Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.

Abstract: A wind-speed accelerating wind turbine has the wind turbine installed in the nacelle, the nacelle has a front nacelle member having a cross-section area formed so as to linearly or curvilinearly contract from a wind inlet to an installed position of the wind turbine and has a rear nacelle member having the contracted cross-section area formed so as to linearly or curvilinearly expand or maintain the same cross-section area from the installed position of the wind turbine to a wind outlet, and a wind dispersion part or a wind dispersion shape is provided at the wind outlet of the rear nacelle member.

Abstract: There are provided a vacuum pump which can effectively prevent stress corrosion cracking of a rotating body and has excellent corrosion resistance, and a rotating body of the vacuum pump. In a vacuum pump (e.g., a turbo-molecular pump 100) exhausting gas by rotation of a rotating body 103, the rotating body 103 has, on a surface thereof, a first area 1 covered with a first surface treatment layer 1A and a second area 2 covered with a second surface treatment layer 2A, and a boundary portion 3 between the first area 1 and the second area 2 has an area in which the surface treatment layers 1A and 1B of the first and second areas 1 and 2 overlap each other.

Abstract: An electrical communication system for unmanned aerial vehicle that includes conductive contact surfaces with magnets that are attached to a landing platform, and conductive pin systems that are attached to the vehicle. Each conductive pin system includes a conductive pin that its lower end is made of a magnetizing material, and its upper end is connected to the controller and the battery of the vehicle. The conductive pin systems includes a main body, that is attached to the vehicle, with a hole inside which the conductive pin is penetrated, a nut assembled on the upper end of the pin, a spring that is wounded on the pin between the nut and the main body so that the spring pushes upwards the pin, and a cable connector that is connected to the upper end of the pin to enable electrical connection with the controller and the battery.

Abstract: Disclosed is a tip section for a wind turbine blade. The tip section comprises an intermediary blade section comprising a first shell part forming a first side of the intermediary blade section and a second shell part forming a second side of the intermediary blade section, the intermediary blade section having a leading edge and a trailing edge and extending from an intermediary blade section first end to an intermediary blade section second end; a tip part forming an end of the tip section and having been rigidly attached to the intermediary blade section first end, the tip part having an outer surface comprising a metal area; and a number of one or more superficial metal strips extending along an outer surface of the intermediary blade section. A wind turbine blade with such a tip section and the manufacturing of such a wind turbine blade is also disclosed.

Abstract: The present invention relates to a pre-manufactured spar cap for a wind turbine blade comprising a spar cap structure comprising a plurality of fibre-reinforced composite elements arranged in stacked rows and separated by interlayers and a first and/or second damage tolerant cover sheet. The first and/or second damage tolerant cover sheets each comprises a first damage tolerant fibre layer and a second damage tolerant fibre layer attached to each other in attachment areas, wherein the attachments areas are separated from each other by a distance between 1-5 cm. Furthermore, the spar cap structure and the first and/or second damager tolerant cover sheet are embedded in a first cured resin. The present invention also relates to a damage tolerant cover sheet as such, as well as a wind turbine comprising a first and/or second damage tolerant cover sheet.

Abstract: A planetary gear system includes a carrier including a first side having a first oil manifold opening therethrough, and a second side having a second oil manifold opening therethrough, a first oil manifold and a second oil manifold. The first oil manifold has a first flange portion floatingly engaging with the first oil manifold opening, and a second flange portion engaging with the second oil manifold opening of the carrier, the second flange portion including a first oil manifold mounting flange. The second oil manifold has a second oil manifold flange portion engaging with the second oil manifold opening of the carrier, and including a second oil manifold mounting flange. At least one connecting member connects the first oil manifold mounting flange and the second oil manifold mounting flange so as to mount the first oil manifold and the second oil manifold to the carrier.

Abstract: A fan module for an aircraft turbine engine includes a fan having variable pitch blades and an oil transfer device configured to provide a transfer of oil between a stator and a rotor. The oil transfer device includes a stator ring having internal oil ducts, a shaft inserted into the ring and having internal oil ducts, and an annular support of the ring configured to deform elastically to allow movements of the ring in the radial direction. A plain bearing is located between the ring and the shaft, and roller bearings are mounted between the ring and the shaft on either side of the plain bearing.

