Injection device for a turbine engine combustion chamber

Patent metadata

Field	Value
Publication number	US-9605594-B2
Application number	US-201213980506-A
Country	US
Kind code	B2
Filing date	Jan 25, 2012
Priority date	Jan 31, 2011
Publication date	Mar 28, 2017
Grant date	Mar 28, 2017

Abstract

A fuel injection device for an annular combustion chamber of a turbine engine, the device including a pilot circuit feeding an injector, a multipoint circuit feeding injection orifices formed in a front face of an annular chamber, and an annular ring mounted in the annular chamber and including fuel-passing orifices opening out into the injection orifices, each fuel-passing orifice formed in the annular ring including a zone of small section that is extended at least downstream or upstream by an orifice portion of increasing section.

First claim

The invention claimed is:

1. A fuel injection device for an annular combustion chamber of a turbine engine, the device comprising:
a pilot circuit continuously feeding an injector opening out into a first Venturi;
a multipoint circuit intermittently feeding injection orifices formed in a front face of an upstream annular chamber of a second Venturi that is coaxial about the first Venturi; and
an annular ring mounted in the annular chamber and including fuel-passing orifices opening out into the injection orifices,
wherein each of the fuel-passing orifices formed in the annular ring includes a zone of small cross-section extended at least downstream or upstream by a portion of increasing cross-section, and
wherein the pilot circuit includes a circuit for cooling the annular ring, and further comprising a gap interposed between a front face of the annular ring and a front face of the annular chamber for thermally protecting the front face of the annular ring.

2. A device according to claim 1 , wherein the portion of increasing cross-section increases progressively to upstream or downstream ends of the fuel-passing orifices.

3. A device according to claim 1 , wherein the zone of small cross-section is formed at an upstream or downstream end of the fuel-passing orifices.

4. A device according to claim 1 , wherein the zone of small cross-section is formed between upstream and downstream ends of the fuel-passing orifices and is extended by respective portions of section that increases going upstream and of section that increases going downstream.

5. A device according to claim 4 , wherein the zone of small cross-section is formed in a middle portion of the fuel-passing orifices.

6. A device according to claim 1 , wherein the portion of increasing cross-section has a profile that is straight or curved.

7. A device according to claim 1 , wherein the gap is in fluid communication with a portion of the cooling circuit extending over the front face of the annular ring in an immediate vicinity of the injection orifices.

8. An annular combustion chamber of a turbine engine, comprising at least one fuel injection device according to claim 1 .

9. A turbine engine, a turbojet, or a turboprop, comprising a combustion chamber according to claim 8 .

10. A device according to claim 1 , wherein the annular chamber includes a first radially inner wall and a first radially outer wall connected together by a first frustoconical downstream wall,
the annular ring includes a second radially inner wall and a second radially outer wall connected together by a second frustoconical downstream wall,
the first frustoconical downstream wall abuts the second frustoconical downstream wall, and
the injection orifices are provided in the first frustoconical downstream wall and the fuel-passing orifices are provided in the second frustoconical downstream wall.

Assignees

• Cortes Thierry
• Cameriano Laurent Bernard
• Snecma

Inventors

• Cortes Thierry
• Cameriano Laurent Bernard

Classifications

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F02C7/22 Primary

  Fuel supply systems · CPC title

• F23D11/24 Primary

  by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space · CPC title

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23D11/38

  Nozzles; Cleaning devices therefor · CPC title