Turbomachine including a ceramic matrix composite (CMC) bridge

• US 8,347,636 B2
• Filed: 09/24/2010
• Issued: 01/08/2013
• Est. Priority Date: 09/24/2010
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Butkiewicz, Jeffrey John, Garcia-Crespo, Andres Jose, Simpson, Stanley Frank
• Primary Examiner(s): Wongwian, Phutthiwat
• Application Number:
  US12/889,860
• Publication Number:
  US 20120073304A1
• Time in Patent Office: 837 Days
• Field of Search: 60752-760, 60796-800, 415/9, 415/92, 415/110, 415/134, 415136-139, 415/191, 415/197, 415/199.5, 415/200, 415/202
• US Class Current: 60/800
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: F23R 2900/00012 Details of sealing devices
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means

Abstract

A turbomachine includes a turbine section including a turbine inlet. A transition piece includes a transition piece inlet and a transition piece outlet. A ceramic matrix composite (CMC) bridge member links the transition piece outlet and the turbine inlet.

Claims

1. A turbomachine comprising:

a turbine section including a turbine inlet;

a combustor transition piece including a transition piece inlet and a transition piece outlet;

a ceramic matrix composite (CMC) bridge member linking the transition piece outlet and the turbine inlet, the CMC bridge member including an inlet portion having a first flange operatively connected to the combustor transition piece outlet and an outlet portion having a second flange operatively connected to the turbine inlet; and

a seal member provided on one of the transition piece outlet and the turbine inlet, the seal member engaging one of the first and second flanges.

2. The turbomachine according to claim 1, wherein the CMC bridge member includes an outer surface and an inner surface, the inner surface having a flow guide that directs combustion gases into the turbine inlet.

3. The turbomachine according to claim 2, wherein the flow guide is configured and disposed to direct combustion gases away from an end wall portion of the turbine inlet.

4. The turbomachine according to claim 1, wherein the first flange extends about the inlet portion and a second flange extends about the outlet portion.

5. The turbomachine according to claim 4, wherein one of the first and second flanges is fastened to the corresponding one of the combustor and the turbine section.

6. The turbomachine according to claim 5, wherein the seal member comprises a flexible seal member.

7. The turbomachine according to claim 6, further comprising:

a retaining ring operatively connected to the turbine section, the at least one bridge member being secured to the retaining ring through the mounting element.

8. The turbomachine according to claim 7, further comprising:

a first seal member arranged between the first flange and the combustor and a second seal member arranged between the second flange and the turbine section.

9. The turbomachine according to claim 4, wherein the CMC bridge member includes a mounting element projecting radially outward from the body between the first and second flanges.

10. The turbomachine according to claim 1, wherein the CMC bridge member is formed from one of a silicon carbide-silicon carbide (SiC—

SiC) composite, oxide-oxide composite, and silicon nitride composite material.

11. The turbomachine according to claim 1, further comprising:

an air channel arranged at the transition piece outlet, the air channel guiding a fluid flow onto the CMC bridge member.

12. A method of delivering combustion gases from a turbomachine combustor to a turbine section of a turbomachine, the method comprising:

producing combustion gases in the turbomachine combustor;

directing the combustion gases into a combustor transition piece;

guiding the combustion gases along a ceramic matrix composite (CMC) bridge member linking the transition piece and the turbine section; and

passing the combustion gases from the CMC bridge member into the turbine section, the CMC bridge member including an inlet portion having a first flange operatively connected to a combustor transition piece outlet and an outlet portion having a second flange operatively connected to a turbine inlet; and

sealing an interface between the CMC bride member and one of the transition piece and the turbine section to prevent compressor discharge air from entering into a turbine inlet of the turbine section.

13. The method of claim 12, wherein, guiding the combustion gases through the CMC bridge member includes diverting the combustion gases away from an end wall portion of the turbine section.

14. A turbomachine component comprising:

a ceramic matrix composite (CMC) bridge member configured and disposed to link a combustor transition piece and a turbine section of a turbomachine, the CMC bridge member including an inlet portion having a first flange configured and disposed to operatively connect to a combustor transition piece outlet and an outlet portion having a second flange configured and disposed to operatively connect to a turbine inlet; and

a seal member provided on one of the transition piece outlet and the turbine inlet, the seal member engaging one of the first and second flanges.

15. The turbomachine component according to claim 14, wherein the CMC bridge member includes an outer surface and an inner surface, the inner surface having a flow guide.

16. The turbomachine component according to claim 14, wherein the first flange extends about the inlet portion and the second flange extends about the outlet portion.

17. The turbomachine component according to claim 16, wherein the CMC bridge member includes a mounting element projection radially outward from the body between the first and second flanges.

18. The turbomachine according to claim 14, wherein the CMC bridge member is formed from one of a silicon carbide-silicon carbide (SiC—

SiC) composite, oxide-oxide composite, and silicon nitride composite material.