US 12,110,120 B2
Propulsion unit for an aircraft and method for mounting same
Hazem Kioua, Moissy-Cramayel (FR); Thomas Marlay, Moissy-Cramayel (FR); Charles-Antoine Lampaert, Moissy-Cramayel (FR); and Pierre-Alain Reboul, Moissy-Cramayel (FR)
Assigned to SAFRAN NACELLES, Gonfreville-L'Orcher (FR)
Appl. No. 18/255,025
Filed by SAFRAN NACELLES, Gonfreville-L'Orcher (FR)
PCT Filed Dec. 1, 2021, PCT No. PCT/FR2021/052164
§ 371(c)(1), (2) Date May 30, 2023,
PCT Pub. No. WO2022/123146, PCT Pub. Date Jun. 16, 2022.
Claims priority of application No. 2012769 (FR), filed on Dec. 7, 2020.
Prior Publication US 2024/0026798 A1, Jan. 25, 2024
Int. Cl. B64D 27/40 (2024.01); B64D 29/06 (2006.01); B64D 29/08 (2006.01); F01D 25/24 (2006.01); F01D 25/28 (2006.01); F02C 7/00 (2006.01); F02C 7/04 (2006.01); F02C 7/20 (2006.01)
CPC B64D 27/40 (2024.01) [B64D 29/06 (2013.01); B64D 29/08 (2013.01); F01D 25/243 (2013.01); F01D 25/28 (2013.01); F02C 7/00 (2013.01); F02C 7/04 (2013.01); F02C 7/20 (2013.01); F05D 2220/323 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A propulsion unit for an aircraft, the propulsion unit comprising:
a gas generator having a longitudinal axis and comprising at least one compressor, a combustion chamber, and at least one turbine arranged one behind the other along said axis,
a tubular air inlet arranged upstream of the gas generator with reference to flowing gases in operation, and
an annular sealing system axially interposed between the air inlet and the gas generator, the sealing system being configured to provide a sealing between a downstream edge of the air inlet and an upstream edge of the gas generator, the edges being configured to be disjoint from each other,
wherein the sealing system comprises:
a compression ring comprising a first axial end to mechanically connect to a first element chose from the gas generator and the air inlet, and a second opposite axial end configured to be axially separated from a second element chosen from the gas generator and the air inlet by an annular space, said annular space having an axial dimension which is suitable to be reduced by bringing the compression ring closer to said second element, and
an annular seal mounted in the space and configured to be axially compressed by reduction of the axial dimension of the space,
wherein the second end of the compression ring comprises projecting clevises which are located opposite similar clevises of the corresponding edge and which are configured to allow the application of a force to reduce the axial dimension of said space.