INLET - NAI EXHAUST HOLE DEFINITION FOR REDUCED D-DUCT RESONANCE NOISE AND DILUTED EXHAUST PLUME FOR THERMAL CONTROL
FIG2 illustrates a side view of the aircraft of FIG1 including a nacelle in accordance with various embodiments
In various embodiments and with reference to FIG2, a thrust reverser system of the aircraft 100 may be included in the nacelle assembly 122 and may include a translating sleeve 230 and a cascade, or cascade array, 240. The thrust reverser system may also comprise an air diversion system that is configured to direct airflow in the bypass duct through the cascade to create reverse thrust. The air diversion system may be any suitable system including, for example, blocker doors, diversion doors, and/or the like. An A-R-C axis as shown throughout the drawings to illustrate the axial, radial, and circumferential directions, respectively. The aft cascade ring 380 may include a first aft cascade ring 500 and a second aft cascade ring 502. The first aft cascade ring 500 extends from the first hinge beam 504 to the latch beam 510 and has an arc shape. The second aft cascade ring 502 extends from the second hinge beam 506 to the latch beam 510 and likewise has an arc shape. Together, the first aft cascade ring 500 and the second aft cascade ring 502 form an entire aft cascade ring 380. The aft cascade ring 380 defines a plurality of actuator pathways 508. Actuators may extend through each of the plurality of actuator pathways 508 and may be coupled to, and actuate forward and aft, the translating sleeve 230 of FIG2.
side view
122
nacelle assembly
230
translating sleeve
220
fan cowl
100
aircraft
250
bottom
260
axis
124
inlet
['1. An inlet (124) for use with a nacelle (122) having an axis (260), comprising: an outer barrel (300); and a lip skin (306) defining a plurality of elongated exit holes (305) including a first circumferential outer hole (308), a second circumferential outer hole (310), and a plurality of center holes (312) located between the first circumferential outer hole (308) and the second circumferential outer hole (310), the first circumferential outer hole (308) being located at least 10 degrees of an entire circumference of the inlet (124) away from the second circumferential outer hole (310).', '13. A nacelle (122) for use with a gas turbine engine (120), comprising: a fan cowl (220); a thrust reverser (235); and an inlet (124) as recited in any preceding claim.']