Combined inlet laminar and thrust reverser cascade efflux flow control system
AssigneeUnited Technologies Corporation
InventorNigel David Sawyers-Abbott
Life of this patent
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Abstract
A nacelle assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan nacelle bounding a bypass flow path. The fan nacelle includes a first nacelle section and a second nacelle section. The second nacelle section includes a moveable portion movable relative to a forward portion to define a secondary flow passage. The first nacelle section includes an inlet lip. A thrust reverser is configured to selectively communicate a portion of bypass airflow between the bypass flow path and the secondary flow passage. A pump is configured to selectively communicate airflow between the inlet lip and the secondary flow passage. A method of flow distribution for a gas turbine engine is also disclosed.
Claims21
A nacelle assembly for a gas turbine engine, comprising:
- a fan nacelle bounding a bypass flow path, the fan nacelle including a first nacelle section and a second nacelle section, the second nacelle section including a moveable portion movable relative to a forward portion to define a secondary flow passage, the first nacelle section including an inlet lip;
- a thrust reverser configured to selectively communicate a portion of bypass airflow between the bypass flow path and the secondary flow passage;
- and
- a pump configured to selectively communicate airflow between the inlet lip and the secondary flow passage, wherein the pump is configured to draw airflow from surfaces of the inlet lip, and the pump is configured to communicate airflow from the inlet lip to the second nacelle section, and wherein the pump is a bi-directional pump.
A gas turbine engine, comprising:
- a core cowling arranged at least partially about a compressor section, a combustor section and a turbine section;
- a fan nacelle arranged at least partially about the core cowling to define a bypass flow path, the fan nacelle including a first nacelle section having an inlet lip and a second nacelle section, the second nacelle section including moveable portion movable relative to a forward portion to define a secondary flow passage;
- a thrust reverser positioned axially between the first nacelle section and the second nacelle section, the thrust reverser including a cascade configured to direct bypass airflow through the secondary flow passage;
- and
- a bi-directional pump configured to selectively communicate airflow between surfaces of the inlet lip and surfaces of the secondary flow passage.
A method of flow distribution for a gas turbine engine, comprising:
- providing a first nacelle having an inlet lip;
- providing a second nacelle including a forward portion and a moveable portion selectively defining a secondary flow passage;
- causing a flow device to draw airflow from surfaces of the inlet lip in response to detecting a first operating condition, the flow device being a bi-directional pump;
- and
- causing the flow device to discharge airflow from the secondary flow passage to the surfaces of the inlet lip in response to detecting a second, different operating condition.
Dependencies are inferred from the claim text.