# US 2014/0190176 A1 · Fuel control method and fuel control apparatus for gas turbine and gas turbine

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- Number: US 2014/0190176 A1
- Document ID: US20140190176A1
- Status: Published application
- Kind: A1
- Application number: 14/203,414
- Filed: 2014-03-10
- Published: 2014-07-10
- Earliest claimed: 2008-10-01
- Assignees: Mitsubishi Heavy Industries, Ltd.
- Applicants: Mitsubishi Heavy Industries, Ltd.
- Inventors: Sosuke NAKAMURA; Satoshi TANIMURA; Shinji AKAMATSU; Shinsuke NAKAMURA; Takashi SONODA; Akihiko SAITO; Makoto KISHI
- Web page: https://patentgrep.com/patent/US20140190176A1

## CPC

- F02C 9/26: Control of fuel supply (F02C9/48 takes precedence; fuel valves F02C7/232)
- F02C 9/34: Joint control of separate flows to main and auxiliary burners
- F23K 5/005: {from a central source to a plurality of burners}
- F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)}
- F23R 3/36: Supply of different fuels
- F05D 2270/082: with as little NOx as possible
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F23K: FEEDING FUEL TO COMBUSTION APPARATUS (fuel feeders specially adapted for fluidised bed combustion apparatus F23C10/22)
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced. Because fuel is supplied from the main nozzles of all groups and burned in the entire area of the combustor upon ignition, it is possible to easily propagate a flame to all the other adjacent main nozzle groups, thereby improving the ignition characteristics of the whole gas turbine.

## Claims

### Claim at position 1

1-5. (canceled)

### Claim 6

A fuel control method for a gas turbine being formed of at least two groups of pluralities of main nozzles for supplying fuel, the fuel control method for a gas turbine comprising:
during ignition and acceleration but before loading of the gas turbine, supplying fuel from the main nozzles of all groups upon ignition of the combustor but before loading of the gas turbine, and after the ignition of the combustor, while keeping supply of the fuel from the main nozzles of at least one group excluding all groups, stopping supply of the fuel from the main nozzles of other group(s) during acceleration of the gas turbine.

### Claim 7 (depends on 6)

The fuel control method for a gas turbine according to claim 6, wherein the main nozzles of the group that supply fuel during acceleration of the gas turbine are adjacently arranged to each other.

### Claim 8 (depends on 6)

The fuel control method for a gas turbine according to claim 6, wherein number of the main nozzles of a group that supply fuel during acceleration of the gas turbine is less than a half of total number of the main nozzles.