Axially oriented internally mounted continuous ignition device: removable hot surface igniter

Patent metadata

Field	Value
Publication number	US-11486309-B2
Application number	US-202017125083-A
Country	US
Kind code	B2
Filing date	Dec 17, 2020
Priority date	Dec 17, 2020
Publication date	Nov 1, 2022
Grant date	Nov 1, 2022

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 at an upstream end of the combustor liner, a torch igniter at least partially within the combustor case, and a removable surface igniter. The torch igniter includes a combustion chamber, a cap configured to receive a fuel injector, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, an aperture, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The torch igniter is configured to receive the removable surface igniter through the aperture. An internal end of the removable surface igniter extends through the aperture into the combustion chamber of the torch igniter.

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;
a combustor liner disposed within the combustor case to define a main combustor zone;
a fuel nozzle situated at an upstream end of the combustor liner, relative to the primary combustor centerline;
a first removable surface igniter connected to a power source; and
a torch igniter situated at least 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 configured to receive at least one fuel injector;
a tip defining the axially downstream end of the combustion chamber with respect to the torch igniter axis;
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;
a first aperture configured to receive the first removable surface igniter;
a structural wall coaxial with and surrounding the igniter wall; and
an outlet passage defined by the igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber;

wherein the first removable surface igniter is situated such that a first external end of the first removable surface igniter is external to the combustor case, a first internal end of the first removable surface igniter extends through the first aperture into the combustion chamber of the torch igniter, the torch igniter is situated entirely within the combustor case, the first external end of the first removable surface igniter extends through a first opening of the combustor case when the first internal end of the first removable surface igniter is received by the torch igniter through the first aperture, and a first central region of the first removable surface igniter is disposed radially inward of the first external end of the first removable surface igniter with respect to the primary combustor centerline and the torch igniter axis.

2. The combustor of claim 1 , further comprising a flange which secures the first removable surface igniter within the first opening and creates a seal between the combustor case and the first removable surface igniter.

3. The combustor of claim 1 , wherein the torch igniter axis is parallel to the primary combustor centerline.

4. The combustor of claim 1 , wherein the first removable surface igniter is oriented perpendicular to the torch igniter axis and the primary combustor centerline.

5. The combustor of claim 1 , further comprising a second removable surface igniter, wherein the torch igniter is configured to receive the second removable surface igniter and the second removable surface igniter is situated such that a second external end of the second removable surface igniter is external to the combustor case, a second internal end of the second removable surface igniter extends through a second aperture into the combustion chamber of the torch igniter, a second central region of the second removable surface igniter is disposed radially inward of the second external end of the second removable surface igniter with respect to the primary combustor centerline and the torch igniter axis, and the second removable surface igniter extends through a second opening of the combustor case.

6. The combustor of claim 1 , wherein a first sheath is coaxial to the first removable surface igniter.

7. The combustor of claim 6 , wherein the first sheath extends from the first opening to the structural wall of the torch igniter.

8. The combustor of claim 7 , wherein the first sheath is brazed to the first removable surface igniter.

9. The combustor of claim 8 , wherein the first sheath contains surface threads which interact with surface threads in the first opening and the first aperture to secure the first removable surface igniter.

10. The combustor of claim 6 , further comprising a second removable surface igniter and a second sheath which is coaxial to the second removable surface igniter, wherein the torch igniter is configured to receive the second removable surface igniter and a first internal end of the second removable surface igniter extends through a second aperture into the combustion chamber of the torch igniter.

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

12. The combustor of claim 1 , wherein the first removable surface igniter is connected to the power source by a metallic element.

13. A method of replacing a first removable surface igniter for a torch igniter within a gas turbine engine, the method comprising:
disconnecting a power source from the first removable surface igniter;
detaching a flange from a combustor case of the gas turbine engine, the combustor case comprising a first opening configured to receive a removable surface igniter, wherein the combustor case extends along a primary combustor centerline to convey compressed airflow from a compressor to a turbine section;
removing the first removable surface igniter from the torch igniter through the first opening, the torch igniter being situated entirely within the combustor case and 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 configured to receive at least one fuel injector;
a tip defining the axially downstream end of the combustion chamber with respect to the torch igniter axis;
a first aperture configured to receive the first removable surface igniter;
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;
a structural wall coaxial with and surrounding the igniter wall; and
an outlet passage defined by the igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber;

inserting a second removable surface igniter into the first opening such that a second external end of the second removable surface igniter is external to the combustor case, a second internal end of the second removable surface igniter extends through the first aperture into the combustion chamber of the torch igniter, and a first central region of the first removable surface igniter is disposed radially inward of the first external end of the first removable surface igniter with respect to the primary combustor centerline and the torch igniter axis, wherein the second external end of the second removable surface igniter extends through the first opening of the combustor case when the second internal end of the second removable surface igniter is received by the torch igniter through the first aperture;
reattaching the flange to the combustor case, and
connecting the power source to the second removable surface igniter.

14. The method of claim 13 , wherein the first removable surface igniter is surrounded coaxially by a first sheath and the second removable surface igniter is surrounde

Assignees

• Delavan Inc

Inventors

• Ryon Jason
• Prociw Lev Alexander
• Williams Brandon P

Classifications

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F02C7/264 Primary

  Ignition · CPC title