Injection device for a combustion chamber of a turbine engine

Patent metadata

Field	Value
Publication number	US-9360218-B2
Application number	US-201314039408-A
Country	US
Kind code	B2
Filing date	Sep 27, 2013
Priority date	Sep 28, 2012
Publication date	Jun 7, 2016
Grant date	Jun 7, 2016

Abstract

A fuel injection device is provided. The device includes a pilot injector opening out into a venturi and an annular row of multipoint injection orifices opening out axially in a downstream direction and radially outside the venturi, the venturi being connected at its downstream end to a separation wall. The outer peripheral edge of the separation wall has a diameter greater than the diameter of the annular row of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber.

First claim

The invention claimed is:

1. A fuel injection device for an annular combustion chamber of a turbine engine, the device having a longitudinal axis along which fuel is flowing, and comprising:
a pilot circuit feeding an injector leading into a venturi, and a multipoint circuit feeding an annular row of injection orifices oriented parallel to said longitudinal axis, for leading fuel towards a radial periphery of the venturi, the venturi being provided with an annular separation wall at a downstream end, for separating combustion zones of the pilot circuit and of the multipoint circuit, respectively,
wherein an outer peripheral edge of the separation wall has a diameter greater than a diameter of the annular row of injection orifices, such that the annular separation wall forms a thermal protection screen for said injection orifices against heat radiation coming from the combustion zone of the pilot circuit.

2. A device according to claim 1 , wherein the annular separation wall is frustoconical in shape, flaring downstream.

3. A device according to claim 1 , wherein the injection orifices are formed in a frustoconical wall situated at an upstream end of the venturi and formed integrally with the venturi.

4. A device according to claim 1 , wherein the annular separation wall has a thickness that decreases from upstream to downstream.

5. A device according to claim 1 , further comprising a frustoconical bowl surrounding the venturi, a larger-diameter downstream end of the bowl and the outer peripheral edge of the annular separation wall being situated in a same transverse plane.

6. A device according to claim 1 , wherein the venturi has an inner cavity fed with air and communicating with at least one annular row of first air-passing orifices opening out in a radially inner wall of the venturi.

7. A device according to claim 6 , wherein the first air-passing orifices are formed in a vicinity of the annular separation wall.

8. A device according to claim 7 , wherein the inner cavity of the venturi communicates with at least one annular row of second air-passing orifices formed in a downstream annular wall of the cavity, the second air-passing orifices opening out upstream from the annular separation wall in order to cool the annular separation wall.

9. A device according to claim 8 , wherein a radially inner end of the downstream annular wall is connected to an upstream end of the annular separation wall.

10. A device according to claim 8 , wherein a radially outer end of the downstream annular wall is connected to a downstream end of a cylindrical outer wall of the inner cavity, an upstream end thereof being surrounded by the injection orifices of the multipoint circuit.

11. A device according to claim 8 , wherein downstream outlets of the second air-passing orifices, are situated at a distance from the separation wall such that air delivered by said second air-passing orifices impacts against the annular separation wall.

12. A device according to claim 11 , wherein the downstream outlets of the second air-passing orifices are situated facing an inner periphery of the annular separation wall.

13. An annular combustion chamber for a turbine engine, the annular combustion chamber including at least one fuel injection device according to claim 1 .

14. A turbine engine comprising a combustion chamber according to claim 13 .

Assignees

• Snecma

Inventors

• Rullaud Matthieu Francois
• Dancie Galadriel
• Lunel Romain Nicolas
• Noel Thomas Olivier Marie

Classifications

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/34 Primary

  Feeding into different combustion zones · 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

• F23R3/20 Primary

  incorporating fuel injection means · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title