초록 ▼

The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments (16) each having an engine vibration insulation system (20) including a housing (22), a stress transmitt

The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments (16) each having an engine vibration insulation system (20) including a housing (22), a stress transmitting member (24) extending along a first axis (26) parallel to an axis of rotation of the propeller and a hollow member (28) integrated in the housing and extending along a second axis (30) orthogonal to and intersecting the first axis. According to the invention, a support means for supporting the system (20) is formed by a plurality of clevises (32a, 32b) each having a middle plane parallel to its clevis heads, integrating one of the first and second axes and orthogonal to the other of said axes.

대표청구항 ▼

1. An engine assembly for an aircraft, comprising: a turboprop provided with a propeller and a transmission driving a rotor of said propeller; an attachment mast of the turboprop;an attachment means for attaching the turboprop on said attachment mast, said means comprising a plurality of front engin

1. An engine assembly for an aircraft, comprising: a turboprop provided with a propeller and a transmission driving a rotor of said propeller; an attachment mast of the turboprop;an attachment means for attaching the turboprop on said attachment mast, said means comprising a plurality of front engine attachments inserted between said attachment mast and a casing of the turboprop transmission, each front engine attachment comprising an engine vibration insulation system, a support means thereof integrated into the casing of the transmission, as well as a fastening means inserted between said support means and the vibration insulation system, the latter part including:a housing mounted on the support means via a fastening means;a stress transmitting member extending along a first axis parallel to a rotational axis of said propeller, said member comprising an outer end mounted on said attachment mast; anda hollow member integrated in said housing and extending along a second axis orthogonal to and intersecting said first axis, said hollow member housing an inner end of the stress transmitting member, characterized in that for each front attachment, said support means is formed by a plurality of clevises each having a middle plane parallel to a clevis head, integrating one of said first and second axes and orthogonal to the other of said axes. 2. The engine assembly according to claim 1, characterized in that said plurality of clevises includes: a first clevis arranged in front relative to said housing of the engine vibration insulation system, said first clevis having a middle plane parallel to a clevis head, integrating said first axis and orthogonal to the second axis; andtwo second clevises arranged respectively on either side of said housing of the engine vibration insulation system, along said second axis, the two second clevises having a same middle plane parallel to clevis heads, integrating said second axis and orthogonal to the first axis. 3. The engine assembly according to claim 2, characterized in that said fastening means includes a fork connecting said first clevis to the housing of the engine vibration insulation system, said fork extending in a plane integrating said second axis. 4. The engine assembly according to claim 2, characterized in that said first clevis extends from a front fastening clip of the transmission casing, said front fastening clip being fixedly mounted on a rear fastening clip of a stator of said propeller. 5. The engine assembly according to claim 2, characterized in that said fastening means connected with at least one of said two second clevises includes a hinge member passing through said at least one of said two second clevises, said hinge member being parallel to the first axis and also passing through a fitting housed in the clevis, formed in a single piece with the housing. 6. The engine assembly according to claim 2, characterized in that said fastening means connected with at least one of said two second clevises comprises a hinge member passing through said at least one of said two second clevises, a fitting housed in the first clevis, also passed through by said hinge member parallel to the first axis, and another hinge member parallel to the first axis, passing through the fitting and clevis provided in a single piece with the housing, in which said fitting is housed. 7. The engine assembly according to claim 6, characterized in that said fitting is triangular or assumes the form of a connecting rod. 8. The engine assembly according to claim 2, characterized in that said plurality of clevises also includes a third clevis arranged between the two second clevises, and in that said fastening means connected with said third clevis includes a hinge member passing through said third clevis, a connecting rod parallel to the second axis housed in the third clevis, also passed through by said hinge member parallel to the first axis, and another hinge member parallel to the first axis, passing through the connecting rod and a clevis provided in a single piece with the housing, in which said connecting rod is housed. 9. The engine assembly according to claim 1, characterized in that each front attachment is designed such that the picking up of stresses by said plurality of clevises is done with only six degrees of freedom, in order to preserve an isostatic system.