Abstract: Proposed is an airfoil wing-shaped aircraft including a body having a wing-shaped longitudinal cross-section and having an upper surface on which a shape of a concave curvature-surface portion is formed along a center axis in a streamwise direction, a fluid inlet being formed in each of the opposite lateral sides of a leading portion of the body, and a fluid output being formed in each of the opposite lateral sides of a tail portion of the body, wherein a duct connects the fluid inlet and the fluid outlet to each other.

Abstract: A method for determining a mass flow of a dynamic compressor that does not include a mass flow sensor while the compressor is operating to compress a working fluid includes determining, by a processor, a current operating point of the compressor. If the current operating point is the same as one in a map of a plurality of predetermined operating points stored in a memory, the mass flow of that predetermined operating point is retrieved as the mass flow of the current operating point. Otherwise, the processor calculates the mass flow at the current operating point from the mass flows of a subset of the predetermined operating points nearest the current operating point. The dynamic compressor continues to operate to compress the working fluid based at least in part on the calculated mass flow rate for the current operating point.

Abstract: The present disclosure discloses a hiding fan, the hiding fan includes a turntable, a plurality of fan blades, and a synchronization mechanism, the synchronization mechanism includes a rotation ring and a plurality of connection rods, the rotation ring is mounted on the turntable, the rotation ring can rotate relative to the turntable around a central axis of the turntable, each fan blade has an installation end and a free end, the installation end has an installation portion and a connection portion, the installation portion is mounted on the turntable through a first rotation connection portion, a first end of the connection rod is mounted on the turntable on the rotation ring through a second rotation connection portion, a second end of the connection rods is mounted on the connection portion, the fan blade can rotate around a central axis of the first rotation connection portion.

Abstract: A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.

Abstract: A turbine engine comprising an engine core, a plurality of circumferentially arranged vanes, and a floating seal. The plurality of circumferentially arranged vanes forming an upper band and a lower band. The floating seal being carried by at least one respective vane of the plurality of circumferentially arranged vanes. The floating seal having a ring and at least one dynamic seal.

Abstract: A scroll structure of a centrifugal compressor includes, of a flow passage connection section where a scroll start portion and a scroll end portion of a scroll flow passage intersect, a connection region where a first inner circumferential surface of the scroll end portion in the centrifugal compressor and a second inner circumferential surface of the scroll start portion in the centrifugal compressor are connected. The connection region includes a turning start point where a direction starts to change from the first inner circumferential surface toward the second inner circumferential surface, and a turning end point where the change in direction from the first inner circumferential surface toward the second inner circumferential surface comes to an end.

Abstract: There is provided a pit initiation evaluation system or the like capable of predicting pit initiation effectively and at low cost. In a pit initiation evaluation system of an embodiment, a pit initiation evaluation unit creates and retains, based on a dry-wet alternate time data, a deposit impurity concentration data, and a pit initiation data on pitting corrosion initiated in each of a plurality of turbine stages when an operation is actually performed in the steam turbine, a pit initiation evaluation table presenting a relationship between a dry-wet alternate time, a deposit impurity concentration, and pit initiation. Further, the pit initiation evaluation unit is configured to evaluate, by using the pit initiation evaluation table, pitting corrosion to be initiated in each of the plurality of turbine stages in an operation planned for the steam turbine.

Abstract: Each of a plurality of blades of a turbofan includes a thick wall portion, a thin wall portion and a stepped portion. The stepped portion is formed between the thick wall portion and the thin wall portion. A plate thickness of the stepped portion is progressively decreased toward a positive pressure surface of the blade in a direction that is directed from the thick wall portion toward the thin wall portion. In the blade, a first curved surface forms a negative pressure surface of the thick wall portion, and a second curved surface forms a negative pressure surface of the thin wall portion while the second curved surface is located on a side of the first curved surface where the positive pressure surface of the blade is placed, and a negative pressure surface of the stepped portion connects between the first curved surface and the second curved surface.

Abstract: A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight assembly is configured to balance a weight distribution of the rotor assembly.

Abstract: A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight located in a space radially between the first rotor and the second rotor.

