Methods and apparatus for cooling gas turbine nozzles
AssigneeGeneral Electric Company
InventorsJoel Barreto, Andrew Charles Powis, Judd Dodge Tressler
Life of this patent
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Abstract
A turbine nozzle for a gas turbine engine includes a hollow airfoil vane including a first wall, a second wall, and a plurality of pins extending therebetween. The nozzle also includes at least one row of turbulators. The first and second walls are connected at a leading edge and a trailing edge. The first wall includes a plurality of slots extending towards the trailing edge, and the row of turbulators are substantially radially-aligned and extend between the plurality of slot and the pins.
Claims20
A method for cooling a turbine nozzle for a gas turbine engine, the nozzle including an airfoil, said method comprising:
- providing an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge such that a cavity is defined therebetween, the airfoil also including a plurality of pins extending between the first and second sidewalls, and at least one row of turbulators, the first sidewall including a plurality of slots in flow communication with the airfoil cavity and extending through the first sidewall towards the trailing of the airfoil;
- and
- channeling cooling air into the airfoil cavity such that the airflow is routed through the pins and then through the turbulators before exiting the airfoil through the first sidewall slots.
A turbine nozzle for a gas turbine engine, said nozzle comprising a hollow airfoil vane comprising a first wall, a second wall, a plurality of pins extending therebetween, and at least one row of turbulators, said first and second walls connected at a leading edge and a trailing edge, said first wall comprising a plurality of slots extending towards said trailing edge, said at least row of turbulators substantially radially-aligned and extending between said plurality of slot and said pins.
An airfoil for a gas turbine engine nozzle, said airfoil comprising a first sidewall and a second sidewall connected at a trailing edge such that a cavity is defined therebetween, each said sidewall extending radially between an airfoil root and tip, said first sidewall comprising a plurality of slots extending towards said trailing edge, said airfoil further comprising a plurality of pins and at least a row of turbulators, said pins extending between said first and second sidewalls, said turbulators extending between said pins and said slots.
Dependencies are inferred from the claim text.