Method of operating a multi-stage flamesheet combustor

Patent metadata

Field	Value
Publication number	US-10378456-B2
Application number	US-201514956048-A
Country	US
Kind code	B2
Filing date	Dec 1, 2015
Priority date	Oct 1, 2012
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels.

First claim

What is claimed is:

1. A computerized method, implemented by a processing unit, for staging fuel in a gas turbine combustor where the gas turbine combustor has a pilot fuel nozzle, a set of pilot tune stage injectors for tuning the pilot fuel nozzle and a main set of fuel injectors, the method comprising the steps of:
operating the combustor in a first mode in which the fuel is injected into the combustor by the pilot fuel nozzle until a first temperature is detected;
upon detecting the first temperature, operating the combustor in a second mode in which the fuel is injected into the combustor by the pilot fuel nozzle and the set of pilot tune stage injectors until a second temperature is detected;
upon detecting the second temperature, operating the combustor in a third mode in which the fuel is injected into the combustor by the pilot fuel nozzle, the set of pilot tune stage injectors, and a first portion of the main set of fuel injectors until a third temperature is detected; and
upon detecting the third temperature, operating the combustor in a fourth mode in which the fuel is injected into the combustor by the pilot fuel nozzle, set of pilot tune stage injectors, the first portion of the main set of fuel injectors and a second portion of the main set of fuel injectors.

2. The computerized method of claim 1 , wherein the third mode comprises two sub-modes, Mode 3 ′ and Mode 3 ″.

3. The computerized method of claim 1 , wherein the first mode is bypassed and the method begins by operating the combustor in a second mode in which the fuel is injected into the combustor by the pilot fuel nozzle and the set of pilot tune stage injectors until a second temperature is detected.

4. The computerized method of claim 1 , wherein the first portion of the main set of fuel injectors extend across an arc-like span of approximately 120 degrees and the second portion of the main set of fuel injectors extend across an arc-like span of approximately 240 degrees.

5. The computerized method of claim 1 , wherein the first mode provides a pilot flame to the gas turbine combustor.

6. The computerized method of claim 5 , wherein the fuel injected by the set of pilot tune stage injectors provides an additional fuel source for modulating and supporting the pilot flame.

7. The computerized method of claim 6 , wherein the gas turbine combustor further includes a torch configured to provide additional fuel to supplement the fuel injected by the pilot fuel nozzle and the set of pilot tune stage injectors for modulating and supporting the pilot flame.

8. The computerized method of claim 1 , wherein the fuel injected by the third mode and fourth mode is injected in an axially upstream direction and undergoes a reversal of direction prior to ignition.

9. The computerized method of claim 1 , wherein the fuel flow to the pilot fuel nozzle and the injectors of the pilot tune stage is adjustable after operating the combustor in the fourth mode.

10. A method of operating a gas turbine combustor comprising:
supplying fuel to a pilot fuel nozzle of the gas turbine engine and to a set of pilot tune stage injectors until a second temperature is detected, wherein the set of pilot tune stage injectors are positioned radially outward of the pilot fuel nozzle;
upon detecting the second temperature, supplying the fuel to a first portion of a set of main fuel injectors, the pilot fuel nozzle, and the set of pilot tune stage injectors until a third temperature is detected; and
upon detecting the third temperature, supplying the fuel to a second portion of the set of main fuel injectors, the first portion of the set of main injectors, the pilot fuel nozzle and the set of pilot tune stage injectors.

11. The method of claim 10 further comprising:
supplying the fuel to the pilot fuel nozzle of the gas turbine combustor until a first temperature is detected,
wherein the supplying fuel to a pilot fuel nozzle of the gas turbine engine and to a set of pilot tune stage injectors until a second temperature is detected is not commenced until the first temperature is detected.

12. The method of claim 11 , wherein the gas turbine combustor transitions from a first operating mode to a second operating mode at the first temperature.

13. The method of claim 12 , wherein the gas turbine combustor transitions from a second operating mode to a third operating mode at the second temperature.

14. The method of claim 13 , wherein the gas turbine combustor transitions from a third operating mode to a fourth operating mode at the third temperature.

15. The method of claim 14 , wherein the upon detecting the second temperature, supplying the fuel to a first portion of a set of main fuel injectors, the pilot fuel nozzle, and the set of pilot tune stage injectors until a third temperature further comprises:
upon anchoring a Main 1 flame, turning down the supply of fuel to at least one of the pilot fuel nozzle and the set of pilot tune stage injectors.

16. The method of claim 10 , wherein at least one of the first temperature, the second temperature, or the third temperature is a firing temperature of the gas turbine combustor at the pilot fuel nozzle.

17. The method of claim 10 , further comprising:
coupling a first turbine stage to the gas turbine combustor,
wherein at least one of the first temperature, the second temperature, or the third temperature is a turbine inlet temperature of the combustion gases at the first turbine stage.

18. The method of claim 10 , wherein at least one of the first temperature, the second temperature, or the third temperature is an exhaust temperature of a gas turbine engine to which the gas turbine combustor is coupled.

19. The method of claim 10 , wherein the set of main fuel injectors are positioned radially outward of the pilot fuel nozzle and the set of pilot tune stage injectors.

20. The method of claim 10 , wherein the gas turbine combustor further comprises a torch configured to provide additional fuel to supplement the fuel injected by the pilot fuel nozzle and the set of pilot tune stage injectors for modulating and supporting the pilot flame.

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Stuttaford Peter John
• Oumejjoud Khalid
• Hernandez Fred
• Rizkalla Hany
• Hui Timothy
• Yaquinto Matthew
• Sewell Jesse

Classifications

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F02C9/28 Primary

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title

• F05D2270/31

  Fuel schedule for stage combustors · CPC title

• F05D2270/304

  Spool rotational speed · CPC title

• F05D2270/091

  in particular sudden load loss · CPC title