A nacelle assembly (16) for a gas turbine engine includes a fan nacelle (62) bounding a bypass flow path (B). The fan nacelle (62) includes a first nacelle section (68A) and a second nacelle section (68B). The second nacelle section (68B) includes a moveable portion (79) movable relative to a forward portion (81) to define a secondary flow passage (74). The first nacelle section (68A) includes an inlet lip (71). A thrust reverser (72) is configured to selectively communicate a portion of bypass airflow between the bypass flow path (B) and the secondary flow passage (74). A pump (88) is configured to selectively communicate airflow between the inlet lip (71) and the secondary flow passage (74).
COMBINED INLET LAMINAR AND THRUST REVERSER CASCADE EFFLUX FLOW CONTROL SYSTEM
KOMBINIERTES REGELSYSTEM DER STRÖMUNG EINES LAMINAREN EINLAUFS UND EINES KASKADENSCHUBUMKEHRERS
SYSTÈME DE COMMANDE D'ÉCOULEMENT D'EFFLUENT EN CASCADE LAMINAIRE D'ENTRÉE COMBINÉE ET D'INVERSEUR DE POUSSÉE
2020-03-18
Patent
Electronic Resource
English
Combined inlet laminar and thrust reverser cascade efflux flow control system
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