公开(公告)号：US12110120B2

公开(公告)日：2024-10-08

申请号：US18255025

申请日：2021-12-01

Applicant: SAFRAN NACELLES

Inventor： Hazem Kioua ,  Thomas Marlay ,  Charles-Antoine Lampaert ,  Pierre-Alain Reboul

IPC: B64D27/40 ,  B64D29/06 ,  B64D29/08 ,  F01D25/24 ,  F01D25/28 ,  F02C7/00 ,  F02C7/04 ,  F02C7/20

CPC classification number: B64D27/40 ,  B64D29/06 ,  B64D29/08 ,  F01D25/243 ,  F01D25/28 ,  F02C7/00 ,  F02C7/04 ,  F02C7/20 ,  F05D2220/323

Abstract: A propulsion unit for an aircraft includes a gas generator; an air inlet; and a sealing system inserted axially between the air inlet and the gas generator. The sealing system has at least: a compression ring with a first axial end configured for mechanical connection to one of the gas generator and the air inlet. The compression ring also has a second opposite axial end configured to be axially separated from the other of the gas generator and the air inlet by an annular space. An annular seal is mounted in the space and configured to be axially compressed by reduction of the axial dimension of said space.

公开(公告)号：US20240018903A1

公开(公告)日：2024-01-18

申请号：US18247052

申请日：2021-10-01

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Damien Lemoine ,  Charles-Antoine Lampaert ,  Hazem Kioua

IPC: F02C7/047 ,  B64D33/02

CPC classification number: F02C7/047 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/026 ,  F05D2220/80

Abstract: Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.