Propulsion unit for an aircraft and method for mounting same

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 chosen 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 seal comprises:
• at least one annular portion comprising an annular cavity having, in axial cross-section, a shape configured to be modified upon the compression of the seal, and/or
• at least one annular portion comprising a cylindrical bead configured to be engaged in the compression ring or one of the edges, and/or
• at least one annular sealing lip.

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 chosen 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 seal comprises an annular body of elastomeric or composite material and an annular sheet-metal extending to an internal periphery of the body.