# US 2019/0170357 A1 · Improved injectors for gas turbine combustion chamber

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- Number: US 2019/0170357 A1
- Document ID: US20190170357A1
- Status: Published application
- Kind: A1
- Application number: 16/092,694
- Filed: 2017-04-06
- Published: 2019-06-06
- Earliest claimed: 2016-04-13
- Assignees: Safran Helicopter Engines
- Applicants: Safran Helicopter Engines
- Inventors: Guillaume TALIERCIO; Nicolas SAVARY; Olivier LAMAISON
- Web page: https://patentgrep.com/patent/US20190170357A1

## CPC

- F23R 3/34: Feeding into different combustion zones
- F02C 7/228: Dividing fuel between various burners
- F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances}
- F23R 3/56: Combustion chambers having rotary flame tubes
- 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)

## Abstract

An injector for a gas turbine combustion chamber, includes a fluid feed system; an injector body extending along a longitudinal axis; an injection head arranged on the injector body and configured to spray the fluid in a direction that is inclined relative to the longitudinal axis; and an actuator configured to turn the injector selectively about the longitudinal axis so as to vary the direction in which the fluid is sprayed; wherein the actuator is configured to enable the orientation of the injector to be varied by turning about the longitudinal axis through an amplitude less than or equal to 90°.

## Claims

### Claim 1

An injector for a gas turbine combustion chamber, the injector comprising:
a fluid feed system;
an injector body extending along a longitudinal axis;
an injection head arranged on the injector body and configured to spray said fluid in a direction that is inclined relative to the longitudinal axis; and
an actuator configured to turn the injector selectively about the longitudinal axis so as to vary the direction in which the fluid is sprayed;
wherein the actuator is configured to enable the orientation of the injector to be varied by turning about the longitudinal axis through an amplitude less than or equal to 90°.

### Claim 2 (depends on 1)

An injector according to claim 1, wherein said fluid feed system includes a flexible feed line or a rigid feed line having a leaktight hinge connecting it to the injector.

### Claim 3 (depends on 1)

A combustion chamber including at least one injector according to claim 1.

### Claim 4 (depends on 3)

A combustion chamber according to claim 3, wherein said combustion chamber is a gyratory technology combustion chamber, and wherein said at least one injector is arranged in a sleeve outside the combustion chamber.

### Claim 5 (depends on 3)

A combustion chamber according to claim 3, wherein said actuator comprises a control system configured to vary the orientation of the injector as a function of a pressure bypassing the combustion chamber and/or a fuel pressure.

### Claim 6 (depends on 3)

A turbine engine including a combustion chamber according to claim 3.

### Claim 7 (depends on 6)

An aircraft including a turbine engine according to claim 6.

### Claim 8 (depends on 2)

A combustion chamber including at least one injector according to claim 2.