Abstract: A seal includes a mating ring that rotates relative to a porous carbon primary ring at a seal interface. A buffer gas is provided into the seal and passes from the back of the primary ring to the seal interface. The seal can be used as a separation seal or in combination with another seal.

Abstract: An extension assembly for a rotor system for rotating a plurality of rotor blades about a rotor axis with a central rotor hub that defines the rotor axis includes a beam assembly and a first bearing assembly. The beam assembly is configured to attach to the central rotor hub and is positioned at least partially within a corresponding one of the plurality of rotor blades. The first bearing assembly is configured to be fastened to the beam assembly and to at least one of a leading edge or a trailing edge of the corresponding one of the plurality of rotor blades.

Abstract: A fan includes a support, a motor mounted at the support and including a first rotation shaft, a first blade mounted at one end of the first rotation shaft, a transmission mechanism mounted at the support and connected to another end of the first rotation shaft, and a second blade. The transmission mechanism includes a second rotation shaft. A rotation direction of the second rotation shaft is opposite to a rotation direction of the first rotation shaft. The second blade is mounted at the second rotation shaft. A tilt direction of the first blade is opposite to a tilt direction of the second blade.

Abstract: Embodiments of the present disclosure include a drive belt tensioner configured to adjust tension in a drive belt of a blower assembly for a heating, ventilation, and/or air conditioning (HVAC) system. The drive belt tensioner includes a mounting bracket configured to couple directly to a blower housing that is configured to house a blower of the blower assembly. The drive belt tensioner further includes an idler pulley configured to contact the drive belt. A position of the idler pulley is adjustable relative to the mounting bracket to enable adjustment of the tension in the drive belt.

Abstract: A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to % Fn3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ra

Abstract: A fan includes a motor, a rotatable hub coupled to the motor, and at least one fan blade. The at least one fan blade includes a first end coupled to the rotatable hub, a second end, a leading edge, a trailing edge, a passage extending from the first end to the second end, and a winglet attached to the second end. At least one flexible strap extends through the passage of the at least one fan blade. The flexible strap is coupled at a first end to the rotatable hub and coupled at a second end to the winglet, such as to an inner portion thereof within the passage.

Abstract: A radial fan comprising: a plurality of blades rotatable about an axis of rotation and extending radially from the axis of rotation; characterised in that each of the blades has a transverse profile that is symmetrical about a radial line of symmetry extending through the blade, at least a portion of the profile of each blade being curved.

Abstract: A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.

Abstract: A cross flow fan blade includes an inner edge disposed on an inner circumferential side of a cross flow fan, an outer edge disposed on an outer circumferential side of the cross flow fan, and a base part formed between the inner edge and the outer edge. The base part has a pressure face and a negative pressure face. A thickness of the inner edge is larger than 1.5 times a thickness of the outer edge. An interval between the pressure face and the negative pressure face in a direction perpendicular to the pressure face is a thickness of the base part. A maximum thickness position of the base part is closer to the inner edge than to the outer edge. When a blade chord length is L and a maximum thickness of the base part is tmax, tmax/L?0.094, and a range of tmax/L?0.08 is excluded.

Abstract: An interface of a centrifugal fan includes an inlet shroud of an impeller, an air intake positioned in overlapping arranged with a portion of the inlet shroud, and a clearance defined between the inlet shroud and the air intake. The clearance forms a labyrinth fluid flow path for a leakage air flow.

Abstract: An electric blower includes an air blowing unit including a mixed-flow fan to generate a current of air, a motor to rotate the mixed-flow fan, and a housing including a first portion surrounding the mixed-flow fan in a circumferential direction, and a second portion surrounding the motor in the circumferential direction. The inner diameter of the second portion is smaller than the inner diameter of the first portion.

Abstract: The lengths and/or chords and/or pitches of wind turbine or propeller blades are individually established, so that a first blade can have a length/chord/pitch that is different at a given time to the length/chord/pitch of a second blade to optimize performance and/or to equalize stresses on the system.

Abstract: A heat dissipation fan including a housing, a hub, and a plurality of blades is provided. The hub is rotatably disposed in the housing. The blades are disposed at a surrounding edge of the hub to be rotated with the hub. When the heat dissipation fan is operated, at least one flow path is formed by two adjacent blades, and the flow path has a reduction section away from the hub.

Abstract: The invention relates to a method for producing a shielding cartridge (1) of a turbomachine element (10), said method comprising a step of winding a carbon wire (3) comprising a plurality of fibres about a longitudinal axis and a step of trapping and preserving the outside surroundings of the wound-up wire (3) in a housing (2).

Abstract: An outlet guide vane for an axial compressor extending along a rotor axis, includes an airfoil extending in a span direction from a radially inner end at 0% height to a radially outer end at 0% height. The airfoil has a suction side and an opposite pressure side, both sides extending in a chord direction from a leading edge to a trailing edge, wherein for each profile of the airfoil a stagger angle between the chord and the rotor axis is defined. A more favorable air flow profile behind the outlet guide vane is achieved by a new shape of the outlet guide vane, wherein a stagger angle distribution in the span direction has a curved course having a minimum located between 40% and 60% in the span direction, a first maximum at 0% and a second maximum at 100% in the span direction.

Abstract: A rotor assembly has a drive shaft and a bladed rotor mounted to the drive shaft for rotation therewith. A dampening material is bonded to the rotor at a location where there is torsional strain energy present. Shear forces in the damping material are used to convert the torsional strain energy into heat energy, thereby providing torsional vibration damping.

Abstract: The present disclosure relates to a variable stator vane and a method of fabricating the variable stator vane of a gas turbine engine. The method includes providing at least one fibre sheet. The method further includes rolling the at least one fibre sheet around a mandrel to form a spindle section of the variable stator vane. An excess of material of the at least one fibre sheet remains after forming the spindle section. The method further includes using the excess of material of the at least one fibre sheet to form the at least one aerofoil section of the variable stator vane.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine case, a first transceiver and a second transceiver. The turbine engine case includes a case wall and a waveguide. The waveguide is formed integral with the case wall. The waveguide includes a waveguide channel. The second transceiver is configured to be in signal communication with the first transceiver through the waveguide channel.

Abstract: A fluid machine includes a bladed wheel, a resolver, a first fastener, and a second fastener. A resolver rotor is held between the first fastener and the rotary shaft and fixed to a large-diameter portion of the rotary shaft. The bladed wheel is held between the second fastener and the rotary shaft and fixed to a small-diameter portion of the rotary shaft. While the resolver rotor is fixed by the first fastener in a same direction as the bladed wheel is fixed by the second fastener along an axial direction of the rotary shaft, and the resolver rotor is fixed by the first fastener at a position away in a radial direction of the rotary shaft from a position where the bladed wheel is fixed by the second fastener so that the resolver rotor does not receive an axial force from the second fastener.

Abstract: The object of the invention is a system recording the collisions of flying animals (9) with wind turbines (1) and indicating where they fell on the ground, which comprises a wind turbine (1) composed of a tower (2), a nacelle (3), a rotor (4) with blades (5) and a sensor unit comprising one sensor (6) and peripheral devices of the sensor, characterised in that the sensor (6) mounted on the nacelle (3) and/or tower (2) of the wind turbine (1) is a LIDAR sensor or a 3D light field camera or a 3D radar scanning the space around the wind turbine (1) in the field of view (7) of the sensor (6). The object of the invention is also the method of application of the above described system for recording the collisions of flying animals (9) with wind turbines (1) and indicating where they fell on the ground and the application of the system.