Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

Abstract: Provided is a method of correcting a measurement value of least one wind characteristic, in particular wind speed and/or wind direction, related to a wind turbine having a rotor with plural rotor blades at least one having an adaptable flow regulating device installed, the method including: measuring a value of the wind characteristic; obtaining state information of the adaptable flow regulating device; and determining a corrected value of the wind characteristic based on the measured value of the wind characteristic and the state information of the adaptable flow regulating device.

Abstract: A vacuum pump comprises: a rotor; a stator; a first heating section configured to heat the stator cylindrical portion to a temperature for reducing product accumulation; an exhaust pipe provided at a housing storing the rotor and the stator to discharge gas discharged by the rotor and the stator to an outside of the housing; a second heating section configured to heat the exhaust pipe to a temperature for reducing product accumulation; and a gas passage container arranged in the housing, having an inlet port into which gas discharged through a gap between the rotor cylindrical portion and the stator cylindrical portion flows and an outlet port from which inflow gas flows to the exhaust pipe, and heated to a temperature for reducing product accumulation. A gas-inflow-side end portion of the exhaust pipe is inserted into the outlet port of the gas passage container through a clearance.

Abstract: Provided is a wave force utilization unit capable of further reducing product cost and installation cost and effectively utilizing a wave force while decreasing the wave force, and a wave force utilization system in which the unit is used. The wave force utilization unit includes a box-shaped floating unit 1 supported via a support to move in an up-down direction, in response to movement of the sea surface in the up-down direction. The floating unit 1 includes a main body 2, an introduction part 3 disposed continuously on one side of the main body 2, and a water drain part 4 disposed continuously on the other side of the main body 2, the main body 2 includes an air chamber 5 that is a sealed space and acts to float up the floating unit 1, and a flow-through chamber 6 through which seawater flows from the introduction part 3 to the water drain part 4.

Abstract: An exhaust duct assembly includes: a case having an inner space; a duct inserted into an inner space of the case, the duct including an inlet through which an exhaust gas is introduced, and an exhaust port through which the exhaust gas is exhausted; a stiffener configured to attach the duct to the case; and a connector disposed on the exhaust port, wherein the duct, the stiffener and the connector are welded to one another such that at least a portion of each of the duct, the stiffener and the connector overlaps one another in a first direction.

Abstract: A multi-engine system for an aircraft, has: a first engine having a first output shaft, a first core shaft, and a first electric machine drivingly engaged by the first output shaft or the first core shaft; a second engine having a second output shaft, a second core shaft, and a second electric machine drivingly engaged to the second core shaft; a reduction gearbox drivingly engaged by the first output shaft and by the second output shaft for driving a common load; and a transmission path between the first engine and the second engine, the transmission path being independent from the reduction gearbox and being one or more of: a torque-transfer connection between the second core shaft and the first core shaft or the first output shaft via a coupling gearbox, and an electrical connection between the generator and the electric motor to transmit electrical power to the electric motor.

Abstract: The gas turbine engine can have an engine core; a core output shaft drivable by the engine core; a power output shaft; an auxiliary power shaft; and a reduction gearbox having gears, the gears drivingly connecting the core output shaft to the auxiliary power shaft. The gears can include an epicyclic gearing drivingly connecting the core output shaft and the auxiliary power shaft to the power output shaft. The gas turbine engine can further have a second auxiliary power shaft interconnected to the auxiliary power shaft, the power output shaft, and the core output shaft by the gears.

Abstract: A structure is provided that includes a perforated first skin, a second skin and a core. The core includes a first sidewall, a second sidewall, a first baffle and a second baffle. The core forms a plurality of cavities vertically between the perforated first skin and the second skin. The first baffle is connected to the perforated first skin at a first baffle first end. The first baffle is connected to the second skin at a first baffle second end by a first moveable joint. The second baffle is connected to the perforated first skin at a second baffle first end. The second baffle is connected to the second skin at a second baffle second end. A first of the cavities extends laterally between the first sidewall and the second sidewall. The first cavity extends longitudinally between the first baffle and the second baffle.

Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.

Abstract: A propeller apparatus of an air mobility may include blades configured for being folded or unfolded in a response to flight situation of the air mobility, so that energy efficiency of the air mobility is improved and flight distance is increased by efficient use of the plurality of blades in each flight situation. Furthermore, as a pitching motion of the plurality of blades is performed in addition to a folding or unfolding motion of the plurality of blades, flight performance is improved.

Abstract: A propulsion system for use with an aircraft includes a gas turbine engine, an electric power system, and at least one propulsor. The gas turbine engine includes a compressor, a combustor, and a turbine. The electric power system includes a generator coupled to the gas turbine engine to generate electrical energy, power electronics connected to the generator to receive the electrical energy from the generator, and a motor configured to produce rotational energy in response to receiving electric energy from the power electronics. The propulsor is configured to use rotational energy received from the motor of the electric power system to generate thrust for propelling the aircraft.

Abstract: A system for retaining a folded proprotor blade in flight. The system includes a mounting plate, a first arm coupled to the mounting plate at an acute angle relative to the mounting plate, and a first deformable pad affixed to the first arm and adapted to contact the folded proprotor blade.

Abstract: Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.

Abstract: Provided is an adaptable spoiler for a wind turbine blade, including: a flexible body including: an outer surface to be exposed to air flow; an internal surface limiting a cavity to be inflated with fluid to different level, wherein a shape and/or position and/or orientation of the surface to be exposed to air flow changes upon inflating the cavity to different level.

Abstract: Provided is an adaptable spoiler for a wind turbine rotor blade, including: a base element adapted to be connected at or integrated with a rotor blade; an airfoil element being attachable to the base element and having an airfoil shaped surface to be exposed to an air flow.

Abstract: Provided is an arrangement for releasing fluid from a deformable container adapted to modify a state of an adaptable flow regulating device of a wind turbine rotor blade, the arrangement including: a valve connectable to the container; an exhaust tube connected to the valve, wherein the valve is adjustable to allow fluid communication between a lumen of the container and a lumen of the exhaust tube.

Abstract: A fan track liner for a fan containment arrangement for a gas turbine engine comprises a cellular impact structure and a supporting sub-laminate integrally formed with each other from a fibre-reinforced polymer material.

Abstract: The invention provides a rotor assembly for a vacuum pump. The rotor assembly comprises a hub and one or more rotor blade arrays each comprising at least one rotor blade, each rotor blade extending from a rotor blade root contiguous with the hub to a rotor blade tip, wherein each rotor blade comprises a continuous fibre reinforced matrix material. The invention further provides methods of designing and manufacturing rotor blades, and vacuum systems comprising a component comprising a continuous fibre reinforced matrix material.

Abstract: Provided is an arrangement for controlling inflow and outflow of a fluid into and out of an expandable container arranged to change a state of an adaptable flow regulating device installed at a wind turbine rotor blade, the arrangement including: an inflow valve arranged to control fluid inflow into the container; an outflow valve arranged to control fluid outflow out of the container; wherein the inflow valve and the outflow valve are configured to prohibit fluid flow into and/or out of the container in case of safety stop event.

Abstract: A turbomachine inner housing for a radial turbomachine, wherein the turbomachine inner housing includes a partial joint along a longitudinal axis, in particular a rotor longitudinal axis, such that the turbomachine inner housing can be divided into a lower part and an upper part, wherein the turbomachine inner housing is designed for a radial turbomachine with at least two stages, wherein the turbomachine inner housing has a return stage in each case between two stages, wherein the lower part and/or the upper part is designed in one piece so as to span at least two stages at least in sections. In order to improve a turbomachine inner housing of this kind, the lower part and/or the upper part is designed in one piece so as span at least two stages at least in sections.