Sequential liner for a gas turbine combustor
View Patent ↗The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.
1. A sequential liner for a gas turbine combustor, comprising:
a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall; and
the sequential liner outer wall having a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face,
the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole facing the cooling channel and not the sequential liner inner wall to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face.
2. The sequential liner of claim 1 , comprising:
at least one rib between the sequential liner inner wall and the sequential liner outer wall of the first adjacent face for directing the convective cooling flow.
3. The sequential liner of claim 2 , wherein the at least one rib extends across part of the distance between the sequential liner outer wall and the sequential liner inner wall.
4. The sequential liner of claim 2 , in which at least one of the one or more ribs is substantially parallel to a gas turbine combustor hot gas flow.
5. The sequential liner of claim 2 , comprising:
a plurality of ribs, wherein each rib has a downstream end and an upstream end relative to the flow of cooling air, and wherein the upstream ends of the ribs are further apart from one another than the downstream ends of the ribs.
6. The sequential liner of claim 5 , wherein one or more of the ribs are curved.
7. The sequential liner of claim 1 , wherein each of the first convective cooling hole and the second convective cooling hole comprise:
at least two separate holes adjacent to one another.
8. The sequential liner of claim 1 , wherein the longest distance across each convective cooling hole is at least twice the length of the shortest distance across each respective convective cooling hole.
9. The sequential liner of claim 1 , comprising:
a plurality of impingement cooling holes in the sequential liner outer wall.
10. The sequential liner of claim 1 , wherein the plurality of impingement cooling holes are smaller than the first convective cooling holes.
11. A gas turbine comprising the sequential liner of claim 1 .
12. A method of cooling a sequential liner for a gas turbine combustor having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall, the sequential liner outer wall having a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to face the cooling channel and not the sequential liner inner wall to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face, the method comprising:
feeding cooling air through the convective cooling holes into the sequential liner cooling channel; and
convectively cooling the sequential liner inner wall with the cooling air.
13. A method of retrofitting a gas turbine having a sequential liner with a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall, the method comprising:
removing the sequential liner outer wall; and
adding a new sequential liner outer wall, the sequential liner outer wall having a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to face the cooling channel and not the sequential liner inner wall to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face.
14. The method of claim 13 , comprising:
attaching at least one rib to the sequential liner inner wall before adding a new sequential liner outer wall.