Fuel systems for torch ignition devices

Patent metadata

Field	Value
Publication number	US-12313005-B2
Application number	US-202318123764-A
Country	US
Kind code	B2
Filing date	Mar 20, 2023
Priority date	Nov 18, 2020
Publication date	May 27, 2025
Grant date	May 27, 2025

Abstract

A torch igniter system for a combustor of a gas turbine engine includes a housing defining a combustion chamber, an ignition source disposed at least partially in the combustion chamber, a fuel injector, a first fluid path connecting a first fuel source to the fuel injector, a second fluid path connecting an air source to the fuel injector, and a third fluid path connecting a second fuel source to the combustion chamber. The fuel injector is configured to inject fuel, air, or a mixture of fuel and air into the combustion chamber and to impinge on the ignition source.

First claim

The invention claimed is:

1. A torch igniter system for a combustor of a gas turbine engine, the torch igniter system comprising:
a housing defining a combustion chamber, wherein the housing is annular and extends along an axis;
an ignition source disposed at least partially in the combustion chamber;
a fuel injector configured to inject at least one of fuel and air into the combustion chamber and to impinge on the ignition source;
a first fluid path connecting a first fuel source to the combustion chamber;
a second fluid path connecting an air source to the fuel injector;
a third fluid path connecting a second fuel source that is liquid to the fuel injector;
a cap formed by the housing disposed at an axial end of the torch igniter system, wherein the cap receives the fuel injector;
an annular channel embedded within the cap and centered on the axis, wherein the annular channel is fluidly connected to the second fuel source that is liquid and the third fluid path includes the annular channel;
a first aperture extending through an inner wall of the housing that connects the annular channel to the combustion chamber, wherein the first aperture is embedded in the cap and the third fluid path includes the first aperture, and a first fuel from the first fuel source is injected into the combustion chamber downstream of the first aperture;
a mixing annulus configured to mix a second fuel from the second fuel source with air to atomize the second fuel before entering the combustion chamber through the first aperture;
a swirling annulus embedded within the cap and centered on the axis, wherein:
the swirling annulus is fluidly connected to the first fuel source and the first fluid path includes the swirling annulus, and
the swirling annulus annularly surrounds the first aperture; and

a second aperture extending through the inner wall of the housing that connects the swirling annulus to the combustion chamber.

2. The torch igniter system of claim 1 , wherein the ignition source is a glow plug.

3. The torch igniter system of claim 1 , further comprising a controller to control flow from the first fuel source, flow from the second fuel source, and flow from the air source.

4. The torch igniter system of claim 3 , wherein the controller is configured to:
deliver the first fuel from the first fuel source to the combustion chamber;
detect an interruption in the delivery of the first fuel from the first fuel source; and
deliver the second fuel from the second fuel source and the air from the air source to the combustion chamber after detecting the interruption.

5. The torch igniter system of claim 1 , wherein the first aperture, the mixing annulus, and the swirling annulus are centered on the axis, and wherein the second aperture is radially spaced from the axis.

6. The torch igniter system of claim 1 , wherein:
the second fluid path and the third fluid path are at least partially overlapping upstream of the combustion chamber,
the first fluid path and the second fluid path are non-overlapping upstream of the combustion chamber, and
the first fluid path and the third fluid path are non-overlapping upstream of the combustion chamber.

7. The torch igniter system of claim 1 , wherein the first aperture and the second aperture are fluidly separated.

8. The torch igniter system of claim 6 , wherein the first aperture, the mixing annulus, and the swirling annulus are centered on the axis, and wherein the second aperture is radially spaced from the axis.

9. A torch igniter system for a combustor of a gas turbine engine, the torch igniter system comprising:
a housing defining a combustion chamber, wherein the housing is annular and extends along an axis;
an ignition source disposed at least partially in the combustion chamber;
a cap formed by the housing disposed at an axial end of the torch igniter system;
a fuel injector configured to inject at least one of fuel and air into the combustion chamber and to impinge on the ignition source, the fuel injector comprising:
a mixing annulus formed in the cap;
a first fluid path connecting a first fuel source to the mixing annulus;
a second fluid path connecting an air source to the mixing annulus;
a first aperture formed in the cap and fluidly connecting the mixing annulus to the combustion chamber;
a swirling annulus formed in the cap and annularly surrounding the first aperture;
a third fluid path connecting a second fuel source to the swirling annulus; and
a second aperture formed in the cap and fluidly connecting the swirling annulus to the combustion chamber.

Assignees

• Collins Engine Nozzles Inc

Inventors

• Ryon Jason A
• Prociw Lev Alexander
• Williams Brandon P

Classifications

• F23R3/36

  Supply of different fuels · CPC title

• F23Q9/00

  Pilot flame igniters · CPC title

• F02P21/00

  Direct use of flames or burners for ignition · CPC title

• F02C9/40

  specially adapted to the use of a special fuel or a plurality of fuels · CPC title

• F02C7/264 Primary

  Ignition · CPC title