Cooling assembly for a gas turbine system
AssigneeGeneral Electric Company
InventorsDavid Richard Johns, Kevin Richard Kirtley
Life of this patent
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Abstract
A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a 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. Also included is an exit cavity for fluidly connecting 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.
Claims20
A cooling assembly for a gas turbine system comprising:
- a turbine nozzle having at least one channel comprising a channel inlet configured to receive a 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;
- and
- an exit cavity for fluidly connecting 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.
A cooling assembly for a gas turbine system comprising:
- a turbine nozzle disposed between a radially inner segment and a radially outer segment, the turbine nozzle having a plurality of channels each comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the plurality of channels directs the cooling flow through the turbine nozzle in a radial direction to a channel outlet;
- a plurality of rotor blades rotatably disposed between a rotor shaft and a stationary turbine shroud assembly supported by a turbine casing, wherein the stationary turbine shroud assembly is located downstream of the turbine nozzle;
- and
- an exit cavity fully enclosed by a hood segment for fluidly connecting the channel outlet to the stationary turbine shroud assembly, wherein the cooling flow is transferred to the stationary turbine shroud assembly.
A gas turbine system comprising:
- a compressor for distributing a cooling flow at a high pressure;
- a turbine casing operably supporting and housing a first stage turbine nozzle having a plurality of channels for receiving the cooling flow for cooling the first stage turbine nozzle and directing the cooling flow radially through the first stage turbine nozzle;
- a first turbine rotor stage rotatably disposed radially inward of a first stage turbine shroud assembly, wherein the first stage turbine shroud assembly is disposed downstream of the first stage turbine nozzle;
- and
- an enclosed exit cavity fluidly connecting at least one of the plurality of channels to the first stage turbine shroud assembly for delivering the cooling flow to the first stage turbine shroud assembly.
Dependencies are inferred from the claim text.