Combustor quench aperture cooling

Patent metadata

Field	Value
Publication number	US-2016290644-A1
Application number	US-201415037555-A
Country	US
Kind code	A1
Filing date	Dec 4, 2014
Priority date	Dec 6, 2013
Publication date	Oct 6, 2016
Grant date	—

Abstract

An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.

First claim

What is claimed is:

1 . An assembly for a turbine engine, the assembly comprising:
a combustor wall including a shell, a heat shield and an annular body; the annular body extending through the combustor wall and at least partially defining a quench aperture along a centerline through the combustor wall; and the shell defining a first cooling aperture radially outward of the annular body relative to the center line and configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.

2 . The assembly of claim 1 , wherein a funnel-shaped portion of the shell extends around the body and defines the cooling aperture.

3 . The assembly of claim 2 , wherein the funnel-shaped portion of the shell has a substantially straight sectional geometry.

4 . The assembly of claim 2 , wherein the funnel-shaped portion of the shell has an arcuate sectional geometry.

5 . The assembly of claim 2 , wherein the funnel-shaped portion of the shell has a compound sectional geometry.

6 . The assembly of claim 2 , wherein
the shell includes a second portion; the funnel-shaped portion extends laterally from the second portion towards the body; and the second portion is substantially parallel with an opposing portion of the heat shield.

7 . The assembly of claim 1 , wherein a portion of the shell is non-parallel with an opposing portion of the heat shield, and the portion of the shell defines the cooling aperture.

8 . The assembly of claim 1 , wherein a first angle of incidence is defined relative to a centerline of the first cooling aperture and a surface of the shell.

9 . The assembly of claim 8 , wherein
the shell further defines a second cooling aperture through which air is directed to impinge against an outer surface of the portion of the body; and a second angle of incidence is defined relative to a centerline of the second cooling aperture and the surface of the shell, and the second angle of incidence is different than the first angle of incidence.

10 . The assembly of claim 1 , wherein the portion of the body includes an outer surface which defines a rib.

11 . The assembly of claim 10 , wherein at least a portion of the rib comprises a chevron.

12 . The assembly of claim 1 , wherein the portion of the body includes an outer surface which defines a point protrusion.

13 . The assembly of claim 1 , wherein the portion of the body includes an outer surface which defines a channel extending into the body.

14 . The assembly of claim 1 , further comprising a sleeve extending around the body and extending vertically from the heat shield towards the shell.

15 . The assembly of claim 1 , wherein the heat shield includes a plurality of panels that are attached to the shell, and the body is connected to one of the panels.

16 . The assembly of claim 1 , further comprising:
a second combustor wall; and a combustor bulkhead that extends between the combustor wall and the second combustor wall; wherein the heat shield, the second combustor wall and the combustor bulkhead define a combustion chamber.

17 . An assembly for a turbine engine, the assembly comprising:
a combustor wall including a shell, a heat shield and an annular body; the body extending between the shell and the heat shield and defining a quench aperture in the combustor wall; wherein a funnel-shaped portion of the shell extends around the body and defines a cooling aperture fluidly coupled with a cooling cavity between the shell and the heat shield.

18 . The assembly of claim 17 , wherein the funnel-shaped portion of the shell is adapted to direct air through the cooling aperture and into the cooling cavity to impinge against the body.

19 . An assembly for a turbine engine, the assembly comprising:
a combustor wall including a shell, a heat shield and an annular body; the body extending between the shell and the heat shield and defining a quench aperture in the combustor wall; wherein the shell defines a cooling aperture that extends along an axis with a trajectory to the body, and the cooling aperture is fluidly coupled with a cooling cavity between the shell and the heat shield.

20 . The assembly of claim 19 , wherein a portion of the shell is non-parallel with an opposing portion of the heat shield, and the portion of the shell defines the cooling aperture.

Assignees

• United Technologies Corp

Inventors

• Cunha Frank J
• Kostka Jr Stanislav

Classifications

• F02C7/18

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

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/002 Primary

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

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/03045

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