US 2017/0370591 A1Published application

Turbine engine combustion assembly

AssigneeSafran Helicopter Engines

InventorsLorenzo Huacan HERNANDEZ, Nicolas SAVARY

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Abstract

The invention relates to a turbine engine combustion assembly (20), which includes: an annular flame tube (21) including a front wall (23), a rear wall (24) and a bottom (22) arranged facing an engine shaft (30); an injection wheel (41) rotated by said engine shaft (30), partially projecting into the bottom (22) of the flame tube (21) and configured such as to spray fuel into the flame tube by centrifugation; and at least one injector (35), capable of depositing a film of fuel on said injection wheel (41), said combustion assembly being characterised in that said injector (35) is arranged so as to pass through said upstream area of the front wall (23) or the rear wall (24) of the flame tube (21), so that the injection opening thereof (37) opens into said tube (21), opposite the portion (43) of said injection wheel (41) which is located inside said flame tube (21).

Claims9

Dependent claims

A turbine engine combustion assembly comprising:

an annular flame tube, comprising a front wall equipped with an upstream zone oriented upstream of the combustion assembly, a rear wall provided with an upstream zone oriented upstream of the combustion assembly and a bottom positioned opposite an engine shaft,
an injection wheel driven in rotation by said engine shaft coaxial with the longitudinal axis X-X′ of the combustion assembly, said injection wheel protruding partially into the flame tube through its bottom and being configured to centrifugally atomize fuel in the flame tube,
at least one injector capable of depositing a film of fuel on said injection wheel,
this combustion assembly being characterized in that said injector is positioned through said upstream zone of the front wall or through said upstream zone of the rear wall of the flame tube and in such a manner that its injection opening leads inside this tube opposite the portion of said injection wheel which is located in said flame tube.

1 more element

Dependencies are inferred from the claim text.

Facts

Application: 15/543,563Filed 12 Jan 2016
Priority: FR 155031415 Jan 2015
Published: 28 Dec 2017
Term ends: Not estimatedThe source records don’t support an estimate.

Classification6 codes

F23R 3/38
Characterised by the fuel supply: comprising rotary fuel injection means
F23D 11/04
Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space: the spraying action being obtained by…
F23R 3/46
Characterised by the arrangement or form of the flame tubes or combustion chambers: combustion chambers comprising an annular arrangement of…
F23R 3/52
Characterised by the arrangement or form of the flame tubes or combustion chambers: toroidal combustion chambers