GAS TURBINE COMBUSTOR

1 . A combustor for a gas turbine comprising:

a front panel;

an elongated sleeve with a first end and a second end; and

a burner mounted in the sleeve, wherein the second end of the sleeve seallessly mounted on the front panel.

2 . The combustor of claim 1 wherein the burner is movable in an axial direction inside a sleeve and relative to the sleeve during operation of the combustor.

3 . The combustor of claim 1 wherein the burner is slidably mounted in the sleeve so as to enable axial adjustment of the burner within the sleeve.

4 . The combustor of claim 1 wherein the sleeve, at the second end, has a bell shaped.

5 . The combustor of claim 1 , wherein the burner comprises:

a burner body; and

a conically expanding swirl shell, extending from the body, having a narrow first end and a wider distal second end, wherein the sleeve shrouds the swirl shell.

6 . The combustor of claim 1 wherein the burner comprises:

a burner ring having:

a first end towards an axial upstream end of the burner;

a second distal end towards an axial downstream end of the burner; and

an outer surface,

wherein the burner ring is fixingly mounted to the swirl shell second end on an inner surface of the burner ring at a point between the burner ring first end and the burner ring second end so as to a least partially shroud the swirl shell.

7 . The combustor of claim 6 further comprising a seal for sealing a cavity formed between the burner ring and the sleeve wherein the seal is located on either the burner ring or the sleeve.

8 . The combustor of claim 7 wherein the seal is a labyrinth and piston ring seal.

9 . The combustor of claim 7 wherein the seal is located on the outer surface of the burner ring.

10 . The combustor of claim 7 wherein the seal is located towards the first end of the burner ring.

11 . The combustor of claim 8 wherein the seal is located on the outer surface of the burner ring towards the burner ring first end.

12 . The combustor of claim 7 wherein the sleeve comprises a plurality of purge holes therethrough configured and located such that the purge holes are capable of directing purge gas into an annular gap formed between the burner ring outer surface and the sleeve between the seal and the burner ring second end.

13 . The combustor of claim 12 wherein the plurality of purge holes circumscribe the sleeve.

14 . The combustor of claim 5 wherein the burner body further comprises a lance, axially extending through the burner body and out from the burner body into a cavity formed in the swirl shell, for oil premix and gas pilot injection.

15 . The combustor of claim 1 wherein the combustor further comprises a plurality of sleeves and burners, wherein at least two of the burners in the sleeves are axially staggered.