# US 9,435,540 B2 · Fuel injector with premix pilot nozzle

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- Number: US 9,435,540 B2
- Document ID: US9435540B2
- Status: Granted
- Kind: B2
- Application number: 14/102,846
- Filed: 2013-12-11
- Published: 2015-06-11
- Granted: 2016-09-06
- Earliest claimed: 2013-12-11
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: Jonathan Dwight Berry; Michael John Hughes; Kara Johnston Edwards
- Web page: https://patentgrep.com/patent/US9435540B2

## CPC

- F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)}
- F02C 7/222: {Fuel flow conduits, e.g. manifolds}
- F23R 3/343: {Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00)}
- F05D 2220/32: in gas turbines
- F23R 2900/03343: Pilot burners operating in premixed mode
- 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)
- 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)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

An apparatus for injecting premixed fuel and air through a center body and into the combustion zone of a gas turbine includes a fuel injector nozzle with a premix pilot nozzle having a plurality of premix passages in fluid communication with an air supply and a fuel supply that premixes air and fuel within the premix passages. The apparatus has either an active or passive fuel feed control. Fuel can be fed to the apparatus either conventionally or as a breech load circuit integrated into the oil cartridge. Fuel can be supplied passively via a fuel channel connecting the swozzle fuel plenum to the premix passages. Alternatively, fuel can be injected from the oil cartridge into the premix passages.

## Claims

### Claim 1

A fuel injector for a gas turbine engine, comprising:
a. an axially elongating peripheral wall defining an outer envelope of the injector, the wall having an interior surface defining an axially elongating interior cavity;
b. a center body disposed within the axially elongating interior cavity, the center body defined by an exterior wall, wherein the exterior wall includes an upstream end and a downstream end disposed axially opposite the upstream end, the exterior wall concentrically arranged about a longitudinal axis of the axially elongating peripheral wall, wherein the exterior wall defines a hollow axially elongating interior passage radially inward of the exterior wall through which air flows from the upstream end to the downstream end, and wherein the center body and the axially elongating peripheral wall define a primary air flow channel therebetween;
c. a fuel pipe positioned within the center body, extending axially from the upstream end to the downstream end of the center body, the fuel pipe defining a fuel passage disposed radially outward from the longitudinal axis of the axially elongating peripheral wall, the fuel pipe configured in fluid connection to a source of fuel;
d. a swozzle including a plurality of swirler vanes extending radially across the primary air flow channel, at least one of the swirler vanes including a radial air supply tube, the radial air supply tube defining an auxiliary air passage through which air from a head end volume enters the axially elongating interior passage, and at least one of the swirler vanes defining at least one fuel outlet opening configured and disposed in fluid communication with the primary air flow channel; and
e. a premix nozzle positioned at the downstream end of the center body, the premix pilot nozzle defining a circumferentially extending fuel plenum at an upstream end of the premix pilot nozzle, the fuel passage in fluid communication with the fuel plenum, the premix pilot nozzle defining a plurality of axially extending premix passages in fluid communication with the fuel plenum and defining a plurality of exit openings at a downstream end of the premix pilot nozzle, the premix pilot nozzle defining at least one fill opening at the upstream end of the premix pilot nozzle, the at least one fill opening communicating a fluid from the interior passage to the plurality of premix passages, the premix pilot nozzle defining an outlet at the downstream end of the premix pilot nozzle, and wherein the premix pilot nozzle defines an axially extending inner channel radially inward of the fuel pipe extending upstream from the outlet to the downstream end of the interior passage.

### Claim 2 (depends on 1)

The fuel injector of claim 1, wherein the center body further defines an annular fuel passage in fluid communication with the at least one fuel outlet of the swozzle.

### Claim 3 (depends on 1)

The fuel injector of claim 1, wherein the exit opening of each premix passage is arranged circumferentially around the inner channel.

### Claim 4 (depends on 1)

The fuel injector of claim 1, wherein each premix passage is arranged circumferentially around the inner channel.

### Claim 5 (depends on 1)

The fuel injector of claim 1, further comprising a plurality of radial air supply tubes, each radial air supply tube extending through the axially elongating peripheral wall and fluidly connecting with at least one of the fill openings of one of the premix passages.