| 摘要 |
A cooling assembly for a gas turbine system includes a turbine nozzle (28) having at least one channel (38,40) comprising a channel inlet (42) configured to receive a cooling flow (34) from a cooling source (12), wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet (44). Also included is an exit cavity (47) for fluidly connecting the channel outlet to a region (50) of a turbine component (32), wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure. |
