Abstract: An airfoil vane assembly according to an exemplary embodiment of this disclosure, among other possible things includes a vane piece having a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform, a spar piece having a spar platform and a spar extending from the spar platform into the hollow airfoil section, and at least one seal arranged at a sealing surface of the spar platform and sealing between the spar platform and the first vane platform. The airfoil vane assembly also includes a thermal barrier coating disposed on the spar piece. The sealing surface is free from the thermal barrier coating. A gas turbine engine and a method of making a spar piece for an airfoil vane assembly are also disclosed.

Abstract: The invention relates to an assembly (10) for a turbomachine comprising a pipe (12) connected at one end (12a) to means (14) for supplying pressurized air and at one opposite end (12b) to an item of equipment (16) of the turbomachine, the pipe (12) having a bent portion (12c) intended for forming in use a low point of the pipe (12), said bent portion (12c) having a hole (18) for first draining water from the pipe (12), wherein it further comprises an orifice (20) arranged downstream of the drain hole (18).

Abstract: A gas turbine engine rotor assembly comprises a torque tube, turbine stage and stiffening mass. The torque tube comprises a shaft extending from a forward location to an aft end, and a shaft fastening flange disposed at the aft end. The turbine stage comprises a disc, a disc adapter extending forward from the disc, and a disc fastening flange extending from the disc adapter and couplable to the shaft fastening flange at an interface. The stiffening mass is positioned proximate the interface to reduce operational stress in the torque tube. A method of reducing operational stress in a rotor assembly comprises de-stacking a rotor stack, separating a first stage rotor disc adapter from a torque tube, attaching a stiffening mass to an inner diameter of one or both of the disc adapter and the torque tube, attaching the disc adapter to the torque tube, and re-stacking the rotor stack.

Abstract: Provided is a rotating body, including: a shaft; and a compressor impeller including: a main body having an insertion hole, which extends from one end to another end side and is configured to receive the shaft inserted therethrough; a boss portion formed at one end side of the main body; and a joint portion, which is formed on an inner peripheral surface of the insertion hole at the boss portion and is welded to the shaft.

Abstract: A gas turbine engine comprising a planetary gear train, and a core engine casing. The gear train has a ratio of greater than approximately 3.0, with an input to the gear train being operatively connected to the compressor section, and an output from the gear train being operatively connected to the fan. The core engine casing encloses the compressor section and the turbine section. The fan has a diameter F, and the core engine casing has a diameter C. The core engine casing diameter C varies along an axial length of the core engine casing, and a ratio (C/F) of the core engine casing diameter C to the fan diameter F is within the range 0.2<(C/F)<0.4, along an axial length of the core engine casing.

Abstract: An example centrifugal compressor includes a housing that defines an inlet chamber and includes first and second openings that define a recirculation passage in fluid communication with the inlet chamber. An impeller is disposed within the housing and is rotatable about a longitudinal axis to draw fluid into the inlet chamber. The first and second openings are at different axial locations along the longitudinal axis. A plurality of inlet guide vanes are rotatable and situated in the inlet chamber. The centrifugal compressor includes a ring and a controller for moving the ring along the longitudinal axis between a first position and a second position when rotating the inlet guide vanes. The ring obstructs at least one of the first and second openings more in the second position than in the first position.

Abstract: A ceramic matrix composite gas turbine blade comprising a root portion coupled to a disk, said root portion having a neck; a platform region is disposed along an upper portion of the neck; an airfoil is located opposite the neck relative to the platform and extends outwardly from the platform; and a limiting section fuse formed in the blade proximate the neck.

Abstract: A ceiling fan including a retention system and method of redundantly retaining a ceiling fan can include a ceiling fan motor assembly including a hollow motor shaft at least partially surrounded by a motor housing. A retainer plate is provided at the bottom of the motor housing including an opening. A retainer rod extends through the opening in the retainer plate and secures to the retainer plate. A support cable couples to the retainer rod to suspend the retainer plate from a structure, wherein the retainer plate is configured to redundantly retainer the ceiling fan.

Abstract: A ceiling fan assembly including a stator assembly having a non-rotating motor shaft and stator slidably and non-rotationally coupled to the non-rotating motor shaft, a rotor assembly, a first bearing slidably mounted to the non-rotating motor shaft and rotatably coupling the rotor assembly to the stator assembly, and a first spacer located between the first bearing and the stator assembly to fix the sliding location of the first bearing relative to the stator along the non-rotating motor shaft.

