Abstract: A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.

Abstract: A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.

Abstract: A decoupling system for a rotary shaft of an aircraft turbojet, the decoupling system including: a rolling bearing including rolling elements inserted between a first ring fastened to a stationary bearing support and a second ring mounted in a mounting chamber fastened to a rotary shaft; a transmission mechanism transmitting rotary torque from the rotary shaft to the second ring; a mechanism allowing the second ring to move radially relative to the mounting chamber when a static force associated with an unbalance affecting the rotary shaft exceeds a predetermined threshold; and a plurality of leaktight flexible bags interposed between the second ring and the mounting chamber and each including a heterogeneous structure including a porous capillary solid matrix and an associated liquid relative to which the matrix is lyophobic.

Abstract: A decoupling system for a rotary shaft of an aircraft turbojet, the decoupling system including: a rolling bearing including rolling elements inserted between a first ring fastened to a stationary bearing support and a second ring mounted in a mounting chamber fastened to a rotary shaft; a transmission mechanism transmitting rotary torque from the rotary shaft to the second ring; a mechanism allowing the second ring to move radially relative to the mounting chamber when a static force associated with an unbalance affecting the rotary shaft exceeds a predetermined threshold; and a plurality of leaktight flexible bags interposed between the second ring and the mounting chamber and each including a heterogeneous structure including a porous capillary solid matrix and an associated liquid relative to which the matrix is lyophobic.

Abstract: A device for detecting breakage of a turbomachine shaft is disclosed. The device includes a shaft having an upstream end and a downstream end; a rod having an upstream end and a downstream end, and placed coaxially inside the shaft, the downstream end of the rod being securely fastened to the downstream end of the shaft and the upstream end of the rod being free to rotate relative to the upstream and of the shaft; and a sensor suitable for detecting a difference in speed of rotation between the upstream end of the rod and the upstream end of the shaft.

Abstract: The present invention relates to detecting breakage of a shaft of a turbomachine, in particular of the aviation type. The invention relates in particular to a device designed to perform such detection. According to the invention, the device for detecting breakage of a turbomachine shaft comprises: a shaft having an upstream end and a downstream end; a rod having an upstream end and a downstream end, and placed coaxially inside the shaft, the downstream end of the rod being securely fastened to the downstream end of the shaft and the upstream end of the rod being free to rotate relative to the upstream and of the shaft; and a sensor suitable for detecting a difference in speed of rotation between the upstream end of the rod and the upstream end of the shaft.