Systems and methods for variable microchannel combustor liner cooling

Patent metadata

Field	Value
Publication number	US-2020271317-A1
Application number	US-201916285186-A
Country	US
Kind code	A1
Filing date	Feb 25, 2019
Priority date	Feb 25, 2019
Publication date	Aug 27, 2020
Grant date	—

Abstract

In accordance with an embodiment of the disclosure, a system includes a combustor liner disposed about a combustion chamber of a combustor of a gas turbine system. The combustor liner includes an inner wall portion exposed to the combustion chamber, an outer wall portion disposed about the inner wall portion, and multiple channels between the inner and outer wall portions of the combustor liner. Each channel of the multiple channels is configured to direct a coolant along the combustor liner to convectively cool the combustor liner, and each channel of the multiple channels includes a cross-sectional area that progressively changes along a length of each channel of the plurality of channels.

First claim

1 . A system, comprising:
a combustor liner disposed about a combustion chamber of a combustor of a gas turbine system, wherein the combustor liner comprises:
an inner wall portion exposed to the combustion chamber;
an outer wall portion disposed about the inner wall portion; and
a plurality of channels between the inner and outer wall portions of the combustor liner, wherein each channel of the plurality of channels is configured to direct a coolant along the combustor liner to convectively cool the combustor liner, and each channel of the plurality of channels includes a cross-sectional area that progressively changes along a length of each channel of the plurality of channels.

2 . The system of claim 1 , wherein the inner and outer wall portions are integral portions of a one-piece structure.

3 . The system of claim 1 , wherein the outer wall portion comprises a covering coupled to the inner wall portion.

4 . The system of claim 3 , wherein the covering is bonded to the inner wall portion along an entire length of the covering.

5 . The system of claim 3 , wherein at least one of the plurality of channels is recessed into an outer surface of the inner wall portion, an inner surface of the outer wall portion, or a combination thereof.

6 . The system of claim 1 , comprising an inlet guide having a ramp and an opening upstream from inlets of the plurality of channels.

7 . The system of claim 6 , wherein the opening extends circumferentially about the combustor liner.

8 . The system of claim 1 , comprising an aft end portion of the combustor liner having the inner and outer wall portions and the plurality of channels.

9 . The system of claim 1 , wherein each channel of the plurality of channels is a microchannel.

10 . The system of claim 1 , wherein the cross-sectional area of each channel of the plurality of channels decreases along the length from an inlet to an outlet of each channel of the plurality of channels.

11 . The system of claim 1 , comprising the gas turbine system a turbine and the combustor with the combustor liner.

12 . A system, comprising:
a combustor liner disposed about a combustion chamber of a combustor of a gas turbine system, wherein the combustor liner comprises:
an inner wall portion exposed to the combustion chamber;
an outer wall portion disposed about the inner wall portion; and
a plurality of channels between the inner and outer wall portions of the combustor liner, wherein each channel of the plurality of channels is configured to direct a coolant along the combustor liner to convectively cool the combustor liner, and each channel of the plurality of channels is a microchannel.

13 . The system of claim 12 , wherein a cross-sectional area of each channel of the plurality of channels varies along a length of each channel of the plurality of channels.

14 . The system of claim 13 , wherein the cross-sectional area of each channel of the plurality of channels decreases along the length from an inlet to an outlet of each channel of the plurality of channels.

15 . The system of claim 12 , wherein a cross-sectional area of the microchannel is less than or equal to approximately 6.45 square millimeters.

16 . The system of claim 12 , comprising an inlet guide having a ramp and an opening upstream from inlets of the plurality of channels, wherein the opening extends circumferentially about the combustor liner.

17 . The system of claim 12 , wherein the outer wall portion comprises a covering bonded to the inner wall portion along at least half a length of the covering, and the covering comprises a pre-sintered preform (PSP).

18 . A system, comprising:
a combustor liner disposed about a combustion chamber of a combustor of a gas turbine system, wherein the combustor liner comprises:
an inner wall portion exposed to the combustion chamber;
an outer wall portion disposed about the inner wall portion;
a plurality of channels between the inner and outer wall portions of the combustor liner, wherein each channel of the plurality of channels is configured to direct a coolant along the combustor liner to convectively cool the combustor liner; and
an inlet guide having a ramp and an opening upstream from inlets of the plurality of channels, wherein the ramp and the opening extend circumferentially about the combustor liner.

19 . The system of claim 18 , wherein each channel of the plurality of channels is a microchannel having a cross-sectional area that is less than or equal to approximately 6.45 square millimeters.

20 . The system of claim 18 , wherein a cross-sectional area of each channel of the plurality of channels decreases along a length from an inlet to an outlet of each channel of the plurality of channels.

Assignees

• Gen Electric

Inventors

• Simmons Scott Robert
• Chila Ronald James

Classifications

• Y02T50/60

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

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F23R3/002 Primary

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

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F05D2250/294

  grooved · CPC title