Abstract: An impeller apparatus includes a housing, an impeller, and a heat generation member. The housing includes an air duct formed in the housing. The air duct includes a first air duct and a second air duct successively connected to each other. The second air duct has a non-blocking area. The impeller is arranged in the first air duct. The heat generation member is rotatably arranged in the second air duct and has a blocking state and a non-blocking state. In the blocking state, the heat generation member blocks the second air duct, in the non-blocking state, the heat generation member is accommodated in the non-blocking area and does not block the second air duct.

Abstract: A blower housing comprises first and second blower housing pieces for surrounding a blower fan. The first blower housing piece comprises a blower discharge section comprising an inner tubular portion, an outer tubular portion, and a drain hole. The inner tubular portion defines a blower discharge passage. The inner and outer tubular portions define an exhaust pipe cavity adapted to receive an end margin of an exhaust pipe. The tubular portions are adapted to enable condensate water that forms on the inner surface of the exhaust pipe to flow into the exhaust pipe cavity. The drain hole extends through the outer tubular portion. The drain hole is configured to enable condensate water flowing into the exhaust pipe cavity to drain from the blower housing. The first blower housing piece is a molded one-piece member.

Abstract: A blower assembly for an HVAC system includes a blower wheel, which includes a plurality of blades. A laminated insert is concentric with the blower wheel and radially inward of the plurality of blades. A shaft is coupled to the blower wheel through the laminated insert.

Abstract: A wind turbine nacelle configured for mounting on a wind turbine tower and for supporting a rotor-supporting assembly, the nacelle comprising a main unit, and at least one auxiliary unit. The auxiliary unit accommodates at least one operative component, e.g. a converter, a transformer, an electrolysis cell, or a battery. An operative component having a similar function is accommodated in another auxiliary unit which thereby facilitate shared operation, and easy and fast maintenance or replacement of the operative component.

Abstract: Embodiments provide a propeller ground stop mechanism configured to keep an unpowered propeller of an aircraft (e.g. when the aircraft is on the ground and not operating) static. The propeller is prevented from rotating due to external forces (e.g. an air flow caused by wind, manual rotation of the propeller). When the propeller is powered, and the propeller is providing thrust, the propeller ground stop mechanism automatically disengages and does not provide any drag. Among various benefits, the propeller ground stop mechanism provides added safety to the ground support personnel.

Abstract: An apparatus includes a ceiling fan and an accessory. A receiver is adapted to attach to the ceiling fan, and an adaptor for the accessory is provided. The adaptor is adapted to releasably attach to the receiver and fix the accessory in position with respect to the ceiling fan. A dampener may be provided, and receiver may include at least one projection adapted to engage the dampener, thereby inhibiting vibration of the accessory during operation of the ceiling fan. The accessory may also include a gasket, and the receiver may include at least one projection adapted to engage the gasket, thereby at least partially sealing a motor from an environment external to the ceiling fan.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement a low radius ratio fan blade for a gas turbine engine. A fan blade for a gas turbine engine includes an airfoil including a leading edge and a trailing edge extending between a root and a tip of the airfoil, a distance between the leading edge and the trailing edge defining a flow path length, a leading edge hub point defined by a radially innermost point of the leading edge, and an axial dovetail including a pair of opposed pressure faces, an axial length of the axial dovetail less than the flow path length, a top edge of the axial dovetail separating the pressure faces from the airfoil, the top edge of the axial dovetail radially outward of the leading edge hub point.

Abstract: An air-to-air heat exchanger in flow communication with a gas turbine engine is provided. The air-to-air heat exchanger has an air-to-air heat exchanger potential defined by a product raised to a half power, the product being a heat transfer surface area density associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine. The air-to-air heat exchanger potential is between about 6.7 and 19.5 for a bypass ratio associated with the gas turbine engine between about 3 and 10 and the heat transfer surface area density being between about 3,000 m2/m3 and 10,000 m2/m3 and is between about 2.9 and 12.2 for a bypass ratio associated with the gas turbine engine between about 10 and 20 and the heat transfer surface area density being between about 1,000 m2/m3 and 10,000 m2/m3.

