33results about How to "Simple and economical and effective" patented technology

A support for a bearing that guides a shaft in a turbomachine is disclosed. The support includes an annular part made of a shape memory material which retains an initial shape when the load applied to it remains below a threshold value and which deforms, absorbing energy when the applied load becomes at least equal to the threshold value. The annular part is capable of reverting at least approximately to its initial shape when the applied load drops back below the threshold value.

A turbomachine rotor disk (32) comprising inter-blade platforms (44) fixed to ribs (16) delimited by cavities (14) in which blade roots (20) are retained, and protective liners (30) mounted between the flanks of the cavities (14) of the disk (32) and the blade roots (20), wherein the protective liners (30) have a C-shaped cross section so that they can be fitted translationally and retained radially on the ribs (16) of the disk (32) and constitute means of locking the platforms (44) on the ribs (16) of the disk (32).

A turbomachine rotor disk including inter-blade platforms fixed to ribs delimited by cavities in which blade roots are retained, and protective liners mounted between the flanks of the cavities of the disk and the blade roots is disclosed. The protective liners have a C-shaped cross section so that they can be fitted translationally and retained radially on the ribs of the disk and constitute a locking device which locks the platforms on the ribs of the disk.

A turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring held by a casing of the turbine, and an annular thermal protection sheet mounted between the casing and the sealing ring is disclosed. The annular thermal protection sheet is formed by a plurality of curved plates mounted end-to-end and attached by pins to the casing.

A boomerang link for aircraft engine mounts, including a first orifice and a second orifice both designed to connect the boomerang link to an aircraft pylon, and a third orifice designed to connect the boomerang link to an aircraft engine. The third orifice is offset relative to a plane passing simultaneously through an axis of the first orifice and through an axis of the second orifice. When the boomerang link is seen in section in any plane orthogonal to the axes, a straight line segment extending from the axis of the second orifice to an axis of the third orifice crosses a region external to the boomerang link. This conformation confers on the boomerang link a flexibility enabling it to filter transverse vibrations between an engine and an aircraft pylon.

In order to facilitate the thermoacoustic insulation of an aircraft portion, a method for manufacturing a thermoacoustic insulation module for an aircraft comprises a step of providing a mat configured to provide thermoacoustic insulation of an aircraft portion, followed by a step of attaching a bendable structure to the mat, followed by a step of bending the bendable structure, along a bending axis parallel to a longitudinal direction of the mat, such that the bendable structure forms a load-bearing structure supporting the mat in a curved shape.

To facilitate the removal of a bearing housed in an arm of a turbomachine casing, which bearing guides a transmission shaft of the turbomachine, a casing arm includes a body with a vertical portion and a base defining a portion of a shaft housing; an additional part removably attached to the body and defining a bearing housing opening in the shaft housing; and a removable shim inserted between the base and the additional part. A turbomachine including such a casing arm is also described, as well as a method for removing the bearing from such a turbomachine, including removing the shim and moving the additional part towards the base, thereby allowing access to the bearing.

An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).

The present invention discloses a method for preparing a concrete superplasticizer having a phosphorous acid group and a use of the concrete superplasticizer. The concrete superplasticizer having a phosphorous acid group according to the present invention is prepared by free radical copolymerization of a phosphorous-containing monomer A and a polyether macromonomer B. The concrete superplasticizer having a phosphorous acid group obtained in the present invention can effectively improve flowability of concrete and can retain good workability of concrete. The method is simple, economical and effective, and in particular, can be used for commercial mass production.

Housing a conduit of a thermal protection system of a rigid structure of an attachment pylon in an aircraft propulsion assembly within a box of the rigid structure, so as to take advantage of the volume within the rigid structure. The elements forming the conduits thus form an integral part of the rigid structure and can thus play a structural role.

A turbine engine comprises a rotor shaft and a roller bearing supporting the shaft in rotation along an axis. The bearing comprises an inner ring, an outer ring, and rolling elements engaged between the inner and outer rings. The inner ring has a first axial end annular portion that is more exposed to heat during operation than a second axial end annular portion thereof. The turbine engine further comprises an oil injection device configured to supply the rolling elements with oil for lubrication of the latter. In order to homogenise the temperature of the inner ring, the latter comprises through-holes formed in the first axial end annular portion and distributed around the axis in order to allow for a circulation of oil coming from the oil injection device through the first axial end annular portion, thereby providing additional cooling to the first end annular portion.

The invention relates to a vibration damping system for a motor vehicle transmission, comprising:a support member (1) capable of being driven rotationally around an axis X and having a plurality of outer raceways (16); anda plurality of pendulum flyweights (2) distributed circumferentially around the axis X;each of the pendulum flyweights (2) being mounted oscillatingly with respect to the support member (1) by means of two rolling bodies (12, 13) that interact respectively with one and the other of the two inner raceways (14, 15) of the pendulum flyweight (2) and each interact with one of the outer raceways (16) of the support member (1),the outer raceways (16) being juxtaposed one after another continuously around the axis X, so that the rolling bodies (12, 13) are each capable of passing freely from a first outer raceway (16) to a second outer raceway (16).