Aft frame assembly for gas turbine transition piece

Patent metadata

Field	Value
Publication number	US-10684016-B2
Application number	US-201715783291-A
Country	US
Kind code	B2
Filing date	Oct 13, 2017
Priority date	Oct 13, 2017
Publication date	Jun 16, 2020
Grant date	Jun 16, 2020

Abstract

An aft frame assembly for a gas turbine transition piece has a main body with an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface. A plurality of feed hole inlets are located on the upstream facing surface. Each of the feed hole inlets are coupled to one of a plurality of cooling channels passing through the main body towards the radially inner facing surface. A plurality of microchannels are formed near the radially inner facing surface and extend at least partially along the downstream facing surface. The cooling channels are connected to and terminate in the microchannels. A pre-sintered preform is located on the radially inner facing surface of the main body.

First claim

The invention claimed is:

1. An aft frame assembly for a gas turbine transition piece, the aft frame assembly comprising:
a main body comprising an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface;
a corner disposed between the radially inner facing surface and the downstream facing surface;
a plurality of feed hole inlets located on the upstream facing surface, each of the plurality of feed hole inlets coupled to one of a plurality of cooling channels passing through the main body towards the radially inner facing surface;
a plurality of microchannels formed near the radially inner facing surface and extending substantially axially along the radially inner facing surface and substantially radially along the downstream facing surface, wherein the plurality of microchannels curve around the corner, the plurality of cooling channels connected to and terminating in the plurality of microchannels; and
a pre-sintered preform located on the radially inner facing surface of the main body.

2. The aft frame assembly of claim 1 , the plurality of microchannels formed in the main body.

3. The aft frame assembly of claim 2 , wherein each microchannel of the plurality of microchannels exits in a respective exit hole located on the downstream facing surface or the radially outer facing surface.

4. The aft frame assembly of claim 1 , a thermal barrier coating formed on the pre-sintered preform.

5. The aft frame assembly of claim 4 , wherein a circumferential distance between two adjacent microchannels of the plurality of microchannels varies in a radially outward direction based on a circumferential location of each of the two adjacent microchannels of the plurality of microchannels within the aft frame.

6. The aft frame assembly of claim 1 , the plurality of microchannels formed in the pre-sintered preform.

7. The aft frame assembly of claim 6 , wherein each microchannel of the plurality of microchannels exits in a respective exit hole located on the downstream facing surface or the radially outer facing surface.

8. The aft frame assembly of claim 7 , wherein a circumferential distance between two adjacent microchannels of the plurality of microchannels varies in a radially outward direction based on a circumferential location of each of the two adjacent microchannels of the plurality of microchannels within the aft frame.

9. A transition piece assembly having an aft frame assembly, the aft frame assembly comprising:
a main body comprising an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface;
a corner disposed between the radially inner facing surface and the downstream facing surface;
a plurality of feed hole inlets located on the upstream facing surface, each of the plurality of feed hole inlets coupled to one of a plurality of cooling channels passing through the main body towards the radially inner facing surface;
a plurality of microchannels formed near the radially inner facing surface and extending substantially axially along the radially inner facing surface and substantially radially along the downstream facing surface wherein the plurality of microchannels curve around the corner, the plurality of cooling channels connected to and terminating in the plurality of microchannels;
a pre-sintered preform located on the radially inner facing surface of the main body; and
wherein the plurality of microchannels are formed in the main body or the pre-sintered preform.

10. The transition piece assembly of claim 9 , wherein each microchannel of the plurality of microchannels exits in respective exit hole located on the downstream facing surface or the radially outer facing surface.

11. The transition piece assembly of claim 9 , a thermal barrier coating formed on the pre-sintered preform.

12. The transition piece assembly of claim 11 , wherein a circumferential distance between two adjacent microchannels of the plurality of microchannels varies in a radially outward direction based on a circumferential location of each of the two adjacent microchannels microchannels of the plurality of microchannels within the aft frame.

13. A gas turbine comprising:
a compressor;
a combustion section disposed downstream from the compressor, the combustion section being in fluid communication with the compressor;
a turbine disposed downstream from the combustion section;
the combustion section comprising an aft frame assembly having a main body, the main body comprising:
an upstream facing surface, a downstream facing surface, a radially outer facing surface and a radially inner facing surface;
a corner disposed between the radially inner facing surface and the downstream facing surface;

a plurality of feed hole inlets located on the upstream facing surface, each of the plurality of feed hole inlets coupled to one of a plurality of cooling channels passing through the main body towards the radially inner facing surface;
a plurality of microchannels formed near the radially inner facing surface and extending substantially axially along the radially inner facing surface and substantially radially along the downstream facing surface, wherein the plurality of microchannels curve around the corner, the plurality of cooling channels connected to and terminating in the plurality of microchannels;
a pre-sintered preform located on the radially inner facing surface of the main body; and
wherein the plurality of microchannels are formed in the main body or the pre-sintered preform.

14. The gas turbine of claim 13 , wherein each microchannel of the plurality of microchannels exits in a respective exit hole located on the downstream facing surface or the radially outer facing surface.

15. The gas turbine of claim 13 , a thermal barrier coating formed on the pre sintered preform.

16. The gas turbine of claim 15 , wherein a circumferential distance between two adjacent microchannels of the plurality of microchannels varies in a radially outward direction based on a circumferential location of each of the two adjacent microchannels of the plurality of microchannels within the aft frame.

17. The aft frame assembly of claim 1 , wherein the plurality of microchannels have a constant depth and a constant width.

Assignees

• Gen Electric

Inventors

• Simmons Scott Robert
• Chila Ronald James
• Mcmahan Kevin Weston
• Chen Wei
• Davis Iii Charles Lewis

Classifications

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2230/22

  by sintering · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F01D25/12

  Cooling · CPC title

• F01D9/023 Primary

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title