Abstract: A centrifugal blood pump includes a housing having a pumping chamber, an inlet having an inlet axis, and an outlet having an outlet axis. The inlet and the outlet are in fluid communication with the pumping chamber. The pump further includes an impeller rotatably disposed within the pumping chamber, and a strut connected to the housing at the inlet. The strut is connected to the housing at a circumferential position about the inlet axis such that a major axis of the strut and the outlet axis define a predetermined angle in a cross-sectional plane perpendicular to the inlet axis. The circumferential position of the strut relative the outlet axis reduces or eliminates damage to blood flowing around the strut.

Abstract: A compression tool for a seal assembly of a gas turbine engine includes a cover configured to be installed to a seal assembly. The seal assembly includes a seal carrier, a seal element installed to the seal carrier, the seal element configured as a ring, and one or more biasing elements configured to axially bias a position of the seal element. The cover includes a cover body, and a cover flange including a flange groove configured to cover the seal element of the seal assembly.

Abstract: An aircraft turbomachine module, including an accessory gearbox, a transfer shaft, and a drive shaft rotatably connected with one another by a power transmission device. The power transmission device can be housed in a gearbox and the module can further include an electric machine rotatably connected to the transfer shaft. The electric machine can be interposed between the transmission housing and at least one part the transfer shaft.

Abstract: An assembly for mounting an auxiliary component to an engine case for a gas turbine engine includes a support bracket and a locator comprising a fusible guide pin extending at least partially into a first aperture disposed in the support bracket, and a catcher pin extending at least partially into a second aperture disposed in the support bracket. The fusible guide pin is configured to fracture to absorb energy while the catcher pin limits system displacement during and post an overload event, thus reducing the energy transmitted to the auxiliary component (e.g., a gearbox housing).

Abstract: A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include intertwined fibers defining a three-dimensional structure. A laminate overlay surrounds at least a portion of the inner support structure.

Abstract: An assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a support bracket, the support bracket having a first end configured for attachment to a first flange of the engine case, a second end configured for attachment to a second flange of the engine case, and an intermediate portion located intermediate the first end and the second end; a bearing member disposed within the intermediate portion; a locator disposed within the bearing member; and a frangible ring member disposed between the support bracket and the bearing member, wherein the frangible ring member comprises a porous metal material (e.g., frothed aluminum or thin-walled honey combed aluminum or steel). The frangible material thickness can be set to absorb FBO energy while limiting system displacement during and post FBO event, thus reducing the energy transmitted to an auxiliary component (e.g., a gearbox housing).

Abstract: The invention relates to acoustic management, on an aircraft turbomachine or on a nacelle, via a panel (30,32). On a support (38) is reserved a recess (34), recessed with respect to a surrounding general surface (36) for contact with moving air. The recess (34) is adapted to receive the panel, as another so-called surface for contact with moving air. The support (38) and/or the panel comprise removable connecting elements for, in the recess, mounting the panel removably with respect to the support, the panel being an acoustic panel (30) or a non-acoustic panel (32).

Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: A propulsion system includes a drive shaft, a drive turbine including a drive turbine rotor having a turbine disk and turbine blades, and a fan section. The turbine disk has an inner surface, an outer surface, a bore radius, and a rim radius. One or more of the turbine blades includes a root fixed to the turbine disk in a respective slot, a stilt connected to the root and including a platform, and an airfoil connected to the platform and extending within a flowpath. The flowpath includes an outer radius and an inner radius. The drive shaft has a limit speed. The bore radius, the rim radius, the outer radius, the inner radius, and the limit speed satisfy a given relationship.

Abstract: A well pump includes a plurality of diffusers, wherein each diffuser comprises a first threaded coupling on one longitudinal end and a second threaded coupling on an opposed longitudinal end. An impeller is disposed in each diffuser. The plurality of diffusers are coupled end to end to form a pump housing, in which the first threaded coupling on one diffuser is threadedly engaged to the second threaded coupling on adjacent diffuser.

Abstract: A system and method for fabricating a protective leading-edge structure for an airfoil includes system includes a mandrel and a cold spray additive manufacturing apparatus. The cold spray additive manufacturing apparatus is configured to deposit a metallic powder on a tool surface of the mandrel to form an inner layer, intermediate layers, and an outer layer of the leading-edge structure. The inner layer forms an inner surface of the leading-edge structure. The outer layer forms an outer surface of the leading-edge structure. The intermediate layers form a thickness of the leading-edge structure. The inner surface of the leading-edge structure is configured to be coupled to the airfoil such that the outer surface of the leading-edge structure forms a portion of a leading edge and a portion of an aerodynamic surface of the airfoil.

Abstract: A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.