An insert for supplying a fluid to splines of a drive shaft, the insert extending along an axis of rotation, and the insert comprising an insert wall extending along the axis of rotation, a reservoir defined by the insert wall for storing a fluid, an elastically deformable portion, the elastically deformable portion capable of transitioning between an expanded state and an unexpanded state, and wherein the elastically deformable portion is configured to expand to the expanded state in a radial direction with respect to the axis of rotation when the fluid is supplied to the reservoir during rotation of the insert and to contract to the unexpanded state when rotation of the insert and supply of the fluid to the reservoir are ceased.

Aircraft and aircraft blower systems are described. The blower systems include a shaft, a motor having a stator and a rotor, the rotor being operably coupled to the shaft, a fan operably coupled to the shaft and configured to be driven by rotation of the shaft, one or more bearings arranged along the shaft, and a high pressure cooling source configured to supply high pressure air to the one or more bearings.

A vacuum pump and vacuum assembly. The vacuum pump comprises: an inlet for receiving gas; and an exhaust for exhausting the gas; a hollow shaft defining an axial passage extending through the pump from an opening in a base of the pump to an opening axially beyond the pump inlet. The shaft comprises an end remote from the base of the pump, the end being configured to attach to a cathode plate within a vacuum chamber evacuated by the vacuum pump. The shaft is configured for axial movement of the end between at least one open position in which the end is remote from the inlet of the vacuum pump and a sealing position in which the end is closer to the inlet.

A turbine engine has a fan and a low pressure compressor that rotate at a common speed and in a common direction. A fan drive turbine drives a gear reduction to, in turn, drive the low pressure compressor and the fan at a speed which is slower than a speed of the fan drive turbine. A combustor intermediate the low pressure compressor and the fan drive turbine and a thrust bearing mount the fan drive turbine, the thrust bearing being aft of a location of the combustor. A shear section in a drive connection connecting the fan drive turbine to the gear reduction is weaker than other portions of the drive connection. The shear section is aft of the thrust bearing.

To provide a simple blower which can suppress the infiltration of a target gas into a shaft hole and having a small size and cost reduction, a blower comprising a first casing (11) formed with a gas passage (11c) for introducing a high temperature gas and a shaft hole (11e) for communicating therewith, a rotating shaft (14) inserted to be freely rotatable within the shaft hole (11e), an impeller (13) housed within the first casing (11) which integrally rotates with the rotating shaft (14), a motor (15) for driving the rotating shaft (14) from the rear end side, a second casing (12) having an interior space (21) which communicates with the shaft hole (11e) and supporting the rotating shaft (14) via bearing (22A, 22B), and a purge gas introduction means (16) which introduces to the interior space (21), a purge gas having a higher pressure than a pressure of the shaft hole (11e), wherein the inflow of an exhaust gas into the shaft hole (11e) from the gas passage (11c) side of the first casing (11) is suppressed by introducing the purge gas into the interior space (21).

The gas turbine engine includes a combustion section including an annular swirl combustor having a combustor inlet, and a compressor section including a centrifugal compressor with an impeller, the impeller compressing and swirling an airflow and discharging the compressed and swirled airflow from the impeller outlet into the combustor inlet. The turbine section includes a radial turbine having a turbine fuel inlet and a turbine fuel outlet, the radial turbine receiving a flow of fuel at the turbine fuel inlet and discharging the flow of fuel from the turbine fuel outlet of the radial turbine into the combustor inlet.

A pump assembly includes a pump housing having a fluid inlet, a fluid outlet, and a fluid channel defined therebetween. The pump assembly also includes an impeller positioned within the fluid channel and configured to channel a fluid between the fluid inlet and the fluid outlet. The pump assembly also includes a motor assembly having a shaft coupled to the rear plate, wherein the shaft defines a first fluid cavity coupled in flow communication with an opening in the rear plate to enable fluid flow into the shaft. The motor assembly also includes a motor housing having a back plate positioned relative to the impeller rear plate to define a second fluid cavity therebetween. The motor assembly further includes a stator assembly coupled to the back plate and positioned opposite the second fluid cavity such that the fluid facilitates cooling the stator assembly.

A turbine rotor of an embodiment includes a rotor body portion having turbine discs in plural stages in an axial direction protruding radially outside from an outer peripheral surface of the rotor body portion over a circumferential direction. The turbine rotor includes a plurality of axial passages, through which a cooling medium flows, formed at the rotor body portion radially outside than a center axis of the turbine rotor and radially inside than an outer peripheral surface of the rotor body portion in the axial direction; an introduction passage introducing the cooling medium into each of the axial passages; and discharge passages that penetrate from each of the axial passages to the outer peripheral surface of the rotor body portion to discharge the cooling medium.

A shaft for a gas turbine engine includes an inner contour with a stiffening rib that defines a stiffened wall thickness related to a nominal wall thickness according to a ratio between about 1.125-2.1.

A well fluid centrifugal pump has a shaft passage in the shaft. The shaft passage has an open upper end above the impellers and a closed lower end below the impellers. An outlet port extends laterally from the shaft passage. A gas-lock re-priming device in the shaft passage diverts a portion of well fluid in the discharge adapter bore through the shaft passage and out the outlet port. The re-priming device may be a pressure actuated valve that is biased to a closed position and opens when the pressure in the discharge adapter bore drops below a minimum. Alternately, the re-priming device may be an orifice member with an orifice passage that continuously diverts a portion of the well fluid in the discharge adapter bore out the outlet port.