US 12,134,983 B2
Process for using an air input of a turboreactor nacelle comprising an air input lip which comprises a portion which can be moved to promote a thrust inversion phase
Daniel-Ciprian Mincu, Moissy-Cramayel (FR); Mathieu Patrick Jean-Louis Lallia, Moissy-Cramayel (FR); Nicolas Joseph Sirvin, Moissy-Cramayel (FR); Jagoda Alina Worotynska, Moissy-Cramayel (FR); Frederic Dautreppe, Moissy-Cramayel (FR); Anthony Binder, Moissy-Cramayel (FR); and Eva Julie Lebeault, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/601,043
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Apr. 8, 2020, PCT No. PCT/EP2020/060029
§ 371(c)(1), (2) Date Oct. 1, 2021,
PCT Pub. No. WO2020/212225, PCT Pub. Date Oct. 22, 2020.
Claims priority of application No. 1904089 (FR), filed on Apr. 17, 2019.
Prior Publication US 2022/0170429 A1, Jun. 2, 2022
Int. Cl. F02C 7/042 (2006.01); F02K 1/66 (2006.01)
CPC F02C 7/042 (2013.01) [F02K 1/66 (2013.01)] 7 Claims
OG exemplary drawing
 
1. A method for operating an air intake of an aircraft turbojet engine nacelle extending along an axis X oriented from upstream to downstream in which an internal air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a thrust reversal phase, the air intake circumferentially extending about axis X and comprising an internal wall pointing to axis X and configured to guide the internal air flow and the reverse air flow, and an external wall, opposite to the internal wall, and configured to guide an external air flow around an exterior of the nacelle, the internal wall and the external wall being connected to each other by an air intake lip so as to form an annular cavity therebetween, the air intake lip comprising a first radial thickness and at least one fixed portion and at least one movable portion that is translationally movable between a first position and a second position, and wherein when the at least one movable portion of the air intake lip is in the first position the air intake lip has an aerodynamic profile that is configured to guide the internal air flow over the internal wall to promote a thrust phase, the method comprising:
a step of moving the at least one movable portion during a thrust reversal phase of said turbojet engine to promote reverse thrust by moving relative to the fixed portion to the second position so that the air intake lip comprises a second radial thickness when in the second position that is less than the first radial thickness,
wherein the first radial thickness and the second radial thickness are measured in a same plane transverse to axis X, and
wherein the at least one movable portion is rigid and is translationally mounted for translating in a downstream direction in moving to the second position.