Assemblies and apparatus related to combustor cooling in turbine engines

摘要

A combustor of a combustion turbine engine is described. The combustor may include an inner radial wall, which defines a combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall so to form a flow annulus therebetween, and the combustor may include a socket extending from the outer radial wall into the flow annulus. The socket may include: a mouth formed through the outer radial wall; a floor offset a predetermined distance from an outboard surface of the inner radial wall; impingement ports formed through the floor; and an axial nozzle.

主权项

1. A cooling configuration within a combustor of a combustion turbine engine, wherein the combustor includes an inner radial wall, which defines a combustion chamber downstream of a primary fuel nozzle, and an outer radial wall, which surrounds the inner radial wall so to form a flow annulus therebetween, the cooling assembly comprising:
a socket extending from the outer radial wall into the flow annulus; wherein the socket includes:
a mouth formed through the outer radial wall;a floor offset a predetermined, distance from an outboard surface of the inner radial wall;impingement ports formed through the floor; andan axial nozzle;wherein the axial nozzle comprises:
a tube that extends through a hollow interior of the socket, the axial nozzle comprising an approximate axial orientation in relation to a center axis of the combustor; andwherein the tube of the axial nozzle is canted in an inboard direction.