Abstract: A wind turbine rotor blade spar cap includes a stack of layers of conductive material. An intermediate layer is bonded between adjacent layers of the conductive material. The intermediate layer includes a portion of conductive material which is electrically coupled to the adjacent layers of conductive material so as to equipotentially bond the adjacent layers of the conductive material via the intermediate layer.

Abstract: A damper element for a vibration dampening system may be used in a body opening in a rotating blade in a turbine. The damper element includes a base member having an axially fixed position within the body opening, and a spring-suspended bearing member having a spring fixedly coupled to the base member at a first end of the spring and a bearing member coupled to a second end of the spring. With the spring in an elastically extended state under influence of a centrifugal force caused by rotation of the rotating blade at higher than a predefined rotational speed, the bearing member frictionally engages a bearing surface to dampen vibration. The spring-suspended bearing member provides a friction-based vibration dampening interface that experiences a reduced impact of the centrifugal forces of the rotating blade by providing a counteracting force reduction using the spring.

Abstract: The present invention relates to a fan blade of a turbomachine comprising a structure made of composite material comprising a fibrous reinforcement obtained by three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded, which comprises a first portion forming the suction-side wall and a second portion forming the pressure-side wall, the strands of the fibrous reinforcement comprising first strands comprising carbon or aramid fibres, the Young's modulus of which is greater than 250 GPa, and second strands produced from a viscoelastic material and having a Young's modulus less than 10 GPa, the first portion comprises uniquely first strands whereas the second portion comprises second strands.

Abstract: A gas turbine engine includes a propulsor section and a speed change mechanism for driving the propulsor section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers extending from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first propulsor section support bearing is mounted on a first axial side of the speed change mechanism and a second propulsor section support bearing is mounted on the bearing support on a second axial side of the speed change mechanism. The second propulsor section support bearing is a propulsor thrust bearing. Each of the plurality of fingers include a pin opening with a pin extending through the pin opening and into the epicyclic gear train.

Abstract: A blower is provided that may include a fan that creates airflow; a lower body forming a lower space therein in which the fan may be disposed, and having at least one suction hole through which air passes; a first upper body positioned above the lower body, and forming a first inner space that communicates with the lower space of the lower body; a second upper body positioned above the lower body, and forming a second inner space that communicates with the lower space of the lower body, the second upper body being spaced apart from the first upper body; and a space formed between the first upper body and the second upper body, and opened in a frontward-rearward direction. The first upper body may include a first slit formed through the first upper body such that air in the first inner space may be discharged into the space, and the second upper body may include a second slit formed through the second upper body such that air in the second inner space may be discharged into the space.

Abstract: A Multi-Purpose Portable Fan, which may include a hand-held-style fan to enhance the atmosphere at an event while having a mobile device application, which may be able to summon aid when needed. The hand-held style fan may have located in a handle and/or otherwise lights, or a fan array with LED lights. The handle may be configured with a multi-position switch, a global positioning system-enabled location transmitter and/or receiver, at least one universal serial bus port, at least one solar panel, a battery status display, a wiring interface for LED lights and/or other included electronic devices, and a mobile device application interface. The mobile device application may include at least one interface such as a sign-in interface, a color-select interface, and a situation interface.

Abstract: A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

Abstract: A blower unit for a vehicle and an air conditioning device including the same, the blower unit including: a scroll casing having an inlet port; a fan rotatably disposed in the scroll casing; a motor having a shaft coupled to the fan; and a bell mouth disposed in the inlet port, in which an inner end of the scroll casing, which defines the inlet port, is disposed to be spaced apart from the fan in a radial direction to define a separation space, and the bell mouth prevents air, which flows by a rotation of the fan, from flowing reversely through the separation space. The blower unit and the air conditioning device including the same prevent air from flowing reversely to the outside of the scroll casing by means of the arrangement of the bell mouth and the scroll casing and the structural shape of the bell mouth.

Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.

Abstract: A compression system comprises a compressor, an inlet duct, a throttling valve installed in the inlet duct, an outlet duct, an anti-surge valve fluidly coupling the outlet duct with a portion of the inlet duct downstream of the throttling valve and a recycle valve fluidly coupling the outlet duct with a portion of the inlet duct upstream of the throttling valve. Keeping the recycle valve open, the anti-surge valve closed and the throttling valve partially closed allows lowering the pressure of the flow entering the compressor during its start-up.