Patent ID: 11859818
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 12:
13. The system of claim 12, comprising the gas turbine system having a turbine and the combustor with the combustor liner, the transition piece, the flow sleeve, and the intermediate flow passage, wherein a seal is disposed between the aft end portion of the combustor liner and the upstream end portion of the transition piece, wherein a downstream end portion of the transition piece is configured to output the combustion gas to the turbine, wherein the flow direction of the coolant flow is oriented in the downstream direction of the main flow of combustion gas through the combustor, wherein the opening and the ramp are configured to reverse flow directions from the flow through the intermediate flow passage in the upstream direction to the coolant flow through the plurality of channels in the downstream direction.