| 摘要 |
A combustor for a turbine includes a combustor liner (12); a first flow sleeve (28) surrounding the liner, the flow sleeve having a plurality of rows of cooling holes (34) formed about a circumference of flow sleeve; and a transition piece connected to the combustor liner and the flow sleeve and adapted to carry hot combustion gases to a stage of the turbines. The transition piece is surrounded by a second flow sleeve which directs cooling air to the transition piece. One of the plurality of rows of cooling holes in the first flow sleeve is located adjacent the transition piece, and cooling conduits (36) are mounted in the cooling holes of at least the first of the plurality of rows of cooling holes to direct impingement cooling air against the surface of the liner while diverting crossflow cooling air around the impingement cooling air. A related method of cooling a combustor liner of a gas turbine combustor with a flow sleeve surrounding the liner in substantially concentric relationship therewith includes the steps of a) providing a plurality of axially spaced rows of cooling holes in the flow sleeve, each row extending circumferentially of the flow sleeve, a first of the rows adjacent a forward or downstream end of the flow sleeve; b) locating a plurality of cooling conduits in the cooling holes of at least the first of the rows, the cooling conduits extending radially towards, but not engaging, the liner; and c) supplying cooling air to the annulus such that the cooling conduits direct the cooling air against the liner. <IMAGE> |
