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An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow

An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow. The at least one deformable wall selectively forms part of the peripheral wall of the inlet duct when in an undeployed position and selectively forms a curved profile projecting into the inlet duct to reduce line-of-sight noise propagation through the inlet duct.

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1. A compressor inlet for an aeroengine, the compressor inlet comprising: an inlet duct for directing an air flow to a compressor of the aeroengine, and at least one deformable wall providing a portion of at least one peripheral wall of the inlet duct and deformable between an undeployed and a deplo

1. A compressor inlet for an aeroengine, the compressor inlet comprising: an inlet duct for directing an air flow to a compressor of the aeroengine, and at least one deformable wall providing a portion of at least one peripheral wall of the inlet duct and deformable between an undeployed and a deployed position, the at least one deformable wall having a first surface exposed to the air flow and a second surface opposite to the first surface, a plurality of acoustic cells being attached to the second surface of the at least one deformable wall, the at least one deformable wall having a plurality of holes extending therethrough from first to second surface and being in communication with the respective acoustic cells, the at least one deformable wall in the undeployed position being shaped as part of the at least one peripheral wall to substantially avoid interfering with the air flow through the inlet duct, and the at least one deformable wall in the deployed position being deformed to project into the inlet duct to reduce an effective cross-sectional area of the inlet duct to reduce line-of-sight noise propagation, the acoustic cells each comprise a bottom end attached to the second surface of the at least one deformable wall and a top end distal to the bottom end, the top ends of adjacent acoustic cells being spaced apart by a gap between the adjacent acoustic cells when the at least one deformable wall is in the undeployed position to avoid interference between the adjacent acoustic cells. 2. The compressor inlet as defined in claim 1 wherein the at least one deformable wall comprises a plurality of panels pivotally connected one to another to allow relative pivotal axes oriented transverse to a direction of the air flow. 3. The compressor inlet as defined in claim 1 wherein the at least one deformable wall is made of a flexible material. 4. The compressor inlet as defined in claim 1 wherein the acoustic cells positioned on the second surface of the at least one deformable wall, are spaced apart one from another to avoid interference between the adjacent acoustic cells when the at least one deformable wall forms the curved profile causing the second surface thereof to become the concave curvature. 5. The compressor inlet as defined in claim 1 wherein the top end has a dimension smaller than a dimension of the bottom end, resulting in increased spaces between the top ends of the adjacent acoustic cells to avoid interference between the adjacent acoustic cells when the at least one deformable wall forms a curved profile causing the second surface thereof to become a concave curvature. 6. The compressor inlet as defined in claim 1 wherein the compressor inlet comprises a linear actuator for selectively actuating the at least one deformable wall between the undeployed position and the deployed position. 7. The compressor inlet as defined in claim 1 wherein the compressor inlet comprises an air chamber to which the at least one deformable wall is attached and a device for selectively changing air pressure in the air chamber to result in a change of a shape of the at least one deformable wall. 8. The compressor inlet as defined in claim 1 wherein the at least one deformable wall in the deployed position forms a curved ridge extending substantially perpendicular to a direction of the air flow. 9. The compressor inlet as defined in claim 1 wherein the inlet duct comprises an aperture in the at least one peripheral wall thereof, the at least one deformable wall being attached to the at least one peripheral wall to cover the aperture when the at least one deformable wall is in the undeployed position. 10. The compressor inlet as defined in claim 1 wherein the at least one peripheral wall of the inlet duct comprises flat top and bottom walls and flat side walls, the at least one deformable wall being operatively attached to the respective top and bottom walls. 11. The compressor inlet as defined in claim 3 comprising means for selectively forcing deformation of the at least one deformable wall between an unloaded state and a loaded state, the unloaded state being one of the undeployed and deployed positions and the loaded state being the other one of the undeployed and deployed positions. 12. The compressor inlet as defined in claim 11 wherein the at least one deformable wall is substantially flat in said unloaded state and is selectively deformed into the curved profile in the loaded state. 13. The compressor inlet as defined in claim 11 wherein the at least one deformable wall has the curved profile in said unloaded state and is selectively deformed into a substantially flat shape in the loaded state. 14. A compressor inlet for an aeroengine, the compressor inlet comprising: an inlet duct for directing an air flow to a compressor of the aeroengine, and at least one deformable wall providing a portion of at least one peripheral wall of the inlet duct and deformable between an undeployed and a deployed position, the at least one deformable wall having a first surface exposed to the air flow and a second surface opposite to the first surface, a plurality of acoustic cells being attached to the second surface of the at least one deformable wall, the at least one deformable wall having a plurality of holes extending therethrough from first to second surface and being in communication with the respective acoustic cells, the at least one deformable wall in the undeployed position being shaped as part of the at least one peripheral wall to substantially avoid interfering with the air flow through the inlet duct, and the at least one deformable wall in the deployed position being deformed to project into the inlet duct to reduce an effective cross-sectional area of the inlet duct to reduce line-of-sight noise propagation, the acoustic cells each comprising a bottom end attached to the second surface of the at least one deformable wall and a top end distal to the bottom end, the top end having a dimension smaller than a dimension of the bottom end, resulting in increased spaces between top ends of adjacent acoustic cells to avoid interference between adjacent acoustic cells when the at least one deformable wall forms a curved profile causing the second surface thereof to become a concave curvature.