| 摘要 |
<p>PROBLEM TO BE SOLVED: To provide cooling systems which prevent reduction in cooling effectiveness due to a cross flow in a transition piece and a liner of a combustor of a combustion turbine.SOLUTION: A combustor 14 of a combustion turbine engine is described. The combustor may include an inner radial wall 24, 25, which defines a combustion chamber downstream of a primary fuel nozzle, and an outer radial wall 26, 27, which surrounds the inner radial wall so as to form a flow annulus 28 between the inner and outer radial walls, and the combustor may include a socket 33 extending from the outer radial wall into the flow annulus. The socket 33 may include: a mouth formed through the outer radial wall; a floor offset by a predetermined distance from an outboard surface of the inner radial wall; impingement ports formed through the floor; and an axial nozzle.</p> |
