Cooling features for a gas turbine engine transition duct

Patent metadata

Field	Value
Publication number	US-10801341-B2
Application number	US-201516062651-A
Country	US
Kind code	B2
Filing date	Dec 15, 2015
Priority date	Dec 15, 2015
Publication date	Oct 13, 2020
Grant date	Oct 13, 2020

Abstract

A gas engine turbine has a transition duct ( 100 ) that has improved cooling features and a method for forming the cooling features. A continuous exit section cooling channel ( 130 ) is formed through the transition duct panel ( 112 ), the exit frame ( 114 ) and the connection ( 116 ). The continuous exit section cooling channel ( 130 ) reduces the need for effusion channels in the transition duct. The continuous exit section cooling channel ( 130 ) further reduces costs and improves the emissions associated with the transition duct ( 100 ) of the gas engine turbine.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a transition duct having a transition duct panel, and an exit frame connected to the transition duct panel via a connection; and
a continuous exit section cooling channel formed in the transition duct panel through the connection and further through the exit frame to an outlet located on a face of the exit frame,
wherein the continuous exit section cooling channel comprises a transition duct panel channel, a connection channel and an exit frame channel,
wherein the exit frame channel is connected to the connection channel,
wherein the continuous exit section cooling channel further comprises a second exit frame channel connected to a second connection channel, and
wherein the second connection channel is separate from the connection channel.

2. The gas turbine engine claim 1 , further comprising a channel inlet formed within the transition duct panel and connected to the transition duct panel channel.

3. The gas turbine engine of claim 1 , wherein the exit frame channel and the second exit frame channel are connected in fluid communication with the transition duct panel channel.

4. The gas turbine engine of claim 1 , further comprising an angled channel formed within the transition duct panel connecting the second connection channel to the transition duct panel channel.

5. The gas turbine engine of claim 1 , wherein a plurality of continuous exit section cooling channels are formed.

6. The gas turbine engine of claim 1 , wherein the connection has no connection effusion holes.

7. A method for forming a continuous exit section cooling channel for a gas turbine combustor comprising:
forming a transition duct panel channel in a transition duct panel;
connecting an exit frame to the transition duct panel;
forming an outlet and an exit frame channel through the exit frame and a connection channel through the connection; and
connecting the exit frame channel, the connection channel and the transition duct panel channel to form the continuous exit section cooling channel,
wherein the continuous exit section cooling channel further comprises a second exit frame channel connected to a second connection channel, and
wherein the second connection channel is separate from the connection channel.

8. The method of claim 7 , further comprising forming a channel inlet within the transition duct panel and connecting the channel inlet to the transition duct panel channel.

9. The method of claim 7 , wherein the exit frame channel and the second exit frame channel are connected to the transition duct panel channel.

10. The method of claim 7 , further comprising forming an angled channel within the transition duct panel and connecting the second connection channel to the transition duct panel channel.

11. The method of claim 7 , wherein a plurality of continuous exit section cooling channels are formed.

12. The method of claim 7 , wherein the connection has no connection effusion holes.

13. A transition duct comprising:
a transition duct panel;
an exit frame connected to the transition duct panel via a connection; and
a continuous exit section cooling channel formed in the transition duct panel through the connection and further through the exit frame to an outlet located on a face of the exit frame,
wherein the continuous exit section cooling channel comprises a transition duct panel channel, a connection channel and an exit frame channel,
wherein the exit frame channel is connected to the connection channel,
wherein the continuous exit section cooling channel further comprises a second exit frame channel connected to a second connection channel, and
wherein the second connection channel is separate from the connection channel.

14. The transition duct of claim 13 , further comprising a channel inlet formed within the transition duct panel and connected to the transition duct panel channel.

15. The transition duct of claim 13 , wherein the exit frame channel and the second exit frame channel are connected to the transition duct panel channel.

16. The transition duct of claim 13 , wherein a plurality of continuous exit section cooling channels are formed.

Assignees

• Siemens Ag

Inventors

• Kumar Manish
• Cassar Daniel

Classifications

• F05D2230/60

  Assembly methods · CPC title

• F05D2260/20

  Heat transfer, e.g. 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

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title