Combustion system for a gas turbine engine

• US 4,557,106 A
• Filed: 10/26/1984
• Issued: 12/10/1985
• Est. Priority Date: 11/02/1983
• Status: Expired due to Term

• Current Assignee: John E. Ffowcs Williams, Maria A. Heckl, Philip J. Dines
• Original Assignee: John E. Ffowcs Williams, Maria A. Heckl, Philip J. Dines
• Inventors: Dines, Philip J., Ffowcs Williams, John E., Heckl, Maria A.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US06/665,154
• Time in Patent Office: 410 Days
• Field of Search: 60/39.281, 60/261, 60/725, 181/206, 181/207, 181/213, 181/220, 181/221
• US Class Current: 60/39.281
• CPC Class Codes: F02C 9/34 Joint control of separate flows to main and auxiliary burners
• CPC Class Codes: F02K 3/10 by after-burners F02K3/105 takes precedence
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2260/962 by means of "anti-noise"
• CPC Class Codes: F05D 2270/14 to control thermoacoustic behaviour in the combustion chambers counteracting noise or vibration F05D2260/96
• CPC Class Codes: F23M 20/005 Noise absorbing means
• CPC Class Codes: F23N 5/16 using noise-sensitive detectors
• CPC Class Codes: F23R 2900/00013 Reducing thermo-acoustic vibrations by active means
• CPC Class Codes: F23R 2900/00014 Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators silence apparatus using resonance F01N1/023
• CPC Class Codes: F23R 3/28 characterised by the fuel supply burners F23D
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A combustion system for gas turbine engines incorporates a feedback loop which provides positive damping for the control of unstable combustion, particularly buzz in reheat systems, but also at least some cases of combustion rumble in main combustion systems. The feedback loop includes a sensor, a control unit and an exciter. The control unit monitors the strength of the sensor signal, which senses a cyclically varying parameter of the unstable combustion process, and adaptively varies the amount by which the signal is phase-shifted and amplified in order to obtain a sensor signal of minimum strength, this being achieved by controlling the exciter in accordance with the phase-shifted amplified signal to change the boundary conditions of the combustion process and thereby eliminate the unstable combustion.

Claims

1. A combustion system for a gas turbine engine, the combustion system incorporating a feedback loop for the control of an unstable combustion process in the combustion system, the feedback loop including:

sensor means for sensing a cyclically varying parameter of the unstable combustion process and producing a signal corresponding thereto;

control means for phase-shifting and amplifying the signal from the sensor means; and

exciter means for changing the boundary conditions of the combustion process in accordance with the phase-shifted amplified signal;

said control means including adaptive means for monitoring the strength of the sensor signal and varying the amount by which the signal is phase-shifted and amplified to obtain a sensor signal of minimum strength, whereby said unstable combustion is substantially eliminated.

2. A combustion system according to claim 1 in which the control means comprises:

low pass filter means adapted to pass a predetermined range of frequencies of the cyclically varying parameter of the unstable combustion process;

variable phase shifter means for phase-shifting the signal from the sensor means by a variable amount;

a variable gain amplifier for amplifying the phase-shifted signal by a variable amount; and

a supervisory unit for monitoring the strength of the signal from the low pass filter and altering the gain of the variable gain amplifier and the phase change produced by the variable phase shifter until the signal from the low pass filter is at a minimum.

3. A combustion system according to claim 1 in which the sensor means comprises vibration transducer means arranged to detect vibration in the combustion system due to the unstable process.

4. A combustion system according to claim 1 in which the sensor means comprises pressure transducer means arranged to detect pressure fluctuations in the combustion system due to the unstable combustion process.

5. A combustion system according to claim 4 in which the pressure transducer means is a microphone arranged to detect fluctuations in sound pressure level.

6. A combustion system according to claim 1 in which the sensor means comprises opto-electronic transducer means arranged to detect variable light emissions from the unstable combustion process.

7. A combustion system according to claim 1 in which the exciter means comprises means for modulating the flow of a fluid participating in the combustion process.

8. A combustion system according to claim 1 in which the exciter means comprises means for producing pressure fluctuations in a fluid participating in the combustion process.

9. A combustion system according to claim 1, the combustion system having fuel supply means incorporating the exciter means, the exciter means comprising a reciprocatory element adapted to superimpose pressure fluctuations on the fuel supply.

10. A combustion system according to claim 9, in which the reciprocatory element comprises an electromagnetically driven diaphrgm.

11. A combustion system according to claim 8 in which the exciter means comprises a loudspeaker for producing fluctuations in sound pressure level in and near the combustion process.

12. A combustion system according to claim 1, the combustion system being a reheat combustor system.