sensor positioned in the second gas turbine engine combustor, the fourth dynamic sensor output signal containing components indicative of fourth acoustic oscillations generated by the second flame within the second gas turbine engine combustor;
performing a cross-correlation operation on the third and fourth dynamic sensor output signals to determine a cross-correlation value between the third and fourth acoustic oscillations, the cross-correlation operation being constrained by a maximum time delay between correlated components of the third and fourth acoustic oscillations; and
based on the cross-correlation value, determining whether the second flame is present within the second gas turbine engine combustor.

5. The flame monitoring method of claim 4 , wherein a duration of an autocorrelation of the first dynamic sensor output signal is sufficiently narrow to permit distinguishing the signal components indicative of the first acoustic oscillations from the signal components indicative of the third acoustic oscillations.

6. The flame monitoring method of claim 1 , wherein receiving the first and second dynamic pressure sensor output signals from the first and second acoustic sensors further comprises:
receiving data blocks of 1 second or less in length.

7. The flame monitoring method of claim 1 , wherein performing a cross-correlation operation on the dynamic pressure sensor output signals further comprises:
computing representations of oscillations in the output signals; and
weighting the representations with the cross-correlation values.

8. The flame monitoring method of claim 1 , wherein determining whether the first flame is present further comprises determining whether the cross-correlation value meets a predetermined criterion.

9. The flame monitoring method of claim 8 , wherein the predetermined criterion is selected from a group consisting of a threshold value, a steepness in drop of cross-correlation over time and a difference from cross-correlation between other combustors.

10. The flame monitoring method of claim 1 , further comprising:
making a determination that the first acoustic oscillations generated by the first flame reach the first acoustic sensor before the second acoustic oscillations generated by the first flame reach the second acoustic sensor; and
based on the determination, determining that the second acoustic oscillations are generated by the first flame.

11. A system for monitoring flames in a plurality of gas turbine engine combustors arranged for combusting fuel in a gas turbine engine combustor, comprising:
a first acoustic sensor positioned for measuring acoustic oscillations within a first combustor of the gas turbine engine combustor;
a second acoustic sensor positioned for measuring acoustic oscillations within a second combustor of the gas turbine engine combustor;
a processor connected for receiving dynamic pressure sensor output signals from the first and second acoustic sensors;
computer readable media containing computer readable instructions that, when executed by the processor, cause the processor to perform the following operations:
receiving a first dynamic sensor output signal from the first acoustic sensor positioned within the first combustor, the first dynamic sensor output signal containing components indicative of first acoustic oscillations generated by a first flame within the first combustor;
receiving a second dynamic sensor output signal from the second acoustic sensor positioned within the second combustor, the second dynamic sensor output signal containing components indicative of second acoustic oscillations generated by the first flame within the first combustor and propagated to the second acoustic sensor positioned in the second combustor;
performing a cross-correlation operation on the first and second dynamic sensor output signals to determine a cross-correlation value between the first and second acoustic oscillations, the cross-correlation operation being constrained by a maximum time delay between correlated components of the first and second acoustic oscillations; and
based on the cross-correlation value, determining whether the first flame is present within the first combustor.

12. The system of claim 11 , wherein the operations further comprise:
filtering the first and second dynamic sensor output signals to exclude frequencies outside an expected frequency range emitted by the first flame within the first combustor.

13. The system of claim 11 , wherein the maximum time delay is based on a physical geometry of the gas turbine engine combustors and a maximum expected speed of sound in the gas turbine engine combustors.

14. The system of claim 11 , wherein the operations further comprise:
receiving a third dynamic sensor output signal from the first acoustic sensor positioned in the first combustor, the third dynamic sensor output signal containing components indicative of third acoustic oscillations generated by a second flame within the second combustor and propagated to the first acoustic sensor positioned in the first combustor;
receiving a fourth dynamic sensor output signal from the second acoustic sensor positioned in the second combustor, the fourth dynamic sensor output signal containing components indicativ

Assignees

• Siemens Energy Inc

Inventors

• Claussen Heiko
• Ulerich Nancy H
• Momin Zainul
• Flohr Patrick Ronald

Classifications

• F23N2229/16

  using two or more of the same types of flame sensor · CPC title

• F23N2241/20

  Gas turbines · CPC title

• F23N2231/06

  for flame failures · CPC title

• F23N2225/04

  pressure · CPC title

• G01M15/14

  Testing gas-turbine engines or jet-propulsion engines · CPC title