Abstract: The present application relates to a propulsion device having a motor, a mast connected to the motor, an angle sensing device detecting the angle of the mast, a controller receiving the angle of the mast as an input and outputting a motor torque signal to the motor in response thereto, a hub attached to the mast via a single skewed hinge, and a propeller assembly with one or more blades connected to a hub.

Abstract: An apparatus includes a fan and a controller configured for controlling the fan to operate in a first mode limiting rotational speed of the fan within a first range of speeds between a first minimum speed and a first maximum speed. The controller is further configured to control the fan to operate in a second mode limiting rotational speed of the fan within a second range of speeds between a second minimum speed and a second maximum speed. The second range of speeds may be narrower than the first range of speeds. Related methods are also disclosed.

Abstract: A woven fibrous preform of a hollow aerodynamic profile of a turbomachine vane or blade, has a non-interlinked trailing edge and a draping of two 3D woven fibrous textures.

Abstract: The present invention relates to a blower vane of a turbomachine, comprising a structure made of composite material which comprises a fibrous reinforcement and a matrix in which the fibrous reinforcement is embedded. The vane comprises a first rigidification insert which extends in a first direction and at least one second insert which is connected to the first in a second direction which is non-collinear with the first direction, the first insert projecting from the vane in order to be connected to a disc of a turbomachine element.

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 rotor blade assembly for a rotary wing aircraft includes a main rotor blade body comprising an upper blade skin, a lower blade skin, an inboard end, an outboard end, and a trailing edge. The rotor blade assembly further includes a trailing edge actuator assembly. The trailing edge actuator assembly includes an upper actuator skin and a lower actuator skin defining a cavity and a trailing edge flap, a control panel disposed in the cavity and coupled to one of the upper actuator skin or the lower actuator skin and one or more actuators disposed in the cavity and configured to apply force to the control panel to cause the trailing edge flap to deflect. The trailing edge actuator assembly is coupled to the trailing edge of the main rotor blade body.

Abstract: Provided is a blowing device capable of improving a noise reduction effect as compared with a conventional case, and a combustion device including the blowing device is provided. In a rear side shroud of an impeller configuring a blowing device, a first inclined surface portion that is inclined so as to be located frontward toward the radial outer side is formed in a front surface portion of the rear side shroud in a region close to the outer peripheral edge, while a second inclined surface portion that is inclined so as to be located rearward toward the radial outer side is formed in a front surface portion of the rear side shroud in a region closer to the center than the first inclined surface portion.

Abstract: Provided are a method for designing a vane, which can reduce peaks of secondary flow losses appearing locally in secondary flow regions and a vane obtained by the designing. The method for designing a vane includes: a step of determining a base vane formed by stacking profiles having airfoil shapes in a spanwise direction along a stacking line which is configured as a smooth curved line having no inflection point or a straight line; and a step of changing the stacking line of the base vane to a smooth wavy curved line which waves in an axial direction of a fan, a compressor or a turbine and has no elbows.

Abstract: A fail safety apparatus of the air mobility is provided. Locations of propeller modules are adjusted by rotation parts and length adjustment units to evenly distribute thrust of the re-located propeller modules so that the attitude of the air mobility is stabilized. In particular, when one propeller module among a plurality of propeller modules fails, the attitude of the air mobility is normalized by adjusting a location of the failed propeller module and locations of remaining normal propeller modules so that flight safety of the air mobility is secured.

Abstract: Disclosed herein is a ceramic matrix composite airfoil comprising a triple bifurcated ply that defines a suction side, an outer platform, a pressure side and an inner platform of the airfoil, wherein the triple bifurcated ply comprises at least one ply that comprises a consolidated region, wherein the consolidated region is split into two bifurcated regions in three locations in three different directions.

Abstract: An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.

Abstract: A fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material including a fibrous reinforcement densified by a matrix, wherein the fibrous texture includes an area of reduced stiffness including warp yarns or strands made of second fibers having a second elongation at break greater than the first elongation at break, the area of reduced stiffness extending in the longitudinal direction from the stilt area and up to a height less than or equal to 30% of the height of the blade, extending in the transverse direction between a first area and a second area, the first area extending over a first length from a first edge of the texture intended to form a leading edge, and the second area extending over a second length from a second edge of the texture intended to form a trailing edge.