A toothed coupling mechanism for an assembly of rotating elements of an aircraft gas turbine engine includes a pair of coupling halves having an axial toothed coupling interface therebetween. Each coupling half has a plurality of splined teeth inter-engaged about an axis for transmitting torque therebetween. A protrusion is located on one of the splined teeth of one of the coupling halves. A splined tooth of the other coupling half comes into contact with the protrusion in a situation of uncoupling of said coupling halves.

An oil distribution system including a shaft assembly, bearing assembly and mounting assembly is disclosed. The shaft assembly includes a shaft with an inner shaft. A pocket is defined between the shaft and the inner shaft. A ringed lattice containing oil is secured within the pocket, melting of the ringed lattice releases the oil. The shaft includes shaft slots to usher oil from the pocket towards the bearing assembly. The bearing assembly includes an inner and outer race. The inner and outer race each include axial slots and radial slots. The axial slots of the inner race align with the shaft slots to allow oil to flood the inner race. The mounting assembly includes a bearing support having bearing support slots to receive a stringed lattice. Oil from the bearing support flows into the outer race when the axial slots of the outer race align with the bearing support slots.

A pump device, in particular for a fluid circuit in a motor vehicle, comprising a housing, a drive, a rotor, a stator and a radial bearing, wherein the housing has an inlet, wherein the rotor comprises an impeller wheel, wherein the drive is designed to set the rotor in rotation relative to the stator, wherein the inlet is fluidly connected to the impeller wheel, wherein the rotor has a rotor cavity, wherein a section of the stator projects into the rotor cavity, and wherein the radial bearing is situated in the rotor cavity between the section of the stator and the rotor.

A novel structural arrangement for the various components of an Ultra-Micro Gas Turbine Generator, based on a single part impeller element which comprises the compressor, the turbine and the electrical generator core in a single annular structure, produced as a single piece by an additive manufacturing process. The single annular structure has a hollow shell structure, with a supporting structure within in. The internal hollow space of the shell structure provides for a flow of cooling air from the outside through the internal space, for cooling the turbine region of the impeller. This air flow could be assisted by the use of internal blades, which can also serve as the supporting structure to increase the strength of the shell structure. The air flow can either be ejected at the center of the turbine, or can provide a high pressure supply for air bearings of the impeller element.

An insert for supplying a fluid within a drive shaft, the insert extending along an axis of rotation and comprising an insert wall having a rigid inner insert wall portion and an elastically deformable outer insert wall portion a reservoir defined by the insert wall for storing a fluid, a nozzle positioned at the first end of the insert wall, and wherein the elastically deformable outer insert wall portion is configured to move between an expanded state, when the fluid is supplied to the reservoir, and an unexpanded state, when rotation of the insert and supply of fluid to the reservoir are ceased, and movement of the elastically deformable outer insert wall portion to the unexpanded state forces the fluid to be discharged through the nozzle.

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 drive shaft of an aircraft turbine engine includes a first portion and a second portion, and connecting means connecting the first and second portions and being configured to transmit a torque from the second portion to the first portion. The connecting means has at least one bellows with a first section having a diameter greater than the diameters of the first and second portions and second sections flanking the first section. The first section includes at least one fusible section with at least one through-hole and being configured to break when the value of a torque applied to the first portion exceeds a predetermined threshold value.

A compact axial turbine configured to operate with high density working fluid is described. The turbine comprises an axial majority cantilevered turbomachinery shaft. Rotor assemblies and nozzle spacers communicate torque through turbine shaft splines, allowing them to be slid off the shaft for quick replacement in the field. The compact axial turbine houses turbomachinery within a separable inner casing encircled by a cartridge sleeve, thereby forming a cartridge which can itself be removed as a single component.

An oil distribution system including a shaft assembly, bearing assembly and mounting assembly is disclosed. The shaft assembly includes a shaft with an inner shaft. A pocket is defined between the shaft and the inner shaft. A ringed lattice containing oil is secured within the pocket, melting of the ringed lattice releases the oil. The shaft includes shaft slots to usher oil from the pocket towards the bearing assembly. The bearing assembly includes an inner and outer race. The inner and outer race each include axial slots and radial slots. The axial slots of the inner race align with the shaft slots to allow oil to flood the inner race. The mounting assembly includes a bearing support having bearing support slots to receive a stringed lattice. Oil from the bearing support flows into the outer race when the axial slots of the outer race align with the bearing support slots.

Provided is an electric motor-integrated rocket engine pump. The electric motor-integrated rocket engine pump comprises: a housing; a rotating body provided in one direction inside the housing; an electric motor provided inside the housing, and integrally shaft-coupled to the rotating body; and a plurality of fluid bearings are mounted on front and rear rotating bodies of the electric motor to support rotation of the rotating body.