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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

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.

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1. 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 f

1. 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; anda 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. 2. The nacelle assembly as recited in claim 1, wherein the thrust reverser includes a cascade configured to direct bypass airflow through the secondary flow passage. 3. The nacelle assembly as recited in claim 2, wherein the forward portion defines a bull-nose having an arcuate profile configured to direct bypass airflow towards the cascade, and the bull-nose includes a perforated surface coupled to the pump. 4. The nacelle assembly as recited in claim 3, wherein airflow from the inlet lip is configured to discharge over surfaces of the bull-nose to increase flow attachment. 5. The nacelle assembly as recited in claim 1, wherein the inlet lip includes a perforated surface coupled to the pump. 6. The nacelle assembly as recited in claim 5, wherein the perforated surface defines a radially outer wall of the inlet lip. 7. The nacelle assembly as recited in claim 1, wherein the pump is configured to selectively communicate airflow in at least a first flow direction and in a second flow direction in response to one or more operability conditions of the nacelle assembly. 8. The nacelle assembly as recited in claim 1, wherein airflow from the inlet lip is configured to discharge at a trailing edge region of the second nacelle section. 9. The nacelle assembly as recited in claim 1, comprising: a controller configured to cause the pump to operate in at least a first mode and a second mode in response to determining one or more operability conditions of the nacelle assembly; andwherein airflow is communicated from the forward portion to the inlet lip in the first mode, and airflow is communicated from the inlet lip to a location downstream of the inlet lip in the second mode. 10. 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; anda bi-directional pump configured to selectively communicate airflow between surfaces of the inlet lip and surfaces of the secondary flow passage. 11. The gas turbine engine as recited in claim 10, wherein the bi-directional pump is configured to selectively communicate airflow in at least a first flow direction and in a second flow direction in response to one or more operability conditions of the engine. 12. The gas turbine engine as recited in claim 11, wherein: airflow is discharged at radially outer surfaces of the inlet lip in response to the bi-directional pump communicating airflow in the first flow direction; and airflow is drawn from surfaces of the inlet lip in response to the bi-directional pump communicating airflow in the second flow direction. 13. The gas turbine engine as recited in claim 11, wherein the second nacelle section defines a cavity, and the bi-directional pump is configured to selectively discharge airflow to the cavity when the second nacelle section is located in a stowed position. 14. The gas turbine engine as recited in claim 13, wherein the cavity is defined between inner and outer walls of the second nacelle section, and the cascade is at least partially received within the cavity. 15. The gas turbine engine as recited in claim 10, wherein the bi-directional pump is configured to communicate airflow from at least one of the inlet lip and the secondary flow passage to a heat exchanger. 16. The gas turbine engine as recited in claim 10, comprising: a controller configured to cause the bi-directional pump to operate in at least a first mode and a second mode in response to determining one or more operability conditions of the engine;wherein airflow is communicated in a first flow direction between the bi-directional pump and surfaces of the inlet lip in the first mode, and is communicated in a second, different flow direction between the bi-directional pump and surfaces of the inlet lip in the second mode; andwherein airflow is communicated between the bi-directional pump and surfaces of the secondary flow passage in the first mode, but not in the second mode. 17. 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; andcausing 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. 18. The method as recited in claim 17, comprising: operating the flow device in a first flow direction in response to detecting the first operating condition;operating the flow device in a second flow direction in response to detecting the second operating condition; andwherein the flow device is coupled to the inlet lip and the forward portion of the second nacelle. 19. The method as recited in claim 17, wherein: the second nacelle defines a cavity; andairflow is selectively communicated from surfaces of the inlet lip to the cavity. 20. The method as recited in claim 19, wherein the step of discharging airflow from the secondary flow passage to the surfaces of the inlet lip is in response to moving the moveable portion relative to the forward portion. 21. The method as recited in claim 19, comprising directing flow through a cascade situated in the secondary flow passage, wherein the cascade is at least partially received within the cavity, and the cavity is defined between inner and outer walls of the second nacelle.