Passage geometry for gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-10684017-B2
Application number	US-201415027082-A
Country	US
Kind code	B2
Filing date	Oct 21, 2014
Priority date	Oct 24, 2013
Publication date	Jun 16, 2020
Grant date	Jun 16, 2020

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 wall assembly within a gas turbine engine, comprising: a shell; and
a liner panel attached to the shell, the liner panel comprising a hot side and a cold side, the hot side forming a radial peripheral boundary of a combustion chamber; and
a grommet comprising a passage wall and a flange wall transverse to the passage wall, and the flange wall is between the liner panel and the shell;
the passage wall at least partially forming a dilution passage along an axis;
the passage wall and the flange wall at least partially forming a grommet chamber that at least partially surrounds the dilution passage; and
a section of the grommet projecting along the axis away from the hot side and into the combustion chamber, and the section of the grommet extending partially circumferentially around the axis between opposing circumferential ends of the section of the grommet;
wherein the section of the grommet defines a perimeter of less than three hundred and sixty degrees;
wherein the section of the grommet extends radially relative to the axis between an inner surface and an outer surface;
wherein the section of the grommet is configured with an outlet passage that fluidly couples the grommet chamber with the combustion chamber; and
wherein the outlet passage is located in the outer surface and spaced from the hot side.

2. The wall assembly of claim 1 , wherein
the section of the grommet projects in a first direction along the axis away from the hot side and into the combustion chamber; and
a section of the passage wall projects in a second direction along the axis out from the flange wall, and the second direction is opposite the first direction.

3. The wall assembly of claim 1 , wherein
the passage wall has a first end and a second end;
the passage wall extends along the axis between the first end and the second end;
the flange wall is disposed a non-zero first distance from the first end; and
the flange wall is disposed a non-zero second distance from the second end.

4. The wall assembly of claim 1 , wherein a portion of the grommet chamber within the passage wall extends partially around the axis between opposing circumferential end surfaces.

5. The wall assembly of claim 1 , wherein the flange wall is configured with an inlet passage that extends radially relative to the axis through a section of the flange wall to the grommet chamber.

6. The wall assembly of claim 1 , wherein
the passage wall and the flange wall at least partially form a second grommet chamber circumferentially adjacent the grommet chamber; and
the second grommet chamber partially surrounds the dilution passage.

7. A wall assembly within a gas turbine engine, comprising: a shell; and
a liner panel attached to the shell, the liner panel comprising a hot side and a cold side, the hot side forming a radial peripheral boundary of a combustion chamber; and
a grommet with a passage wall and a flange wall transverse to the passage wall, and the flange wall is between the liner panel and the shell;
wherein the grommet at least partially defines

a dilution passage along an axis; and
at least one grommet chamber that at least partially surrounds the dilution passage;
wherein the at least one grommet chamber includes an outlet passage transverse to the passage wall and adjacent to the hot side;
wherein the outlet passage is defined through an axially extended passage wall section of the passage wall that extends beyond the hot side and into the combustion chamber;
wherein the axially extended passage wall section projects along the axis away from the hot side and into the combustion chamber, and the axially extended passage wall section extends partially circumferentially around the axis between opposing circumferential ends of the axially extended passage wall section;
wherein the axially extended passage wall section defines a perimeter of less than three hundred and sixty degrees; and
wherein the outlet passage is located in an outer surface of the axially extended passage wall section and spaced from the hot side.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

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

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F23R2900/03045

  Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling · 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

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title