Internally cooled dilution hole bosses for gas turbine engine combustors

Patent metadata

Field	Value
Publication number	US-11085644-B2
Application number	US-201916508797-A
Country	US
Kind code	B2
Filing date	Jul 11, 2019
Priority date	Sep 2, 2015
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.

First claim

The invention claimed is:

1. A combustor for a gas turbine engine, the combustor comprising:
a liner defining a combustion chamber, the liner having:
an inner surface facing the combustion chamber and an outer surface opposite the inner surface,
a set of dilution holes extending through the liner, and
a set of hollow bosses formed integrally on the outer surface of the liner, wherein the set of hollow bosses comprises a corresponding hollow boss extending about a corresponding dilution hole of the set of dilution holes, such that each hollow boss corresponds to each dilution hole of the set of dilution holes, each corresponding hollow boss defining an internal cavity extending about each corresponding dilution hole, each hollow boss having an inlet defined in the outer surface of the liner for admitting cooling air into the internal cavity and a plurality of film holes extending through the inner surface of the liner and fluidly connecting the internal cavity to the combustion chamber, the film holes being angled relative to the liner and distributed in a circle pattern about the corresponding dilution hole for forming a cooling film on the inner surface of liner, wherein heat transfer augmentation features are provided on an internal cavity surface of at least one of the hollow bosses of the set of hollow bosses, the heat transfer augmentation features interspersed between the film holes.

2. The combustor defined in claim 1 , wherein the internal cavity of each hollow boss at least partly encircles each corresponding dilution hole and is sealed therefrom.

3. The combustor defined in claim 1 , wherein the internal cavity of each hollow boss is provided in the form of an annulus which is widened in a direction away from each corresponding dilution hole.

4. The combustor defined in claim 1 , wherein the inlet comprises a set of impingement holes distributed atop of the set of hollow bosses.

5. A combustor for a gas turbine engine, the combustor comprising:
a liner defining a combustion chamber, the liner having:
an inner surface facing the combustion chamber and an outer surface opposite the inner surface,
a dilution hole extending through the liner,
a boss integrally formed in the liner about the dilution hole, the boss defining an internal cavity in the liner around the dilution hole, the internal cavity extending over a surface area of the liner around the dilution hole,
a set of inlet holes defined in the outer surface of the liner for admitting cooling air into the internal cavity, and
a set of film holes defined in the inner surface of the liner for discharging the cooling air from the internal cavity into the combustion chamber, the set of film holes being distributed over the surface area of the liner covered by the internal cavity,
wherein heat transfer augmentation features are provided on an internal cavity surface of the boss, and wherein the heat transfer augmentation features are interspersed between the film holes.

6. The combustor defined in claim 5 , wherein the internal cavity is provided in the form of an annulus widened in a direction away from the dilution hole.

7. A cooling arrangement for providing cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine, the cooling arrangement comprising: a hollow boss projecting from an outer surface of the liner about the dilution hole, the hollow boss defining an internal cavity extending circumferentially around the dilution hole, the internal cavity being sealed from the dilution hole defined in the liner, the internal cavity having an inlet in fluid flow communication with an air plenum surrounding the liner and a plurality of film holes distributed in circular pattern about the dilution hole and angled with respect to the liner to promote the formation of coolant film on an inner surface of the liner, and wherein heat transfer augmenters project from an internal cavity surface of the hollow boss, the heat transfer augmenters interspersed between the film holes.

8. The cooling arrangement defined in claim 7 , wherein the inlet comprises a set of impingement holes defined in the hollow boss and oriented to direct impingement jets directly against the internal cavity surface from which the heat transfer augmenters project into the internal cavity.

Assignees

• Pratt & Whitney Canada

Inventors

• Papple Michael
• Lao Si-Man Amy
• Sreekanth Sri

Classifications

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• Y02T50/60

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

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/16 Primary

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title

• F23R2900/03045

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