Two-circuit injector for a turbine engine combustion chamber

Patent metadata

Field	Value
Publication number	US-9927125-B2
Application number	US-201314432952-A
Country	US
Kind code	B2
Filing date	Sep 23, 2013
Priority date	Oct 1, 2012
Publication date	Mar 27, 2018
Grant date	Mar 27, 2018

Abstract

A start-up injector for a turbine engine combustion chamber, said injector including a fuel injection circuit; and a fuel ignition circuit including a fuel injector supplied by the fuel injection circuit and a spark plug for igniting the injected fuel. The start-up injector also includes a partitioned enclosure including a first compartment in which the fuel is ignited by the spark plug and a second compartment separated from the first compartment by a thermally conductive partition; and a main combustion start-up circuit which includes at least one fuel injector supplied by the fuel injection circuit and opens into the second compartment of the enclosure such as to inject the fuel against the wall.

First claim

The invention claimed is:

1. A combustion assembly for a turbine engine, comprising:
a turbine engine combustion chamber; and
a start-up injector for the turbine engine combustion chamber, arranged on a wall of the combustion chamber and leading to the wall of the combustion chamber via an orifice of the wall of the combustion chamber, the start-up injector comprising:
a fuel injection circuit,
a fuel ignition circuit comprising a first fuel injector fed by the fuel injection circuit, and an ignitor for igniting a injected fuel,
a partitioned enclosure comprising a first compartment wherein the ignition of the injected fuel by the ignitor takes place, and a second compartment separated from the first compartment by a thermally conductive partition wall, the first compartment and the second compartment both leading to the combustion chamber via a common fuel evacuation opening and
a principal start-up combustion circuit, comprising at least one second fuel injector fed by said fuel injection circuit, and leading to the second compartment of the partitioned enclosure by being arranged so as to inject fuel against said thermally conductive partition wall.

2. The combustion assembly for a turbine engine according to claim 1 , wherein the fuel injection circuit comprises a fuel supply inlet and an overpressure valve blocking a feed of the combustion start-up circuit when a fuel pressure is less than a predetermined threshold.

3. The combustion assembly for a turbine engine according to claim 2 , wherein the predetermined threshold below which the overpressure valve blocks the feed of the combustion start-up circuit is between 2.5 and 3 bar.

4. The combustion assembly for a turbine engine according to claim 1 , wherein the at least one second fuel injector of the principal start-up combustion circuit is a pre-vaporization injector adapted to vaporize fuel.

5. The combustion assembly for a turbine engine according to claim 1 , wherein the ignitor is a glow plug or a spark plug.

6. The combustion assembly for a turbine engine according to claim 1 , wherein the partitioned enclosure includes an external wall fitted with air admission openings.

7. A turbine engine, comprising a combustion assembly according to claim 1 .

8. The turbine engine according to claim 7 , comprising a casing wherein is arranged the combustion chamber, and the start-up injector being attached to said casing such that:
the partitioned enclosure enters inside the combustion chamber through the casing and the wall of said combustion chamber,
and
air admission openings of an external wall of said partitioned enclosure terminate in an interstice between the casing and the combustion chamber.

Assignees

• Turbomeca

Inventors

• Carrere Bernard

Classifications

• F23D11/446

  heated by an auxiliary flame · CPC title

• F02C7/264

  Ignition · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · 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

• F23R3/30 Primary

  comprising fuel prevapourising devices · CPC title