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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 cha

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.

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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; anda heat transfer enhancement structure provided on the outer peripheral surface of the combustion liner and having a honeycomb c

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; anda 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, andwherein 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.