Apparatus and method for active control of oscillations in gas turbine combustors

• US 6,205,765 B1
• Filed: 10/06/1999
• Issued: 03/27/2001
• Est. Priority Date: 10/06/1999
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Davis, Lewis Berkley Jr., Iasillo, Robert J., Black, Stephen Hugh
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US09/413,665
• Time in Patent Office: 538 Days
• Field of Search: 60/390.6, 607/25, 607/40, 431/1, 431/114
• US Class Current: 60/773
• CPC Class Codes: F02C 7/22 Fuel supply systems
• CPC Class Codes: F05D 2260/962 by means of "anti-noise"
• 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

Abstract

An apparatus and method of applying active, closed loop control to reduce combustion driven pressure oscillation in a single or multi-chamber combustion system in an industrial gas turbine, to increase operability and life of the parts, and in such a way as to require minimal input power. The invention combines the passive control of a two stage nozzle with active control thereby to reduce the requirements on the control device. This allows selection of a control device which will have an adequate life in an industrial environment and yet require minimal input power.

Claims

1. A method of operating a gas turbine combustor in a lean premixed combustion mode, wherein the combustor has discrete fuel and air delivery systems, a fuel/air premixer zone, and a reaction zone, comprising:

supplying air from an air supply system through at least one opening into the premixer zone of the combustor, said air having a predetermined pressure upstream of said opening;

supplying fuel from a fuel supply system, including a nozzle having a fuel passage and a discharge orifice for delivering said fuel, into the premixer zone of the combustor;

reducing the pressure of said fuel upstream of said fuel discharge orifice to approximately said predetermined pressure, said air supply opening and said fuel discharge orifice having substantially the same pressure drop;

sensing at least one of pressure, temperature and velocity fluctuations in said reaction zone and generating a feedback signal; and

actuating a control device operatively coupled to said fuel passage downstream from a locus of said pressure reduction and upstream of said fuel discharge orifice to affect fuel flow therein in response to said feedback signal,

whereby pressure fluctuations in the premixer zone resulting from fuel/air concentration oscillations are substantially minimized or eliminated.

2. A method as in claim 1, wherein said control device comprises a pressure driver including a membrane for generating pressure fluctuations, a front face of said membrane being exposed to said fuel passage downstream from said locus of said pressure reduction and upstream of said fuel discharge orifice.

3. A method as in claim 2, wherein a backside of said pressure driver membrane is in flow communication with said air supply system upstream of said air supply opening so as to be maintained at said predetermined pressure.

4. A method as in claim 1, wherein said sensing step comprises sensing pressure fluctuations in said reaction zone with a microphone operatively coupled to a wall of said reaction zone.

5. A method as in claim 1, wherein said step of reducing the pressure of said fuel comprises reducing the pressure of said fuel from a pressure of about 290 psig to a pressure of about 210 psig and wherein said predetermined pressure of said air upstream of said air supply opening is about 220 psig.

6. A method as in claim 1, wherein said control device comprises a volume driver including a valve for selectively injecting a fluid into said fuel passage of said nozzle upstream of said fuel discharge orifice and downstream from said locus of said pressure reduction.

7. A method as in claim 6, wherein said volume driver comprises a valve in flow communication with said fuel supply system upstream of said locus of pressure reduction for selectively supplying fuel at high pressure to said fuel passage downstream of said locus of pressure reduction.

8. Apparatus for stabilizing combustion in a gas turbine combustor operable in a lean premixed mode, and having a premixer zone and a reaction zone, comprising:

an air supply system including an opening for delivering air into the premixer zone of the combustor and having a predetermined pressure upstream of said opening;

a nozzle including a fuel passage and a discharge orifice for delivering fuel into the premixer zone;

a pressure reducer upstream of said fuel discharge orifice for reducing the fuel pressure upstream of said fuel discharge orifice to approximately said predetermined pressure, said air supply opening and said fuel discharge orifice having substantially the same pressure drop,

a sensor operatively coupled to said reaction zone to sense at least one of pressure, temperature and velocity fluctuations in said reaction zone and to generate a feedback signal; and

a control device operatively coupled to said fuel passage of said nozzle downstream from said pressure reducer and upstream of said fuel discharge orifice to affect fuel flow in the nozzle in response to said feedback signal,

whereby pressure fluctuations in the premixer zone resulting from fuel/air concentration oscillations are substantially minimized or eliminated.

9. An apparatus according to claim 8, including a volume in said fuel passage upstream of said fuel discharge orifice, said control device being operatively coupled to said volume.

10. An apparatus according to claim 8 wherein said pressure reducer includes an orifice in said fuel passage upstream of said fuel discharge orifice, said upstream orifice affording a higher pressure drop than the pressure drop across said fuel discharge orifice, said nozzle defining a volume in said fuel passage between said upstream orifice and said fuel discharge orifice at substantially the same pressure as said predetermined pressure, said control device being operatively coupled to said volume.

11. An apparatus as in claim 8, wherein said sensor comprises a microphone operatively coupled to a wall of said reaction zone.

12. An apparatus as in claim 8, wherein said control device comprises a pressure driver having a membrane, a front side of which is exposed to said fuel passage for selectively applying a pressure pulse to said fuel passage.

13. An apparatus as in claim 12, wherein a back side of said membrane is in flow communication with said air supply system upstream of said air supply opening whereby said backside exposed to said predetermined pressure.

14. An apparatus as in claim 8, wherein said control device comprises a volume driver.

15. An apparatus as in claim 14, wherein said volume driver comprises a valve in flow communication with fuel at elevated pressure disposed upstream of said pressure reducer for selectively injecting said fuel into said fuel passage.