Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-2016208704-A1
Application number	US-201414913770-A
Country	US
Kind code	A1
Filing date	Sep 16, 2014
Priority date	Sep 16, 2013
Publication date	Jul 21, 2016
Grant date	—

Abstract

A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle a therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle a therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.

First claim

What is claimed is:

1 . A wall assembly within a gas turbine engine, comprising:
a transverse structure with at least one effusion passage, the at least one effusion passage including an inlet in an outer periphery of the transverse structure.

2 . The wall assembly as recited in claim 1 , wherein the outer periphery is at least partially circular.

3 . The wall assembly as recited in claim 1 , wherein the outer periphery is at least partially linear.

4 . The wall assembly as recited in claim 1 , wherein the transverse structure includes a first wall that at least partially defines a dilution passage and a second wall transverse to the first wall that at least partially defines a liner panel.

5 . The wall assembly as recited in claim 4 , wherein the first wall includes a seal face in contact with a support shell.

6 . The wall assembly as recited in claim 5 , wherein the effusion passage includes an outlet through a hot side of the liner panel.

7 . The wall assembly as recited in claim 1 , wherein the at least one effusion passage extends at an angle a, and the angle a defines an outlet which does not penetrate an inner periphery of the transverse structure.

8 . The wall assembly as recited in claim 1 , wherein the inlet is in communication with an impingement cavity.

9 . The wall assembly as recited in claim 8 , further comprising a liner panel and a support shell that defines the impingement cavity therebetween.

10 . The wall assembly as recited in claim 1 , wherein the transverse structure at least partially defines an annular grommet.

11 . The wall assembly as recited in claim 10 , further comprising a liner panel and a support shell, the annular grommet located therebetween.

12 . The wall assembly as recited in claim 11 , wherein the at least one effusion passage extends at an angle a, the angle a defines an outlet in a hot side of the annular grommet, and the hot side is generally parallel to a hot side of the liner panel.

13 . The wall assembly as recited in claim 1 , wherein the transverse structure at least partially defines a rail that extends from a liner panel.

14 . The wall assembly as recited in claim 1 , wherein the transverse structure is located within at least one of a combustor section, an augmentor section, an exhaust duct section or a nozzle section of a gas turbine engine.

15 . A wall assembly adjacent a combustion chamber within a gas turbine engine, comprising:
a support shell; a liner panel adjacent to the support shell; and a transverse structure between the support shell and the liner panel, the transverse structure includes at least one effusion passage that extends at an angle a, and the at least one effusion passage includes an inlet in an outer periphery of the transverse structure.

16 . The wall assembly as recited in claim 15 , wherein the transverse structure at least partially defines a dilution passage that extends from the liner panel.

17 . The wall assembly as recited in claim 15 , wherein the transverse structure at least partially defines an annular grommet.

18 . The wall assembly as recited in claim 15 , wherein the transverse structure at least partially defines a rail that extends from a liner panel.

19 . A method of cooling a wall assembly within a gas turbine engine, comprising:
directing at least one effusion passage between an inlet in an outer periphery of a transverse structure at least partially between a liner panel and a support shell, the inlet in communication with an impingement cavity between the liner panel and the support shell.

20 . The method as recited in claim 18 , further comprising:
defining the passage at an angle a to avoid penetration of an inner periphery of the transverse geometry.

Assignees

• United Technologies Corp

Inventors

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

Classifications

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F23R3/002 Primary

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

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title