An intravascular blood pump (1) comprises a catheter (5), a rotor (10), a housing (11) in which the rotor (10) is housed and a flexible drive shaft (12) extending through the catheter (5) and connected to the rotor. The drive shaft (12) comprises at least one outer layer (28) and at least one inner layer (29). The drive shaft (12) is rotatably supported in a proximal bearing (13) located proximally of the rotor (10). The outer layer (28) of the drive shaft (12) is absent or thinned at a location where the drive shaft (12) is supported in the proximal bearing (13).

A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.

The bearing assembly includes one or more elastomeric members loaded in a precompression by a shim that includes a shape memory alloy. The shape memory alloy is configured to generate the precompression in the elastomeric members upon a temperature change.

A bearing system is configured to surround a rotor along a circumferential direction corresponding to the rotor. The rotor is extended along an axial direction co-directional to a centerline axis of the rotor. The bearing system includes a body from which a plurality of first support members is each extended, and wherein the plurality of first support members is spaced apart from one another along the circumferential direction. Each first support member includes a first axial support arm extended along the axial direction and a first radial support arm extended from the first axial support arm along a radial direction. The first radial support arm is configured to position a bearing element in contact with a bearing surface at the rotor.

The present disclosure relates to a reduced friction torsion component system that makes use of a first frame portion adapted to be coupled to, or integrally formed with, a first object, and forming a first bore, and a second frame portion adapted to be coupled to, or integrally formed with, a second object, and forming a second bore. The two bores are axially aligned and receive at least one elongated hinge component. The elongated hinge component operates to both couple the first and second frame portions together for pivoting movement relative to one another, and also provides a torsional biasing force to enable pivotal deployment from a first position to a second position of one of the first or second frame portions.

A bearing system is provided, configured to surround a rotor along a circumferential direction corresponding to the rotor. The rotor is extended along an axial direction co-directional to a centerline axis of the rotor. The bearing system includes a body from which a plurality of first support members is each extended, and wherein the plurality of first support members is spaced apart from one another along the circumferential direction. Each first support member includes a first axial support arm extended along the axial direction and a first radial support arm extended from the first axial support arm along a radial direction. The first radial support arm is configured to position a bearing element in contact with a bearing surface at the rotor.

A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.

A variable-stiffness actuator is to be installed into a flexible member and provide different degrees of stiffness to the flexible member. The actuator includes two hard members located apart from each other, and a shape-memory member connecting the hard members. The shape-memory member has a property of transitioning in phase between a first phase and a second phase. The shape-memory member is in a low stiffness state when in the first phase, and is in a high stiffness state when in the second phase. The actuator also includes a inducing member configured to cause a portion of the shape-memory member between the hard members to transition in phase between the first and second phases, and a urging member configured to urge the hard members in directions away from each other.

A support assembly for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The support assembly includes an outer race positioned radially exterior to the bearing such that the outer race supports the bearing. Additionally, the support assembly includes a shape memory alloy damper positioned radially exterior to the outer race and at least partially supporting the outer race. Moreover, the shape memory alloy damper includes a plurality of sleeves. One or more sleeves of the plurality of sleeves include a shape memory alloy material.

A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.