Patent ID: 9670785
Date: 2017-06-06
CPC Classifications: F01D,F05D

Claim:
1. A cooling assembly for a gas turbine system comprising: a turbine nozzle extending between opposite first and second end portions configured to mount in a hot gas path between a turbine casing and a central structure, wherein the turbine nozzle is configured to route a cooling flow only from the first end portion to the second end portion, the turbine nozzle comprises at least one channel comprising a channel inlet in the first end portion configured to receive a the cooling flow from a cooling source, 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 in the second end portion; a hood surrounding an exit cavity and configured to fluidly connect the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure, wherein the hood is configured to mount in a space between inner and outer casing walls of the turbine casing, and the hood turns from a radially outward direction to a direction along the hot gas path from the channel outlet to the turbine component.