COMBUSTION ASSEMBLY

Abstract

A combustion assembly for a gas turbine includes a flame tube and a fuel supply including a flow rate limiter supplying an injector. The flow rate limiter and the fuel injector are formed in one piece.

Claims

1. A combustion assembly for a gas turbine comprising a flame tube and a fuel supply including a flow rate limiter supplying an injector, wherein the flow rate limiter and the fuel injector are formed in one piece, and wherein the flow rate limiter comprises a first fuel conduit and a second fuel conduit each comprising a succession of chambers which are interconnected by reduced section portions, the first conduit and the second conduit being connected to a fuel inlet, the first conduit opening downstream into a first channel of the fuel injector and the second conduit opening downstream into a second channel of the injector.

2. The assembly according to claim 1, wherein the fuel injector has a substantially L-shape, a first branch of which includes the first channel including an upstream end which is connected to the first conduit of the flow rate limiter and a downstream end which opens into a first fuel outlet end piece, and a second branch of which includes a second fuel outlet end piece which is connected to a downstream end of the second channel which extends in the first branch and in the second branch.

3. The assembly according to claim 1, wherein at least one air inlet is formed at the junction of the injector and the flow rate limiter.

4. A turbomachine comprising an assembly according to claim 1.

5. A method for manufacturing an assembly according to claim 1, comprising the step of making the flow rate limiter and the fuel injector by additive manufacturing.

6. The method according to claim 5, wherein the additive manufacturing is of the laser powder fusion type.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Other features, details and advantages will appear on reading the detailed description below, and on analysing the appended drawings, in which:

[0014] FIG. 1 is a schematic perspective view of a combustion assembly according to the invention.

[0015] FIG. 2 is a schematic perspective representation of fuel supply means according to the invention;

[0016] FIG. 3 is a schematic perspective representation with a cut-out of the part of FIG. 2;

[0017] FIG. 4 is a schematic sectional view of the fuel injector.

DESCRIPTION OF THE EMBODIMENTS

[0018] The drawings and the description below contain, essentially, elements of a certain character. They may therefore not only be used to better understand this disclosure, but also contribute to its definition, where appropriate.

[0019] FIG. 1 represents a casing 10 and a combustion assembly 12 according to the present disclosure which is supported by the casing 10. As shown in FIG. 1, the combustion assembly 12 comprises a flame tube 14 inside which fuel supply means open. The flame tube 14 comprises an inner annular shroud (not visible) and an outer annular shroud 16. These fuel supply means comprise a flow rate limiter 18 supplying fuel to a fuel injector 19. More specifically, the flow rate limiter 18 comprises a base 20 or a radially outer plate which is fastened on the outer face of a boss 22 of the casing 10 in order to ensure a positioning reference of the flow rate limiter 18 on the casing 10. The fuel injector 19 has a substantially L-shape formed by a first branch 19a and a second branch 19b which are connected to each other.

[0020] As shown in FIGS. 2 to 4, the injector 19 which is herein a fuel pre-vaporisation pipe therefore comprises a first branch 19a inside which a first channel 24 of flow of an air/fuel mixture, which exits at the downstream end of the first channel 24 via a first end piece 26, is formed. A second channel 28 extends into the first branch 19a and into the second branch 19b and opens at the downstream end thereof into a second end piece 30. The first channel 24 is supplied with fuel by a first conduit 32 of the flow rate limiter and the second channel 28 is supplied with fuel by a second channel 34 of the flow rate limiter 18.

[0021] The flow rate limiter 18 thus comprises the first fuel conduit 32 and the second fuel conduit 34 which are separate from each other. These two fuel conduits 32, 34 are supplied by a common fuel source, but comprise distinct fuel outlets. The first conduit 32 opens at the outlet facing the upstream end of the first channel 24 of the injector 19. The second conduit 28 opens at the outlet facing the upstream end of the second channel 28 of the injector 19. The first conduit 32 and the second conduit 34 each comprise a succession of chambers interconnected by reduced section portions.

[0022] As shown in FIG. 3, the first conduit 32 and the second conduit 34 extend in one plane and in the example represented in the same plane. This arrangement called “flat” arrangement allows an integration of the first 32 and second 34 conduits into an already existing flange for fastening the injector, without addition of space requirement and weight.

[0023] As shown in FIG. 1 and in FIG. 2, an air inlet 36 is provided at the junction of the fuel injector 19 and the fuel limiter 18. This air inlet 36 is arranged in the annular space formed between the casing 10 and the outer shroud 16.

[0024] According to the present disclosure, the injector 19 and the limiter 18 are manufactured in one piece, for example by additive manufacturing. In particular, it is possible to consider manufacturing this part by laser powder fusion.