System and method of control for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016010493-A1
Application number	US-201514599750-A
Country	US
Kind code	A1
Filing date	Jan 19, 2015
Priority date	Jan 21, 2014
Publication date	Jan 14, 2016
Grant date	—

Abstract

A system includes plurality of combustors and a distributed flow measurement system coupled to the plurality of combustors. Each combustor of the plurality of combustors includes one or more oxidant passages and one or more fuel passages. The distributed flow measurement system is configured to measure an oxidant flow rate for a respective oxidant passage of the one or more oxidant passages of the respective combustor based at least in part on an oxidant pressure drop along the respective oxidant passage, and the distributed flow measurement system is configured to measure a fuel flow rate for a respective fuel passage of the one or more fuel passages of the respective combustor based at least in part on a fuel pressure drop along the respective fuel passage.

First claim

1 . A system comprising:
a first combustor, comprising:
a plurality of first oxidant passages configured to supply a first oxidant flow to the first combustor;
a plurality of first fuel passages configured to supply a first fuel flow to the first combustor;
a plurality of first oxidant pressure sensors, wherein each first oxidant pressure sensor of the plurality of first oxidant pressure sensors is fluidly coupled to a respective first oxidant passage of the plurality of first oxidant passages and is configured to transmit a respective first oxidant pressure signal; and
a plurality of first fuel pressure sensors, wherein each first fuel pressure sensor of the plurality of first fuel pressure sensors is fluidly coupled to a respective first fuel passage of the plurality of first fuel passages and is configured to transmit a respective first fuel pressure signal; and
a controller coupled to the plurality of first oxidant pressure sensors and to the plurality of first fuel pressure sensors, wherein the controller is configured to determine a first oxidant flow rate through each first oxidant passage of the plurality of first oxidant passages based at least in part on the respective first oxidant pressure signal and a first reference oxidant pressure, and the controller is configured to determine a first fuel flow rate through each first fuel passage of the plurality of first fuel passages based at least in part on the respective first fuel pressure signal and a first reference fuel pressure.

2 . The system of claim 1 , wherein the first combustor comprises an annular combustor.

3 . The system of claim 1 , comprising a second combustor, comprising:
a plurality of second oxidant passages configured to supply a second oxidant flow to the second combustor; a plurality of second fuel passages configured to supply a second fuel flow to the second combustor; a plurality of second oxidant pressure sensors, wherein each second oxidant pressure sensor of the plurality of second oxidant pressure sensors is fluidly coupled to a respective second oxidant passage of the plurality of second oxidant passages and is configured to transmit a respective second oxidant pressure signal; and an plurality of second fuel pressure sensors, wherein each second fuel pressure sensor of the plurality of second fuel pressure sensors is fluidly coupled to a respective second fuel passage of the plurality of second fuel passages and is configured to transmit a respective second fuel pressure signal; wherein the controller is configured to determine a second oxidant flow rate through each second oxidant passage of the plurality of second oxidant passages based at least in part on the respective second oxidant pressure signal and a second reference oxidant pressure, and the controller is configured to determine a second fuel flow rate through each second fuel passage of the plurality of second fuel passages based at least in part on the respective second fuel pressure signal and a second reference fuel pressure.

4 . The system of claim 1 , wherein the first combustor comprises a plurality of first fuel nozzles, the plurality of first fuel nozzles comprises the respective plurality of first fuel passages, and the plurality of first fuel nozzles comprises pre-mix nozzles, diffusion nozzles, or any combination thereof.

5 . The system of claim 1 , wherein the first reference oxidant pressure is based at least in part on a pressure of an oxidant supply system fluidly coupled to the plurality of first oxidant passages, and the first reference fuel pressure is based at least in part on a pressure of a fuel supply fluidly coupled to the plurality of first fuel passages.

6 . The system of claim 1 , wherein the first reference oxidant pressure is the first fuel pressure, and the first reference oxidant pressure is based at least in part on a pressure of an oxidant supply system fluidly coupled to the plurality of first oxidant passages, a fuel supply fluidly coupled to the plurality of first fuel passages, a head end pressure, a combustor liner pressure, or a combustion chamber pressure, or any combination thereof.

7 . The system of claim 1 , wherein the controller is configured to control the first fuel flow to the first combustor based at least in part on the determined first oxidant flow rate and the determined first fuel flow rate to the first combustor.

8 . The system of claim 1 , wherein the controller is configured to control the first oxidant flow to the first combustor based at least in part on the determined first oxidant flow rate and the determined first fuel flow rate to the first combustor.

9 . The system of claim 1 , comprising a lambda sensor configured to measure an oxidant concentration in an exhaust gas from the first combustor, wherein the controller is configured to control at least one of the first fuel flow or the first oxidant flow to the first combustor based at least in part on the measured oxidant concentration, the determined first fuel flow rate, and the determined first oxidant flow rate.

10 . The system of claim 1 , comprising a gas turbine engine having the first combustor, wherein the controller is configured to control the first oxidant flow and the first fuel flow based at least in part on a target equivalence ratio between 0.95 and 1.05.

11 . The system of claim 10 , wherein the gas turbine engine comprises a stoichiometric exhaust gas recirculation (SEGR) gas turbine engine.

12 . A system comprising:
a plurality of combustors, wherein each combustor comprises one or more oxidant passages and one or more fuel passages; and a distributed flow measurement system coupled to the plurality of combustors, wherein the distributed flow measurement system is configured to measure an oxidant flow rate for a respective oxidant passage of the one or more oxidant passages of the respective combustor based at least in part on an oxidant pressure drop along the respective oxidant passage, and the distributed flow measurement system is configured to measure a fuel flow rate for a respective fuel passage of the one or more fuel passages of the respective combustor based at least in part on a fuel pressure drop along the respective fuel passage.

13 . The system of claim 12 , wherein each combustor of the plurality of combustors comprises:
a fuel manifold fluidly coupled to the one or more fuel passages of the respective combustor via one or more fuel valves or a multiple port fuel scanning valve; a fuel manifold pressure sensor coupled to the fuel manifold, wherein the fuel manifold pressure sensor is configured to sense a respective fuel pressure of the one or more fuel passages; an oxidant manifold fluidly coupled to the one or more oxidant passages of the respective combustor via one or more oxidant valves or a multiple port oxidant scanning valve; and an oxidant manifold pressure sensor coupled to the oxidant manifold, wherein the oxidant manifold pressure sensor is configured to sense a respective oxidant pressure of the one or more oxidant passages.

14 . The system of claim 12 , wherein the distributed flow measurement system comprises:
a plurality of oxidant pressure sensors, wherein each oxidant pressure sensor of the plurality of oxidant pressure sensors is coupled to a corresponding oxidant passage of the one or more oxidant passages of each combustor of the plurality of combustors; and a plurality of fuel pressure sensors, wherein each fuel pressure sensor of the plurality of fuel pressure sensors is coupled to a corresponding fuel passage of the one or more fuel passages of each combustor of the plurality of combustors.

Assignees

• Gen Electric
• Exxonmobil Upstream Res Co

Inventors

• O'Dea Dennis M
• Minto Karl Dean
• Huntington Richard A
• Dhanuka Sulabh K
• Mittricker Franklin F

Classifications

• F23N2241/20

  Gas turbines · CPC title

• F23N2225/06

  for determining flow · CPC title

• Y02E20/16

  Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT] · CPC title

• F01D21/003 Primary

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

• F23C9/00

  Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber (fluidised bed combustion apparatus with means for recirculation of particles entrained from the bed F23C10/02; fluidised bed combustion apparatus with devices for removal and partial reintroduction of material from the bed F23C10/26) · CPC title