Abstract: A ceiling fan comprising a motor having a rotating blade hub and a downrod mount. The ceiling fan also has multiple blades mounted to the rotating blade hub. The downrod has an upper end configured to mount to a structure and a lower end with a mount motor. The ceiling fan also has multiple studs provided in one of the downrod mount or the motor mount and corresponding openings provided in the other of the downrod mount or the motor mount. The studs are received within the openings to aid in securing the downrod to the motor assembly.

Abstract: Method for operating a wind turbine, the wind turbine including a wind characteristics sensor for measuring a wind characteristic and at least one wind turbine state sensor for measuring a state of the wind turbine, the method comprising: determining or adjusting (102) one or more wind characteristics relationships; and, performing (104) an operation phase, the operation phase including: measuring the wind characteristics with the wind characteristics sensor, thereby obtaining measured wind characteristics; measuring the state of the wind turbine with the at least one wind turbine state sensor and determining an estimated wind characteristics from the measured state of the wind turbine and parameters of the wind turbine; comparing the estimated wind characteristics to an expected wind characteristics determined from the measured wind characteristics, wherein the expected wind characteristics is determined based on the one or more wind characteristics relationships; and, operating or shutting down the wind tur

Abstract: A fan includes a fan hub and a plurality of blades. At least one of the blades includes an axial blade portion and a centrifugal blade portion. The axial blade portion has an axial arc surface. The axial arc surface extends between opposite two edges of the at least one blade, and connects with one of the two edges. The centrifugal blade portion has a guide trench. The guide trench extends away from the centrifugal blade portion. A width of the guide trench increases as it extends away from the centrifugal blade portion.

Abstract: A vane arc segment includes a continuous airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The airfoil section has a pressure side and a suction side. The first platform defines axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along at least a portion the axially-sloped suction side circumferential mate face.

Abstract: A propulsion assembly includes a fan and a fan case system disposed about the fan. The fan case system includes at least one perforated portion including a plurality of holes. The propulsion assembly further includes at least one acoustic panel mounted to the exterior surface of the fan case system coincident with the at least one perforated portion. The at least one acoustic panel includes a core including a plurality of cells extending between a first side of the core and a second side of the core. The at least one acoustic panel further includes a back skin attached to the second side of the core. The first side of the core is in contact with the exterior surface of the fan case system to form a plurality of resonant cavities defined by the plurality of holes, the plurality of cells, and the back skin.

Abstract: A rotorcraft main rotor system, including a yoke, a rotor blade, and a grip assembly attaching the rotor blade to the yoke. The grip assembly includes a grip body formed from a contiguous laminated composite and has a substantially constant thickness, where the grip body has an upper extension, a lower extension and a connecting portion connected between an inboard end of the upper extension and an inboard end of the lower extension. An inside surface of the upper extension faces, and is substantially parallel to, an inside surface of the lower extension, and the upper extension has first features and the lower extension has second features that are aligned with the first features, where the first features and second features each include at least one of an edge contour, attachment holes, or first protective elements.

Abstract: A ceiling fan assembly an upper motor housing, a lower motor housing, and a magnet seat formed in a portion of the upper and lower housing configured to seat a rotor comprising one or more magnets and mount the rotor to the upper and lower motor housings.

Abstract: A ceiling fan assembly a motor assembly having a non-rotating, hollow, motor shaft, a stator winding carried by the motor shaft, a wiring harness passing through the hollow of the motor shaft and electrically coupled to the stator winding.

Abstract: To provide an unmanned aerial vehicle that eliminates or minimizes the laboriousness involved in optimal pitch adjustment of propellers while eliminating or minimizing complexity and instability in airframe structure and/or flight programs. This object is solved by an unmanned aerial vehicle that is provided with a plurality of rotors and that includes: a center frame that is a central portion of an airframe of the unmanned aerial vehicle; and a plurality of arms extending radially from the center frame in plan view. A plurality of motors that are driving sources of the respective rotors are provided in the center frame. The plurality of rotors are supported by the respective arms. Each arm of the arms has a hollow cylindrical structure. A motive power transmission member configured to transmit a driving force of each motor of the motors to the each rotor is provided in the each arm.

Abstract: A swashplate assembly of a rotary wing aircraft includes a first component, a second component arranged concentrically with the first component, and a bearing disposed between the first component and the second component. The bearing includes a spherical bearing and at least one bearing roller element and is operable to transmit torque between the first component and the second component.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extending from a nozzle ring though slots in a shroud, are shaped on one side to as to substantially conform to the profile of the surface of the slot, whereby a close connection can be formed between the vane and the slot to inhibit leakage of gas between the vane and the slot surface.