Gas turbine engine dual-wall hot section structure

Patent metadata

Field	Value
Publication number	US-10775044-B2
Application number	US-201816172383-A
Country	US
Kind code	B2
Filing date	Oct 26, 2018
Priority date	Oct 26, 2018
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

First claim

What is claimed is:

1. A hot section part of a turbine engine configured to be exposed to hot gases, the hot section part comprising:
a first wall having a first wall inner surface and a first wall outer surface opposite the first wall inner surface, the first wall inner surface exposed to the hot gases;
a second wall extending around at least a portion of the first wall to form a dual-wall structure, the second wall having a second wall inner surface and a second wall outer surface opposite the second wall inner surface, the second wall inner surface spaced apart from the first wall outer surface to form an intervening cavity;
a plurality of pedestals, each pedestal coupled to the first wall outer surface and the second wall inner surface and extending through the intervening cavity, each pedestal having at least one outside surface facing the intervening cavity, and each pedestal having a principal axis and extending through the intervening cavity about its principal axis;
a plurality of impingement cooling holes extending through the second wall to admit a flow of cooling air into the intervening cavity; and
a plurality of effusion cooling passages, each effusion cooling passage associated with a different one of the plurality of pedestals and disposed at a predetermined angle relative to its associated principal axis, each effusion cooling passage having an inlet and an outlet, each inlet formed on a different one of the at least one outside surfaces, each outlet formed on the first wall outer surface, whereby a portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

2. The hot section part of claim 1 , wherein the predetermined angle is in the range of 45-degrees to 80-degrees.

3. The hot section part of claim 1 , wherein each pedestal, when taken along a cross section perpendicular to its principal axis, has a circular cross-sectional shape.

4. The hot section part of claim 1 , wherein each pedestal, when taken along a cross section perpendicular to its principal axis, has a non-circular cross-sectional shape.

5. The hot section part of claim 1 , wherein each pedestal is spaced apart from every other pedestal of the plurality of pedestals.

6. The hot section part of claim 1 , further comprising a plurality of heat transfer enhancement features formed on at least portions of one or more of the second wall outer surface and surfaces that define the intervening cavity.

7. The hot section part of claim 1 , wherein at least a portion of the second wall around the impingement cooling holes are locally dimpled in a direction away from the intervening cavity.

8. The hot section part of claim 1 , wherein the first wall, the second wall, and the plurality of pedestals comprise a nickel-based superalloy.

9. The hot section part of claim 1 , wherein the first wall, the second wall, and the plurality of pedestals are integrally formed using one of an additive manufacturing process, an injection molding process, and a casting process.

10. The hot section part of claim 7 , wherein the additive manufacturing process comprises direct metal laser sintering (DMLS).

11. A gas turbine engine combustor, comprising:
a first liner; and
a second liner spaced apart from the first liner to form a combustion chamber that is configured to receive an air-fuel mixture for combustion therein,
wherein at least one of the first and second liners comprises:
a first wall having a first wall inner surface and a first wall outer surface opposite the first wall inner surface, the first wall inner surface exposed to the air-fuel mixture;
a second wall extending around at least a portion of the first wall to form a dual-wall structure, the second wall having a second wall inner surface and a second wall outer surface opposite the second wall inner surface, the second wall inner surface spaced apart from the first wall outer surface to form an intervening cavity;
a plurality of pedestals, each pedestal coupled to the first wall outer surface and the second wall inner surface and extending through the intervening cavity, each pedestal having at least one outside surface facing the intervening cavity, and each pedestal having a principal axis and extends through the intervening cavity about its principal axis;
a plurality of impingement cooling holes extending through the second wall to admit a flow of cooling air into the intervening cavity; and
a plurality of effusion cooling passages, each effusion cooling passage associated with a different one of the plurality of pedestals and disposed at a predetermined angle relative to its associated principal axis, each effusion cooling passage having an inlet and an outlet, each inlet formed on a different one of the at least one outside surfaces, each outlet formed on the first wall outer surface, whereby a portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

12. The gas turbine engine combustor of claim 11 , wherein the predetermined angle is in the range of 45-degrees to 80-degrees.

13. The gas turbine engine combustor of claim 11 , wherein each pedestal, when taken along a cross section perpendicular to its principal axis, has a circular cross-sectional shape.

14. The gas turbine engine combustor of claim 11 , wherein each pedestal, when taken along a cross section perpendicular to its principal axis, has a non-circular cross-sectional shape.

15. The gas turbine engine combustor of claim 11 , wherein each pedestal is spaced apart from every other pedestal of the plurality of pedestals.

16. The gas turbine engine combustor of claim 11 , further comprising a plurality of heat transfer enhancement features formed on at least portions of one or more of the second wall outer surface and surfaces that define the intervening cavity.

17. The gas turbine engine combustor of claim 11 , wherein at least a portion of the second wall around the impingement cooling holes are locally dimpled in a direction away from the intervening cavity.

18. The gas turbine engine combustor of claim 11 , wherein the first wall, the second wall, and the plurality of pedestals comprise a nickel-based superalloy.

19. The gas turbine engine combustor of claim 11 , wherein the first wall, the second wall, and the plurality of pedestals are integrally formed using one of an additive manufacturing process, an injection molding process, and a casting process.

20. A gas turbine engine, comprising:
a compressor section, a combustion section, and a turbine section disposed in flow series, the combustion section comprising a first liner and a second liner spaced apart from the first liner to form a combustion chamber that is configured to receive an air-fuel mixture for combustion therein,
wherein at least one of the first and second liners comprises:
a first wall having a first wall inner surface and a first wall outer surface opposite the first wall inner surface, the first wall inner surface exposed to the air-fuel mixture;
a second wall extending around at least a portion of the first wall to form a dual-wall structure, the second wall having a second wall inner surface and a second wall outer surface opposite the second wall inner surface, the second wall inner surface spaced apart from the first wall outer surface to form an intervening cavity;
a plurality of pedestals, each p

Assignees

• Honeywell Int Inc

Inventors

• Dudebout Rodolphe
• Verma Atul
• James Sunil
• Ozogul Hamdullah
• Gintert John

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

• F05D2260/201

  by impingement of a fluid · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title