Light weight fan casing configurations for energy absorption are disclosed herein. An apparatus includes a first set of metal bands positioned within a containment casing of a turbofan engine, and a second set of metal bands traversing the first set of metal bands, the first set of metal bands and the second set of metal bands to surround at least a portion of the turbofan engine.

An electric coolant pump includes a pump house, a motor connected to the pump house, and an impeller housed in the pump house and driven by the motor. The motor includes a stator and a movable unit rotatably mounted within the stator. The stator is provided with a central shaft. The movable unit includes a support body, a bearing assembly fixedly embedded in the support body, a rotor core fixed to the support body, and a plurality of permanent magnets attached to the rotor core. The bearing assembly includes at least one bearing rotatably sleeved on the central shaft. The support body is formed by an injection-molding process to wrap the bearing assembly and fixed connecting bearing assembly and the rotor core.

An alpha-alumina coated turbocharger turbine wheel includes a hub portion, a plurality of blades disposed about the hub portion, each blade of the plurality of blades having a leading edge and a trailing edge, a centerline passing axially through the hub portion, and a back-side wall defined radially between the leading edge of each blade of the plurality of blades and the centerline. The turbocharger turbine wheel is made of a metal alloy and a surface coating layer of alpha-alumina. The surface coating layer of alpha-alumina may be disposed only on the hub portion, the plurality of blades, and a radially-outer portion of the back-side wall. The radially-outer portion is defined between a radial distance from the centerline and the leading edge of each blade of the plurality of blades. Alternatively, the surface coating layer of alpha-alumina may be disposed on the hub portion, the plurality of blades, and an entirety of the back-side wall.

A vacuum pump generally comprises a low pressure portion and a high pressure portion separated by a gas impermeable partition. Gas molecules exit the low pressure portion through an opening in the partition and passively impinge on a featureless rotatable surface in the high pressure portion. A drive rotates the rotatable surface with tangential velocity in the supersonic range at multiple times the most probable velocity of the impinging gas molecules. Impinging gas molecules are ejected outwardly from the periphery of the rotatable surface generating a substantial net outward flow of gas and reducing the pressure in the low pressure portion. The vacuum pump is effective to reduce the pressure in the low pressure portion to a target minimum pressure without using seals to prevent gas molecules from leaking back to the low pressure portion and without using blades or vanes to actively impact the gas molecules.

A turbofan engine has a primary duct , in which there flows a primary flow at a primary pressure and a secondary duct, which radially surrounds the primary duct and in which there flows a secondary flow at a secondary pressure. The primary duct includes at least one compressor configured to compress the primary flow , a turbine driving the compressor in rotation and a combustion chamber designed to receive, at an inlet, the primary air flow compressed by the compressor The turbomachine further includes a cooling circuit extending between the compressor and the turbine.The cooling circuit has an air flow rate regulating device arranged upstream of the turbine and having at least one valve that is configured to move between an open position and a closed position, located between the compressor and the combustion chamber in the primary duct and the pressure (PS) in the secondary duct.

A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.

A compressor wheel for a compressor of a turbocharger has a hub (16) and a multiplicity of blades (12) on the hub (16). In intermediate spaces of the multiplicity of blades (12), a channel is in each case formed between a suction side (24) and a pressure side (26). The channel guides fluid that flows in axially in relation to a rotation axis (22) radially or radially-axially outward. The hub (16) in relation to the rotation axis (22) in at least one channel is contoured with a rotationally symmetrical portion (18′) and a non-rotationally symmetrical portion (18). The non-rotationally symmetrical portion (18) is formed by radii that are variable in the flow direction, and a transition region (28) between the hub (16) and the blade (12) adjoins the non-rotationally symmetrical portion (18).

An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.

A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. Pressure relief dimples are provided around the outer diameter of the ring for locally reducing contact pressure at the outer diameter below a value at which the damper ring locks in the groove by friction forces when subject to centrifugal loads.

A retaining ring assembly for a gas turbine engine may include a first engine component and a second engine component. A retaining ring may be disposed between the first engine component and the second engine component. The retaining ring may be circumferentially discontinuous and may include a first terminal portion having at least one of a tapered or a contoured geometry. A thickness of the retaining ring at the first terminal portion may be less than a thickness of the retaining ring away from the first terminal portion.