Fuel injector for a turbine engine

Patent metadata

Field	Value
Publication number	US-10563586-B2
Application number	US-201415026082-A
Country	US
Kind code	B2
Filing date	Sep 24, 2014
Priority date	Oct 1, 2013
Publication date	Feb 18, 2020
Grant date	Feb 18, 2020

Abstract

A fuel injector (10) such as an injector for an annular combustion chamber of a turbine engine, comprising a downstream head (16) having a central outlet (22) and an annular peripheral outlet (24) surrounding the central outlet (22), and an injector arm (12) upstream of the head (16) comprising coaxial central channel (18) and annular channel (20), characterised in that the central channel (18) is in fluid communication with the peripheral outlet (24) and the annular channel (20) is in fluid communication with the central outlet (22).

First claim

The invention claimed is:

1. A fuel injector, comprising a downstream head having a central outlet and an annular peripheral outlet surrounding the central outlet, and art injector arm upstream of the head comprising a coaxial central channel and an annular channel, wherein the central channel is in fluid communication with the peripheral outlet and the annular channel is in fluid communication with the central outlet, with downstream ends of the central channel and the annular channel respectively communicating with at least a first duct communicating downstream with the peripheral outlet and at least a second duct communicating downstream with the central outlet, with said first and second ducts being formed in an annular body arranged at a junction of the head and the arm, a downstream end of the first duct opening into an annular channel of the head of the injector internally and externally delimited by an internal annular coaxial tip and an external annular coaxial tip, with a downstream end of the second duct opening into the internal tip, an upstream end of the internal tip being sealingly inserted into a downstream end of the annular body.

2. The injector according to claim 1 , wherein the annular body comprises an upstream central opening communicating an upstream end of the first duct with the downstream end of the central channel of the arm and a downstream central opening communicating the downstream end of the second duct with the internal tip.

3. The injector according to claim 2 , wherein the upstream end of the internal tip is sealingly inserted into a tubular passage forming the downstream central opening of the body and in that an upstream end of the external tip sealingly surrounds the downstream end of the annular body.

4. The injector according to claim 2 , wherein the upstream central opening of the body is formed by a tubular portion projecting in an upstream direction relative to a downstream annular portion of the body, with the tubular portion being sealingly fitted around or inside a downstream end of a tube forming the central channel of the arm.

5. The injector according to claim 2 , further comprising a first plurality of ducts and a second plurality of ducts alternately arranged around an axis passing through the upstream and downstream central openings of the annular body, wherein the first plurality of ducts includes the first duct, and wherein the second plurality of ducts includes the second duct.

6. The injector according to claim 5 , wherein the first plurality of ducts extends from the upstream central opening to the downstream end of the annular body, and the second plurality of ducts extends from an upstream end of the annular body to the downstream central opening.

7. The injector according to claim 6 , wherein the upstream central opening is formed by a projecting tubular portion and the downstream central opening is formed by a tubular passage of the annular body.

8. A combustion chamber of a turbine engine, comprising the injector according to claim 1 .

9. A turbine engine, comprising the combustion chamber according to claim 8 .

Assignees

• Snecma
• Safran Aircraft Engines

Inventors

• Chabaille Christophe
• Loval Sébastien

Classifications

• F23R3/34

  Feeding into different combustion zones · CPC title

• F23R3/38

  comprising rotary fuel injection means · CPC title

• F02C7/22 Primary

  Fuel supply systems · CPC title

• F23D11/38

  Nozzles; Cleaning devices therefor · CPC title

• F05D2220/32

  in gas turbines · CPC title