THIMBLE INSERT OF COMBUSTOR LINER AND RELATED METHOD

摘要

PROBLEM TO BE SOLVED: To provide a gas turbine combustor liner cooling both upstream and downstream edges of air mixing holes. SOLUTION: The gas turbine combustor liner 10 has at least one circumferential row of air holes 16 for radially supplying air into combustion chambers inside of the liner. One or more air holes have thimbles 22 fixed inside of them and the thimble has an almost circular main body and a pair of lips 26, 28 extending from an inner end of the thimble in opposite upstream and downstream directions. COPYRIGHT: (C)2009,JPO&INPIT