Dilution passage arrangement for gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-10655856-B2
Application number	US-201415105427-A
Country	US
Kind code	B2
Filing date	Dec 19, 2014
Priority date	Dec 19, 2013
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.

First claim

What is claimed is:

1. A liner panel for use in a combustor of a gas turbine engine, the liner panel comprising:
a major dilution passage having a lip and a first seal boss; and
a minor dilution passage having a second seal boss adjacent the first seal boss;
the first seal boss connected to the second seal boss, and the first seal boss directly contacting the second seal boss in a circumferential direction;
wherein a connection between the first seal boss and the second seal boss is axially aligned with a center of the major dilution passage and a center of the minor dilution passage along a circumferential line.

2. The liner panel as recited in claim 1 , wherein the lip is configured to extend above a support shell when the liner panel is mounted thereto.

3. The liner panel as recited in claim 1 , wherein the first seal boss defines an inner diameter outside the lip of about 0.64 inches (16.3 mm).

4. The liner panel as recited in claim 3 , wherein the first seal boss defines an outer diameter of about 0.7 inches (17.8 mm).

5. The liner panel as recited in claim 1 , wherein the second seal boss defines an inner diameter of about 0.2 inches (5.1 mm).

6. The liner panel as recited in claim 5 , wherein the second seal boss defines an outer diameter of about 0.27 inches (6.9 mm).

7. The liner panel as recited in claim 1 , wherein the first seal boss and the second seal boss are at least partially surrounded by a multiple of effusion passages.

8. A wall assembly for use in a combustor for a gas turbine engine, the wall assembly comprising:
a support shell with at least one major aperture and at least one minor aperture; and
a liner panel mounted to the support shell, the liner panel including a major dilution passage and a minor dilution passage, the major dilution passage having a lip that extends at least partially through the major aperture and a first seal boss that seals around the major aperture, and the minor dilution passage having a second seal boss that seals around the minor aperture;
the first seal boss directly contacting the second seal boss in a circumferential direction;
wherein a connection between the first seal boss and the second seal boss is axially aligned with a center of the at least one major aperture and a center of the at least one minor dilution aperture along a circumferential line.

9. The wall assembly as recited in claim 8 , wherein the first seal boss defines an inner diameter outside the lip of about 0.64 inches (16.3 mm).

10. The wall assembly as recited in claim 9 , wherein the first seal boss defines an outer diameter of about 0.7 inches (17.8 mm).

11. The wall assembly as recited in claim 10 , wherein the second seal boss defines an inner diameter of about 0.2 inches (5.1 mm).

12. The wall assembly as recited in claim 11 , wherein the second seal boss defines an outer diameter of about 0.27 inches (6.9 mm).

13. The wall assembly as recited in claim 8 , wherein the first seal boss and the second seal boss are at least partially surrounded by a multiple of effusion passages.

14. A method of directing airflow through a wall assembly within a combustor of a gas turbine engine, the method comprising:
at least partially sealing a liner panel to a support shell;
the liner panel including a major dilution passage and a minor dilution passage;
the major dilution passage having a lip extending at least partially through a major aperture in the support shell and a first seal boss that seals with the support shell around the major aperture; and
the minor dilution passage having a second seal boss that seals with the support shell around the minor aperture;
wherein the first seal boss extends to the second seal boss in a circumferential direction such that the first seal boss directly contacts the second seal boss;
wherein a connection between the first seal boss and the second seal boss is axially aligned with a center of the major dilution passage and a center of the minor dilution passage along a circumferential line.

15. The method as recited in claim 14 , further comprising providing a line to line interface between the minor dilution passage and the minor aperture in the support shell in response to a thermal excursion and mechanical tolerance.

16. The method as recited in claim 14 , further comprising at least partially surrounding the first seal boss and the second seal boss by a multiple of effusion passages.

17. The method as recited in claim 14 , further comprising integrally forming the major dilution passage and the minor dilution passage with the liner panel.

18. The method as recited in claim 14 , further comprising connecting the first seal boss and the second seal boss.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Eastwood Jonathan J
• Moura Dennis M
• Bouldin Lee E
• Pacheco-Tougas Monica

Classifications

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title