US 12,392,305 B2
Aircraft propulsion unit
Patrick Boileau, Moissy Cramayel (FR); Pierre Caruel, Moissy Cramayel (FR); Gina Ferrier, Moissy Cramayel (FR); Quentin Garnaud, Moissy Cramayel (FR); and Guillaume Glemarec, Moissy Cramayel (FR)
Assigned to Safran Nacelles, Gonfreville l'Orcher (FR)
Filed by Safran Nacelles, Gonfreville l'Orcher (FR); and SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed on Nov. 29, 2021, as Appl. No. 17/536,480.
Application 17/536,480 is a continuation of application No. PCT/EP2020/064763, filed on May 27, 2020.
Claims priority of application No. 19/05675 (FR), filed on May 28, 2019.
Prior Publication US 2022/0082064 A1, Mar. 17, 2022
Int. Cl. F02K 1/76 (2006.01); F02K 1/72 (2006.01)
CPC F02K 1/763 (2013.01) [F02K 1/72 (2013.01)] 13 Claims
OG exemplary drawing
 
1. An aircraft propulsion unit comprising a nacelle and a turbojet engine, the aircraft propulsion unit comprising:
an external envelope including fan cowls;
at least one fan casing cooperating with the fan cowls to define an interior space configured to house cascades of a cascades thrust reverser, the cascades thrust reverser configured to be displaced between a first position and a second position, the at least one fan casing comprises a first fan casing and a second fan casing, the second fan casing being distinct from the first fan casing and disposed downstream of the first fan casing;
at least one actuator configured to move the thrust reverser between the first position and the second position; and
at least one support structure extending from the fan cowls to the first fan casing to connect the fan cowls and the first fan casing, the at least one support structure comprises at least one aperture configured to allow passage of part of the at least one actuator, the first fan casing and second fan casing engage each other downstream of where the at least one support structure extends from the fan cowls, and
wherein the at least one actuator comprises at least one fitting including a first end and a second end, the first end extending from the at least one actuator and the second end configured to be fixed to the second fan casing at a level of at least one first flange,
wherein the first fan casing supports the fan cowls and the second fan casing supports the at least one actuator, and
wherein the first end of the at least one fitting is located upstream relative to where the support structure is connected to the first fan casing and upstream relative to the at least one aperture in the support structure, the second end of the at least one fitting is located downstream relative to where the first and second fan casings engage each other.