Cooling structure for gas turbine combustor
A gas turbine combustor having an improved cooling structure effective to efficiently suppress a possible occurrence of buckling in the combustion liner while exhibiting a convection cooling effect to the combustion liner, the gas turbine combustor includes a combustion liner having a combustion chamber defined therein and an outer peripheral surface forming a path of a compressed air, and a heat transfer enhancement structure provided on the outer peripheral surface of the combustion liner. The heat transfer enhancement structure referred to above is of a honeycomb construction defined by ribs protruding outwardly from the outer surface of the combustion liner. The honeycomb construction may be of a geometry in which hexagonal shapes, rhombic shapes, parallelogrammic shapes, bent rectangular shapes or triangular shapes are deployed next to each other.
1. A gas turbine combustor comprising:
a combustion liner having a combustion chamber defined therein and an outer peripheral surface forming a path of a compressed air; and
a heat transfer enhancement structure provided on the outer peripheral surface of the combustion liner and having a honeycomb construction defined by ribs protruding outwardly from the outer peripheral surface of the combustion liner,
wherein the honeycomb construction has a slanted rib arranged at a slanted cross angle relative to a direction of flow of the compressed air and a parallel rib extending parallel to the direction of flow of the compressed air, and
wherein the parallel rib protrudes a larger distance than that of the slanted rib.
2. The gas turbine combustor as claimed in claim 1 , wherein the honeycomb construction is of a geometry having an array of hexagonal shapes arranged next to each other.
3. The gas turbine combustor as claimed in claim 2 , wherein at least two vertexes opposed each other, forming one vertex pair out of three vertex pairs of the hexagonal shape, are opposed to each other in a direction along a direction of flow of the compressed air.
4. The gas turbine combustor as claimed in claim 3 , wherein the honeycomb construction has two of the parallel ribs, which forms two sides opposed to each other.
5. The gas turbine combustor as claimed in claim 1 , wherein the honeycomb construction is of a geometry having an array of rhombic shapes arranged next to each other.
6. The gas turbine combustor as claimed in claim 5 , wherein at least two vertexes opposed each other, forming one vertex pair out of two vertex pairs of the rhombic shape, are opposed to each other in a direction along a direction of flow of the compressed air.
7. The gas turbine combustor as claimed in claim 1 , wherein the honeycomb construction is of a geometry having an array of triangle shapes arranged next to each other.
8. The gas turbine combustor as claimed in claim 1 , wherein the honeycomb construction is of a geometry having an array of parallelogrammic shapes arranged next to each other, each shape having two sides opposed to each other and extending parallel to a direction of flow of the compressed air.
9. The gas turbine combustor as claimed in claim 1 , wherein the honeycomb construction is of a geometry having an array of bent rectangular shapes arranged next to each other, each shape having two sides opposed to each other and extending parallel to a direction of flow of the compressed air and the remaining two opposed sides so bent as to protrude towards an upstream side or a downstream side of the direction of flow of the compressed air.
10. The gas turbine combustor as claimed in claim 1 , further comprising a stand-alone rib provided at a center of each of cells defining the honeycomb construction and separate from each of sides of the honeycomb construction.