US 12,442,332 B2
Propulsion unit for an aircraft comprising a system for sealing between two air intake parts
Hazem Kioua, Moissy-Cramayel (FR)
Assigned to SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
Appl. No. 18/257,367
Filed by SAFRAN NACELLES, Gonfreville-l'Orcher (FR)
PCT Filed Dec. 13, 2021, PCT No. PCT/FR2021/052292
§ 371(c)(1), (2) Date Jun. 14, 2023,
PCT Pub. No. WO2022/129756, PCT Pub. Date Jun. 23, 2022.
Claims priority of application No. 2013170 (FR), filed on Dec. 14, 2020.
Prior Publication US 2024/0026819 A1, Jan. 25, 2024
Int. Cl. F02C 7/042 (2006.01); F02C 7/28 (2006.01)
CPC F02C 7/042 (2013.01) [F02C 7/28 (2013.01); F05D 2220/323 (2013.01)] 17 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 the longitudinal axis, and
an air intake of a tubular shape disposed upstream of the gas generator with reference to a flowing of gases during operation, the air intake comprising an upstream annular lip which is movable in axial translation along said longitudinal axis from a rearward position, in which the lip comprises a downstream edge adjoining an upstream edge of the rest of the air intake, and a forward position, in which the downstream edge of the lip is spaced from the upstream edge of the rest of the air intake, and
an annular sealing system which is carried by the lip at a level of the downstream edge and which is configured to adopt, in said rearward position, a restricted state in which the sealing system ensures a sealing between the downstream edge of the lip and the upstream edge of the rest of the air intake, and an extended state in which the sealing system defines, at the level of said downstream edge, an aerodynamic airflow profile inside the gas generator,
wherein the sealing system comprises:
an annular envelope made of a first material and extending around the longitudinal axis and at the level of the downstream edge of the lip, the envelope comprising a downstream annular surface configured to bear on the upstream edge of the rest of the air intake and to define said aerodynamic profile, and
at least one member made of a second material different from the first material and elastically deformable, the member being located at the level of the downstream edge of the lip and configured to be elastically deformed by compression when the lip is in the rearward position and to exert an elastic return force on the envelope when the lip passes from the rearward position to the forward position, so that the sealing system adopts the aforementioned extended state autonomously,
and wherein the at least one member is selected from:
an annular leg made of elastically deformable material,
an annular seal made of elastically deformable material and comprising an internal annular cavity, and
a spring,
the propulsion unit further comprising a plurality of springs distributed around the longitudinal axis on the downstream edge of the lip.
 
10. 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 the longitudinal axis, and
an air intake of a tubular shape disposed upstream of the gas generator with reference to a flowing of gases during operation, the air intake comprising an upstream annular lip which is movable in axial translation along said longitudinal axis from a rearward position, in which the lip comprises a downstream edge adjoining an upstream edge of the rest of the air intake, and a forward position, in which the downstream edge of the lip is spaced from the upstream edge of the rest of the air intake, and
an annular sealing system which is carried by the lip at a level of the downstream edge and which is configured to adopt, in said rearward position, a restricted state in which the sealing system ensures a sealing between the downstream edge of the lip and the upstream edge of the rest of the air intake, and an extended state in which the sealing system defines, at the level of said downstream edge, an aerodynamic airflow profile inside the gas generator,
wherein the sealing system comprises:
an annular envelope made of a first material and extending around the longitudinal axis and at the level of the downstream edge of the lip, the envelope comprising a downstream annular surface configured to bear on the upstream edge of the rest of the air intake and to define said aerodynamic profile, and
at least one member made of a second material different from the first material and elastically deformable, the member being located at the level of the downstream edge of the lip and configured to be elastically deformed by compression when the lip is in the rearward position and to exert an elastic return force on the envelope when the lip passes from the rearward position to the forward position, so that the sealing system adopts the aforementioned extended state autonomously,
wherein the envelope is connected by a plurality of wires to the downstream edge of the lip, the wires being configured to be tensioned when the envelope is in the extended position.