Gas turbine combustion liner with triangular heat transfer element
View Patent ↗A gas turbine combustor achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. The structure of the gas turbine combustor includes a plurality of circularity recesses formed on a side of an annular passage on a partial area of a combustion liner that requires cooling. Each of the circularity recesses has a rectangular surface forming a convex at a right angle with respect to a flowing direction of combustion air. The circularity recesses form a rectangular triangle having an oblique surface facing upstream of the flowing direction of the combustion air.
1. A gas turbine combustor comprising:
a combustion liner configured to form a combustion chamber thereinside;
an outer casing disposed on an outer peripheral side of the combustion liner; and
an annular passage, formed between the combustion liner and the outer casing, configured to allow a heat-transfer medium to flow therethrough, wherein
the combustion liner has a circularity recess on a side of the annular passage, the circularity recess having a cross section in a rectangular triangle shape along a flowing direction of the heat transfer medium, the flowing direction of the heat transfer medium being substantially parallel to a central axis of the combustion liner, a surface at a right angle with respect to the flowing direction of the heat-transfer medium, and an oblique surface inclined with respect to the flowing direction of the heat transfer medium, the surface at the right angle and the oblique surface forming a convex, wherein the surface at the right angle and the oblique surface form edges of the rectangular triangle shape;
a connection point between the surface at the right angle and the oblique surface forms an edge of the combustion liner, the circularity recess forms a concavity, on an inner peripheral surface of the combustion liner exposed to a combustion gas, as seen from the combustion chamber, and
the oblique surface faces upstream of the flowing direction of the heat-transfer medium and the surface at the right angle faces downstream of the flowing direction of the heat-transfer medium.
2. The gas turbine combustor according to claim 1 , wherein the circularity recess has a plurality of holes of jet flow formed in the surface at the right angle thereof, each of the plurality of holes of jet flow having a central axis extending in parallel with the central axis of the combustion liner.
3. The gas turbine combustor according to claim 1 , wherein the circularity recess has a plurality of holes of jet flow formed in the surface at the right angle thereof, each of the plurality of holes of jet flow having a central axis inclined with respect to the central axis of the combustion liner.