# US 10,371,384 B2 · Fuel injection system for aircraft turbomachine, comprising a variable section air through duct

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- Number: US 10,371,384 B2
- Document ID: US10371384B2
- Status: Granted
- Kind: B2
- Application number: 15/542,860
- Filed: 2016-01-20
- Published: 2018-01-11
- Granted: 2019-08-06
- Earliest claimed: 2015-01-20
- Assignees: Safran Aircraft Engines
- Applicants: Safran Aircraft Engines
- Inventors: Yoann Mery; Olivier Baptiste Bidart; Julien Leparoux
- Web page: https://patentgrep.com/patent/US10371384B2

## CPC

- F23R 3/14: by using swirl vanes
- F23N 1/025: {using electrical or electromechanical means}
- F23N 1/027: {using mechanical means}
- F23R 3/28: characterised by the fuel supply (burners F23D)
- F23R 3/30: comprising fuel prevapourising devices
- F23D 2900/11101: Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers
- 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)
- F23N: REGULATING OR CONTROLLING COMBUSTION (control devices specially adapted for combustion apparatus in which combustion takes place in a fluidised bed of fuel or other particles F23C10/28; condition responsive controls for regulating combustion in domestic stoves with open fires for solid fuel F24B1/187)
- F23D: BURNERS

## Abstract

An assembly includes an injection system and an injector for an aircraft turbomachine combustion chamber. The system includes an aerodynamic bowl including a first end widening toward the downstream end and centered on a central axis of the injection system, this also including a central body along which a film of fuel is intended to flow in the downstream direction. The central body includes a second end widening toward the downstream end, the first and second widening ends between them delimiting an air through duct and the system includes motion inducing a device allowing a relative movement between the first widening end which is stationary and the second widening end, along the central axis of the injection system, by moving the central body relative to the injector.

## Claims

### Claim 1

An aircraft turbomachine comprising:
a combustion chamber including a chamber bottom perforated with openings spaced apart from one another;
an assembly associated with each opening of the chamber bottom, the assembly including an injection system for the combustion chamber and a fuel injector engaging with said injection system, the injection system comprising:
an aerodynamic bowl which is stationary with respect to the fuel injector and comprising a first widening end widening toward a downstream end thereof and centered on a central axis of the injection system,
a central body along which a film of fuel is intended to flow in the downstream direction, the central body comprising a second widening end widening toward a downstream end thereof and centered on the central axis of the injection system, said first and second widening ends delimiting therebetween an air through duct, and
an actuator which moves the central body relative to the injector so as to allow a relative movement between said first and second widening ends along the central axis of the injection system; and
a control unit configured to control the actuator in order to vary a cross-section of the air through duct based on a speed of the aircraft turbomachine.

### Claim 2 (depends on 1)

The aircraft turbomachine according to claim 1, wherein said first and second widening ends are tapered in shape.

### Claim 3 (depends on 1)

The aircraft turbomachine according to claim 1, wherein the injection system comprises an intermediate structure arranged radially between a base of the central body and a base of the aerodynamic bowl, said intermediate structure defining with the base of the central body an axial duct for the flow of the film of fuel in the direction of said second widening end of the central body.

### Claim 4 (depends on 3)

The aircraft turbomachine according to claim 3, wherein the base of the aerodynamic bowl comprises two concentric walls between which an air admission twist is arranged between the two concentric walls.

### Claim 5 (depends on 1)

The aircraft turbomachine according to claim 1, wherein the actuator includes a motor.

### Claim 6 (depends on 1)

The aircraft turbomachine according to claim 1, wherein said first widening end of the aerodynamic bowl is perforated with air admission holes in a combustion area defined by the bowl.

### Claim 7 (depends on 1)

The aircraft turbomachine according to claim 1, wherein the control unit is configured to control the actuator such that the cross-section of the air through duct when the aircraft turbomachine is in an idling mode is smaller than the cross-section of the air through duct when the aircraft turbomachine is in a full-throttle mode or a cruising mode.