초록 ▼

Two concentric, partially overlapping annular plates mounted on a parallel support plate are provided for partly defining the gas flow path and for shielding bearings, etc. from hot combustion gases in a radial flow gas turbine. The radially outer plate is cooled by compressed air channeled past the

Two concentric, partially overlapping annular plates mounted on a parallel support plate are provided for partly defining the gas flow path and for shielding bearings, etc. from hot combustion gases in a radial flow gas turbine. The radially outer plate is cooled by compressed air channeled past the plate surface opposite the combustion gases. The compressed air is metered to achieve a temperature distribution decreasing in the radially inward direction for providing sealing contact between the outer edge and the support plate. The radially inner plate is cooled by film cooling using the compressed air exiting the outer plate channel in the vicinity of the overlap.

대표청구항 ▼

Heat shield apparatus for a radial inflow gas turbine, the turbine having a plurality of blades mounted on a hub for rotation about an axis, the combustion gases entering the turbine at an inlet essentially in the radial direction and leaving at an outlet essentially in the axial direction, the appa

Heat shield apparatus for a radial inflow gas turbine, the turbine having a plurality of blades mounted on a hub for rotation about an axis, the combustion gases entering the turbine at an inlet essentially in the radial direction and leaving at an outlet essentially in the axial direction, the apparatus comprising: (a) a first shield member in the form of an annular plate positioned concentric with the hub axis and immediately adjacent the turbine inlet; (b) a second shield member in the form of an annular plate positioned concentric with the hub axis, said second shield member being essentially co-planar with said first shield member and being positioned adjacent to both said first shield member and the hub, said first and second shield members having respective shielding surfaces facing the combustion gas and the turbine outlet and defining, in part, the combustion gas flow path past the turbine blades; (c) means for supporting said first and second shield members; and (d) means cooperating with said support means for cooling said first and second shield members, wherein said support means includes an annular plate member positioned concentric with the hub axis and axially adjacent said first and second shield members, at least some portions of said support plate being spaced from said first shield member, and wherein said cooling means includes (i) a first source of pressurized gas at a low temperature, relative to the combustion gas temperature, and (ii) means for channeling said pressurized low temperature first gas into the space between said first shield member and said support plate for cooling the surface of said first shield member opposite said first shield member shielding surface, and wherein a radially inner edge of said first shield member and an adjacent radially outer edge of said second shield member form an intershield gap, and wherein the heat shield apparatus further includes means for providing a flow path for said pressurized first coolant gas between said first and said second shield members to cooperate with said intershield gap, said first coolant gas flow through said intershield gap for film cooling the shielding surface of said second shield member.