Abstract: A counter weight for use with a rotor module, including: a root portion; a main body portion that extends away from the root portion; a pair of side portions each extending from opposite sides of the main body portion; and at least one plate secured to one of the opposite sides of the main body portion in order to adjust a weight of the counter weight.

Abstract: The present invention provides a flying apparatus that can accurately measure a weight of a transported objected in a simple configuration. The flying apparatus 10 includes rotors 11, motors 12, a flight sensor 13, an electric power conversion unit 14, and a computation control unit 15. The flight sensor 13 measures physical quantities acting on a fuselage base portion 16. The computation control unit 15 generates instruction signals based on the physical quantities to cause the fuselage base portion 16 to be at a predetermined position in a predetermined attitude. The electric power conversion unit 14 adjusts amounts of electric power supplied to the motors 121 and the like based on the received instruction signals. Moreover, the computation control unit 15 calculates an estimated weight that is an estimation value of a weight of the transported object, based on magnitudes of the instruction signals.

Abstract: A rotatable cutter, which may be used in a cutting assembly and in a grinder pump, is provided comprising at least a first cutting blade and a second cutting blade. Each of the first and the second cutting blades include a central region and a distal region. A protruding nub extends axially outwardly from the distal region of at least one of the first and second cutting blades. The rotatable cutter is engageable with a rotating drive shaft, which may also be engaged with an impeller of the pump.

Abstract: A turbine engine having a longitudinal centerline axis. The turbine engine including a fan comprising a plurality of fan blades that rotate about the longitudinal centerline axis and a rotational component coupled to the fan. The turbine engine including a fluid circuit for supplying fuel or lubricant to the turbine engine and a hydraulic fan brake coupled to the fluid circuit to prevent rotation of the rotational component, thus preventing rotation of the fan. The hydraulic fan brake including a hydraulic cylinder fluidly coupled to the fluid circuit and a valve coupled to the hydraulic cylinder and having a first valve position that disengages the hydraulic fan brake to allow rotation of the rotational component and a second valve position that engages the hydraulic fan brake to prevent rotation of the rotational component.

Abstract: A propulsion system includes a drive shaft, a drive turbine including a drive turbine stator and a drive turbine rotor, the rotor being connected to the drive shaft and including a turbine disk and turbine blades, and a fan section including a fan rotor and a fan stator, the drive shaft being connected to the fan rotor. The turbine disk has an inner surface, an outer surface delimiting slots distributed about a longitudinal axis, one or more of the turbine blades including a root fixed to the turbine disk in a respective slot. A bore width of the inner surface, and a rim radius of the outer surface of the turbine disk, and a limit speed of the drive shaft are defined in relation to each other.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor assembly and a stator assembly. The turbine engine including a primary stage of airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor assembly. A subsidiary stage of airfoils located upstream of the primary stage of airfoils and circumferentially arranged about the engine centerline.

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 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: 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: 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).