Cooling air recycling for gas turbine transition duct end frame and related method

• US 6,412,268 B1
• Filed: 04/06/2000
• Issued: 07/02/2002
• Est. Priority Date: 04/06/2000
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Sutcu, Maz, Cromer, Robert Harold, Bechtel, William Theodore
• Primary Examiner(s): Freay, Charles G.
• Assistant Examiner(s): Gartenberg, Ehud
• Application Number:
  US09/544,102
• Time in Patent Office: 817 Days
• Field of Search: 60/390.2, 607/60
• US Class Current: 60/772
• CPC Class Codes: F01D 25/12 Cooling
• 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 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127
• CPC Class Codes: F05D 2260/2214 by increasing the heat transfer surface
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/04 Air inlet arrangements

Abstract

A method of cooling a transition duct end frame in a gas turbine includes the steps of a) directing cooling air into the end frame from a region external of the transition duct and the impingement cooling sleeve; and b) redirecting the cooling air from the end frame into the annulus between the transition duct and the impingement cooling sleeve.

Claims

1. A transition duct assembly for a gas turbine that includes a compressor and at least one combustor, the duct assembly comprising:

a transition duct having opposite ends, one of said ends adapted to communicate with an inlet to a first turbine stage and another of said opposite ends adapted for connection to said at least one combustor;

an impingement cooling sleeve surrounding said transition duct with an annulus therebetween, said impingement cooling sleeve having a plurality of cooling holes formed therein for receiving discharge air from the compressor and directing the discharge air towards said at least one combustor;

said one end of said transition duct including an end frame, a forward edge of said impingement cooling sleeve received in said end frame;

said end frame having a first plurality of cooling holes axially beyond the forward edge of said impingement cooling sleeve, each cooling hole communicating at one end with space external of said impingement cooling sleeve; and

a second plurality of cooling holes in said end frame, each communication at one end with said annulus, and at an opposite end with said first plurality of cooling holes, said second plurality of holes oriented such that, in use, cooling air passing through said first plurality of cooling holes will be directed through said second plurality of cooling holes and mix with discharge air in said annulus directed towards said at least one combustor.

2. The assembly of claim 1 wherein said end frame is formed with a continuous closed recess about a forward edge thereof, and further wherein said first and second pluralities of cooling holes communicate with each other through said closed recess.

3. The assembly of claim 2 wherein said closed recess comprises a groove machined into said end frame and closed by a discrete seal component.

4. The assembly of claim 1 wherein said second plurality of holes are turbulated.

5. A method of cooling a transition duct end frame in a gas turbine with cooling air and recirculating the cooling air to a combustor of the gas turbine wherein an impingement cooling sleeve having a plurality of cooling apertures therein surrounds the transition duct creating an annulus therebetween, and wherein a forward end of said transition duct includes a transition duct end frame, with a forward flange of said impingement sleeve also received in the end frame, the method comprising:

a) directing cooling air into the end frame from a region external of said transition duct and said impingement cooling sleeve; and

b) redirecting said cooling air from said end frame into the annulus between the transition duct and the impingement cooling sleeve in a direction toward the combustor.

6. The method of claim 5 wherein step a) is carried out by providing a first plurality of cooling holes in said end frame, first ends of said cooling holes communicating with said region.

7. The method of claim 5 wherein step a) is further carried out by forming a continuous closed recess about the periphery of the end frame, with second ends of said cooling holes opening into said cooling holes opening into said closed recess.

8. The method of claim 5 wherein step b) is carried out by providing a second plurality of cooling holes in said end frame extending between said closed recess and said annulus.

9. The method of claim 8 and wherein step b) is further carried out by turbulating said second plurality of cooling holes.

10. A method of reducing combustion flame temperature in a gas turbine that includes a compressor, at least one combustor, at least one turbine stage and a transition duct connecting said at least one combustor with said at least one turbine stage, the transition duct having an integral end frame connected to said at least one turbine stage, the method comprising:

a) directing cooling air into and through the end frame from a region external of said transition duct to cool the end frame; and

b) redirecting said cooling air from the end frame to said at least one combustor.

11. The method of claim 10 wherein said transition duct is surrounded by an impingement cooling sleeve formed with a plurality of apertures, thus forming an annulus between the transition duct and the impingement sleeve, and further wherein discharge air from the compressor is utilized to impingement cool the transition duct via said plurality of apertures in said impingement sleeve, and further wherein, in step (b), the cooling air used to cool the end frame is redirected into the annulus for flow to said at least one combustor along with the compressor discharge air used to cool the transition duct.

12. A transition duct assembly for a gas turbine that includes a compressor and at least one combustor, the duct assembly comprising:

a transition duct having opposite ends, one of said ends adapted to communicate with an inlet to a first turbine stage and another of said opposite ends adapted for connection to said at least one combustor;

an impingement cooling sleeve surrounding said transition duct with an annulus therebetween, said impingement cooling sleeve having a plurality of cooling holes formed therein for receiving discharge air from the compressor and directing the discharge air into said annulus and then towards said at least one combustor;

a transition duct end frame integral with said one end of said transition duct, a forward edge of said impingement cooling sleeve received in said end frame; and

means for supplying cooling air into and through the end frame and for redirecting said cooling air to said at least one combustor.