Radially oriented internally mounted continuous ignition device

Patent metadata

Field	Value
Publication number	US-12092333-B2
Application number	US-202318120183-A
Country	US
Kind code	B2
Filing date	Mar 10, 2023
Priority date	Dec 17, 2020
Publication date	Sep 17, 2024
Grant date	Sep 17, 2024

Abstract

An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber and configured to receive a fuel injector and a surface igniter, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The torch igniter is situated such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case.

First claim

The invention claimed is:

1. A combustor of a gas turbine engine oriented about an engine axis, the combustor comprising:
a combustor case extending along a primary combustor centerline to convey compressed airflow from a compressor to a turbine section, wherein the combustor case comprises a torch igniter opening;
a combustor liner disposed within the combustor case to define a main combustor zone;
at least one fuel nozzle situated at an upstream end of the combustor liner, relative to the primary combustor centerline; and
a torch igniter situated partially within the combustor case, the torch igniter comprising:
a combustion chamber extending along a torch igniter axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber with respect to the torch igniter axis;
a cap defining the axially upstream end of the combustion chamber with respect to the torch igniter axis, wherein the cap is disposed radially outward of the combustor case with respect to the primary combustor centerline along which the combustor case extends, and configured to receive at least one surface igniter, at least one air inlet, and at least one fuel injector;
a tip defining the axially downstream end of the combustion chamber with respect to the torch igniter axis, the tip being radially aligned with the main combustor zone defined by the combustor liner of the gas turbine engine, with respect to the primary combustor centerline, wherein the tip is mounted through the combustor liner during operation of the gas turbine engine;
an annular igniter wall extending along and surrounding the torch igniter axis from the cap to the tip and defining a radial extent of the combustion chamber, the combustion chamber extending radially with respect to the primary combustor centerline from the cap, through the combustor case, to the tip;
a structural wall coaxial with and surrounding the annular igniter wall; and
an outlet passage defined by the annular igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber;
wherein the torch igniter is situated within the torch igniter opening such that the tip is mounted through the combustor liner, the combustion chamber downstream the cap is entirely within the combustor case, and the cap extends through the combustor case;
wherein the tip comprises an elbow between the combustion chamber and the combustor liner which fluidly couples the combustion chamber to the main combustor zone;
wherein the elbow turns 90 degrees from the combustion chamber to the combustor liner; and
wherein an outlet portion of the elbow longitudinally extends parallel to the primary combustor centerline.

2. The combustor of claim 1 , wherein the torch igniter is oriented such that the torch igniter axis extends radially inward with respect to the primary combustor centerline and the engine axis.

3. The combustor of claim 1 , wherein a flange is connected to the combustor case and secures the torch igniter within the torch igniter opening and to the combustor case.

4. The combustor of claim 1 , wherein the tip of the torch igniter is mounted to the combustor liner at the upstream end of the combustor liner with respect to the primary combustor centerline.

5. The combustor of claim 4 , wherein the torch igniter ignites fuel in an outer recirculation zone of the combustor.

6. The combustor of claim 4 , wherein the torch igniter ignites fuel in an inner recirculation zone of the combustor.

7. The combustor of claim 1 , wherein the torch igniter axis is oriented perpendicular to the primary combustor centerline.

8. The combustor of claim 1 , wherein the cap is configured to receive at least three surface igniters.

9. The combustor of claim 1 , wherein the torch igniter is positioned between two fuel nozzles of the combustor.

10. A torch igniter for a combustor of a gas turbine engine, the torch igniter comprising:
a combustion chamber extending along a torch igniter axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber with respect to the torch igniter axis;
a cap defining the axially upstream end of the combustion chamber with respect to the torch igniter axis, wherein the cap is disposed radially outward of a combustor case of the gas turbine engine with respect to a primary combustor centerline along which the combustor case extends, and configured to receive at least one surface igniter, at least one air inlet, and at least one fuel injector;
a tip defining the axially downstream end of the combustion chamber with respect to the torch igniter axis, the tip being radially aligned with a main combustor zone defined by a combustor liner of the combustor of the gas turbine engine, with respect to the primary combustor centerline, wherein the tip is mounted through the combustor liner during operation of the gas turbine engine;
an annular igniter wall extending along and surrounding the torch igniter axis from the cap to the tip and defining a radial extent of the combustion chamber, the combustion chamber extending radially with respect to the primary combustor centerline from the cap, through the combustor case, to the tip, wherein the combustion chamber downstream the cap is entirely within the combustor case, and the cap extends through the combustor case;
a structural wall coaxial with and surrounding the annular igniter wall; and
an outlet passage defined by the annular igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber;
wherein the structural wall and the annular igniter wall are configured for a pressure level within the combustor case of the combustor during operation of the combustor;
wherein the tip comprises an elbow between the combustion chamber and the combustor liner of the combustor which fluidly couples the combustion chamber to the main combustor zone of the combustor:
wherein the elbow turns 90 degrees from the combustion chamber to the combustor liner of the combustor; and
wherein an outlet portion of the elbow longitudinally extends parallel to the primary combustor centerline.

11. The torch igniter of claim 10 , wherein a flange is connected to the combustor case of the gas turbine engine and secures the torch igniter within an opening of the combustor case.

12. The torch igniter of claim 10 , wherein the torch igniter ignites fuel in an outer recirculation zone of the combustor.

13. The torch igniter of claim 10 , wherein the torch igniter ignites fuel in an inner recirculation zone of the combustor.

14. The torch igniter of claim 10 , wherein the cap is configured to receive at least three surface igniters.

Assignees

• Collins Engine Nozzles Inc

Inventors

• Ryon Jason
• Williams Brandon P
• Prociw Lev Alexander

Classifications

• F02C7/264 Primary

  Ignition · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2260/99

  Ignition, e.g. ignition by warming up of fuel or oxidizer in a resonant acoustic cavity · CPC title

• F23R3/343 Primary

  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

• F23R3/346

  for staged combustion · CPC title