Combustion liner for a gas turbine engine including heat transfer columns to increase cooling of a hula seal at the transition duct region

1. A combustion duct assembly comprising:

a transition duct having an inner wall;

a combustion liner centered on an axis, with the axis defining an upstream end and a downstream end, and the combustion liner having a hula seal at the downstream end that is forced within the inner wall of said transition duct, said combustion liner being held within said transition duct by said hula seal, but allowed to move relative to said transition duct; and

said combustion liner being formed with heat transfer columns adjacent said downstream end of the combustion liner, and radially inwardly of said hula seal, with said heat transfer columns creating a tortuous path for cooling airflow.

2. The assembly as set forth in claim 1 , wherein said hula seal is fixed to said combustion liner at said downstream end, and has spring fingers extending towards said upstream end, with said spring fingers biased against said combustion liner.

3. The assembly as set forth in claim 1 , wherein an outer housing is secured radially outwardly of said combustion liner and to an outer surface of said transition duct.

4. The assembly as set forth in claim 1 , wherein said columns are cylindrical.

5. The assembly as set forth in claim 1 , wherein said columns are arranged in an array, with rows of said columns extending both along an axial dimension of said combustion liner, and along a circumferential dimension.

6. The assembly as set forth in claim 1 , wherein a chamber is formed in said combustion liner at said downstream end, and between radially inner and outer walls, with said columns formed on said inner wall of said combustion liner.

7. The assembly as set forth in claim 6 , wherein said hula seal is secured to said outer wall of said combustion liner.

8. A combustion liner comprising:

a liner body extending along an axis between an upstream end and a downstream end, and having a hula seal at the downstream aft end;

said liner body being formed with heat transfer columns adjacent said downstream end, and radially inwardly of said hula seal; and

with said heat transfer columns creating a tortuous airflow path for cooling the air.

9. The combustion liner as set forth in claim 8 , wherein said hula seal is fixed to said liner body at said downstream end, and has spring fingers extending towards said upstream end, with said spring fingers biased against an outer periphery of said liner body.

10. The combustion liner as set forth in claim 8 , wherein said columns are cylindrical.

11. The combustion liner as set forth in claim 8 , wherein said columns are arranged in an array, with rows of said columns extending both along an axial dimension of said combustion liner, and along a circumferential dimension.

12. The combustion liner as set forth in claim 8 , wherein a chamber is formed in said combustion liner at said downstream end, and between radially inner and outer walls, with said columns formed on said inner wall.

13. The combustion liner as set forth in claim 12 , wherein said hula seal is secured to said outer wall.

14. A combustion duct assembly comprising:

a transition duct having an inner wall;

a combustion liner centered on an axis, with the axis defining an upstream end and a downstream end, and the combustion liner having a hula seal at the downstream end that is forced within the inner wall of said transition duct, said combustion liner being held within said transition duct by said hula seal, but allowed to move relative to said transition duct;

said combustion liner being formed with heat transfer columns adjacent said downstream end of the combustion liner, and radially inwardly of said hula seal; and

said columns are arranged in an array, with rows of said columns extending both along an axial dimension of said combustion liner, and along a circumferential dimension.

15. The assembly as set forth in claim 14 , wherein said heat transfer columns create a tortuous airflow path.