Method for making measurements of the post-combustion residence time in a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9733141-B1
Application number	US-201514694235-A
Country	US
Kind code	B1
Filing date	Apr 23, 2015
Priority date	Jun 27, 2012
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

A method of measuring a residence time in a gas-turbine engine is disclosed that includes measuring a combustor pressure signal at a combustor entrance and a turbine exit pressure signal at a turbine exit. The method further includes computing a cross-spectrum function between the combustor pressure signal and the turbine exit pressure signal, calculating a slope of the cross-spectrum function, shifting the turbine exit pressure signal an amount corresponding to a time delay between the measurement of the combustor pressure signal and the turbine exit pressure signal, and recalculating the slope of the cross-spectrum function until the slope reaches zero.

First claim

What is claimed is:

1. A method of measuring a residence time in a gas-turbine engine:
measuring a combustor pressure signal at a combustor entrance and a turbine exit pressure signal at a turbine exit;
computing a cross-spectrum function between the combustor pressure signal and the turbine exit pressure signal;
calculating a slope of the cross-spectrum function;
shifting the turbine exit pressure signal an amount corresponding to a time delay between the measurement of the combustor pressure signal and the turbine exit pressure signal; and
recalculating the slope of the cross-spectrum function until the slope reaches zero.

2. The method of claim 1 , wherein prior to measuring a combustor pressure signal at a combustor entrance and a turbine exit pressure signal at a turbine exit the method further comprising placing a plurality of pressure sensors at a combustor entrance and at a turbine exit of the gas-turbine engine.

3. The method of claim 2 , wherein the plurality of pressure sensors includes a combustor pressure sensor disposed at a combustor entrance, a first turbine exit pressure sensor disposed at a first turbine exit, and a second turbine exit pressure sensor disposed at a second turbine exit.

4. The method of claim 3 further comprising computing a post-combustion residence time from the slope of the cross spectrum function.

5. The method of claim 4 , wherein prior to calculating a slope of the cross-spectrum function, the method further comprising applying a linear curve fit to the cross-spectrum function.

6. The method of claim 3 further comprising placing at least one far-field microphone at a pre-determined distance from the gas-turbine engine.

7. The method of claim 6 further comprising measuring a pressure signal at the at least one far-field microphone.

8. The method of claim 7 further comprising computing a cross-spectrum function between the combustor pressure sensor signal from the measured combustor pressure and the pressure signal measured at the at least one far-field microphone.

9. The method of claim 8 further comprising applying a linear curve fit to the cross-spectrum function and calculating a slope of the linear curve fit.

10. The method of claim 9 further comprising re-calculating the slope of the linear curve fit until the slope reaches zero.

11. A method of measuring a residence time in a gas-turbine engine:
measuring a first turbine exit pressure signal at a turbine exit and a pressure signal at a far-field microphone;
computing a cross-spectrum function between the first turbine exit pressure signal and the pressure signal measured at the at least one far-field microphone;
calculating a slope of the cross-spectrum function;
shifting the pressure from the at least one far-field microphone an amount corresponding to a time delay between the measurement of the first turbine exit pressure signal and the pressure signal measured at the at least one far-field microphone; and
recalculating the slope of the cross-spectrum function until the slope reaches zero.

12. The method of claim 11 further comprising a measuring a second turbine exit pressure signal at the turbine exit.

13. The method of claim 12 further comprising computing a cross-spectrum function between the second turbine exit pressure signal and the pressure signal measured at the at least one far-field microphone.

14. The method of claim 13 further comprising calculating a slope of the cross-spectrum function between the second turbine exit pressure signal and the pressure signal measured at the at least one far-field microphone.

15. The method of claim 14 further comprising shifting the pressure signal from the at least one far-field microphone an amount corresponding to a time delay between the measurement of the second turbine exit pressure signal and the pressure signal measured at the at least one far-field microphone.

16. The method of claim 15 further comprising recalculating the slope of the cross-spectrum function between the second turbine exit pressure signal and the pressure signal measured at the at least one far-field microphone until the slope reaches zero.

17. A system to measure a post-combustion residence time in a gas-turbine engine comprising:
a measurement component that measures combustion pressure signals, turbine exit pressure signals, and far-field pressure signals from far-field microphones;
a receiving/calculation component that calculates a plurality of cross-spectrum functions based on the measured plurality of combustion pressure signals, turbine exit pressure signals, and far-field pressure signals;
a tabulation component that tabulates a slope of a linear curve fit over a predetermined frequency range based on the calculated plurality of the cross-spectrum functions; and
a computation component that computes the post-combustion residence time in the gas-turbine engine.

18. The system of claim 17 , wherein the tabulation component shifts at least one of the turbine exit pressure signals an amount corresponding to a time delay between the measurement of at least one of the combustor pressure signals and the at least one of the turbine exit pressure signals and recalculates the slope of the cross-spectrum function between the at least one of the combustor pressure signals and the at least one of the turbine exit pressure signals until the slope reaches zero.

19. The system of claim 17 , wherein the tabulation component shifts at least one of the far-field pressure signals an amount corresponding to a time delay between the measurement of at least one of the combustor pressure signals and the at least one of the far-field pressure signals and recalculates the slope of the cross-spectrum function between the at least one of the combustor pressure signals and the at least one of the far-field pressure signals until the slope reaches zero.

20. The system of claim 17 , wherein the tabulation component shifts at least one of the far-field pressure signals an amount corresponding to a time delay between the measurement of at least one of the turbine exit pressure signals and the at least one of the far-field pressure signals and recalculates the slope of the cross-spectrum function between the at least one of the turbine exit pressure signals and the at least one of the far-field pressure signals until the slope reaches zero.

Assignees

• Nasa
• The Us Administrator Of Nat Aeronautics And Space Administration

Inventors

• Miles Jeffrey H

Classifications

• F23N2241/20

  Gas turbines · CPC title

• F23N2225/06

  for determining flow · CPC title

• G01M15/14

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

• F23N5/00

  Systems for controlling combustion (regulating fuel supply F23N1/00, regulating air supply or draught F23N3/00) · CPC title

• F01D21/003 Primary

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