Core compartment vent during engine shutdown to reduced bowed rotor start
AssigneeRtx Corporation
InventorAnthony R. Bifulco
Life of this patent
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Abstract
A core section and nacelle assembly of a gas turbine engine includes a compressor located at an engine central longitudinal axis, a core case enclosing the compressor, and a nacelle located radially outboard of the core case and defining a core compartment between the nacelle and the core case. One or more vent openings are located in the nacelle to circulate a cooling airflow through the core compartment, and one or more fans are positioned at the one or more vent openings to urge the cooling airflow through the one or more vent openings to cool the core compartment.
Claims7
A method of cooling a core section of a gas turbine engine, comprising:
- providing one or more vent openings in a nacelle of the gas turbine engine, the nacelle enclosing the core section of the gas turbine engine including a core case enclosing at least a compressor;
- providing one or more fans at each vent opening of the one or more vent openings;
- selectably operating the one or more fans to urge an airflow through the one or more vent openings to ventilate a core compartment defined between the nacelle and the core case;
- and
- cooling the core section via ventilation of the core compartment;
- wherein the one or more vent openings are one or more cooling scoops, each of the one or more cooling scoops including a scoop inlet having an scoop intake disposed at least partially across a bypass flowpath of the gas turbine engine.
Dependencies are inferred from the claim text.