Passage geometry for gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-2016238253-A1
Application number	US-201415027082-A
Country	US
Kind code	A1
Filing date	Oct 21, 2014
Priority date	Oct 24, 2013
Publication date	Aug 18, 2016
Grant date	—

Abstract

An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber. A wall assembly within a gas turbine engine includes a liner panel with a hot side and a cold side. The wall assembly also includes an annular grommet with a passage wall and a flange wall transverse to the passage wall. The annular grommet includes a chamber therein. A method of cooling a wall assembly within a gas turbine engine includes injecting air through a chamber in an annular grommet.

First claim

What is claimed is:

1 . A grommet for a wall assembly of a combustor section of a gas turbine engine, the grommet comprising:
a wall that at least partially defines
a dilution passage along an axis; and
at least one chamber that at least partially surrounds the dilution passage.

2 . The grommet as recited in claim 1 , wherein the chamber includes an outlet passage generally transverse to the dilution passage.

3 . The grommet as recited in claim 1 , wherein the chamber includes an outlet passage directed into the dilution passage.

4 . The grommet as recited in claim 1 , wherein the wall is an annular passage wall.

5 . The grommet as recited in claim 4 , wherein the annular passage wall includes a step.

6 . The grommet as recited in claim 5 , further comprising an overhang adjacent to the step.

7 . The grommet as recited in claim 5 , further comprising a feature at least partially formed along the step along an axis of the dilution passage.

8 . The grommet as recited in claim 7 , wherein the chamber is segmented.

9 . The grommet as recited in claim 1 , wherein the wall includes an annular passage wall and a flange wall that extends transversely from the passage wall, the passage wall including an inlet passage in communication with the chamber.

10 . A wall assembly within a gas turbine engine, comprising:
a liner panel with a hot side and a cold side; and a grommet with a passage wall and a flange wall transverse to the passage wall, wherein the grommet at least partially defines
a dilution passage along an axis; and
at least one chamber that at least partially surrounds the dilution passage.

11 . The wall assembly as recited in claim 10 , wherein the chamber includes an outlet passage generally transverse to the passage wall and adjacent to the hot side, the outlet passage defined through an axially extended passage wall section of the passage wall that extends beyond the hot side.

12 . The wall assembly as recited in claim 11 , wherein the axially extended passage wall section defines a perimeter of less than three hundred and sixty degrees.

13 . The wall assembly as recited in claim 11 , wherein the hot side of the liner panel includes a recessed area adjacent to the outlet passage.

14 . The wall assembly as recited in claim 13 , wherein the recessed area around the annular grommet is non-circular.

15 . The wall assembly as recited in claim 10 , wherein the hot side of the liner panel includes a stepped area around the annular grommet, and wherein the stepped area around the annular grommet interfaces with a stepped area within the flange.

16 . The wall assembly as recited in claim 15 , wherein the stepped area around the annular grommet and the stepped area within the flange extends for less than three hundred and sixty degrees.

17 . A method of cooling a wall assembly within a gas turbine engine, comprising:
communicating air into a chamber in an annular grommet.

18 . The method as recited in claim 17 , further comprising ejecting the air from the chamber generally parallel to a hot side of a liner panel.

19 . The method as recited in claim 17 , further comprising ejecting the air adjacent to recessed area of a liner panel.

20 . The method as recited in claim 17 , further comprising ejecting the air from the chamber into a dilution passage formed by the annular grommet.

Assignees

• United Technologies Corp

Inventors

• Moura Dennis M
• Eastwood Jonathan J
• Bouldin Lee E

Classifications

• F23R3/002

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

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title