Fuel injection system for aircraft turbomachine, comprising a variable section air through duct

Patent metadata

Field	Value
Publication number	US-2018010799-A1
Application number	US-201615542860-A
Country	US
Kind code	A1
Filing date	Jan 20, 2016
Priority date	Jan 20, 2015
Publication date	Jan 11, 2018
Grant date	—

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 centred 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.

First claim

1 . An assembly comprising:
an injection system for an aircraft turbomachine combustion chamber as well as a fuel injector engaging with said injection system, the injection system comprising an aerodynamic bowl which is stationary with respect to the injector and comprising a first end widening toward the downstream end and centered on a central axis of the injection system, the injection system also comprising a central body along which a film of fuel is intended to flow in the downstream direction, wherein the central body comprises a second end widening toward the downstream end and centered on the central axis of the injection system, said first and second widening ends between them delimiting an air through duct, wherein the system comprises motion-inducing means allowing a relative movement between said first and second widening ends, along the central axis of the injection system, by moving the central body relative to the injector.

2 . The assembly according to claim 1 , wherein said first and second widening ends are tapered in shape and define therebetween a tapered air through duct, having a variable cross-section according to a relative axial position between said first and second widening ends.

3 . The assembly 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.

4 . The assembly 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.

5 . The assembly according to claim 1 , wherein the motion-inducing means comprise a motor.

6 . The assembly 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 this bowl.

7 . An aircraft turbomachine combustion chamber comprising:
a chamber bottom perforated with openings spaced apart from one another, the combustion chamber comprising, associated with each opening of the chamber bottom, the assembly according to claim 1 .

8 . An aircraft turbomachine comprising:
the combustion chamber according to claim 7 .

Assignees

• Safran Aircraft Engines

Inventors

• Mery Yoann
• Bidart Olivier Baptiste
• Leparoux Julien

Classifications

• F23R3/30

  comprising fuel prevapourising devices · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title

• F23N1/027

  using mechanical means · CPC title

• F23N1/025

  using electrical or electromechanical means · CPC title

• F23D2900/11101

  Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers · CPC title