Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: •? pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, •? a speed reducer fixedly mounted inside the pipe along the longitudinal axis, •? at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and •? at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a blade track assembly and a carrier assembly. The blade track assembly includes a blade track segment made of ceramic matrix composite materials and arranged to define a portion of a path of the turbine shroud assembly. The carrier assembly includes a carrier segment made of metallic materials that supports the blade track segment to locate the blade track segment radially outward of the axis.

Abstract: A heatshield for a gas turbine engine, includes a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface. The first surface being exposed to a hot working gas in use passing through the gas turbine engine. The heatshield having a leading hook and a trailing hook each extending between the lateral edges, the leading hook and the trailing hook extending from the second surface. A stiffening structure extends from the leading hook to the trailing hook and free from direct contact or attachment to the second surface.

Abstract: The present document relates to an annular assembly for a turbomachine turbine, in particular of an aircraft, said annular assembly extending about a longitudinal axis X and comprising: a distributor fixed to an external casing; a bladed disc mounted so as to rotate inside the external casing; said bladed disc being surrounded by a circumferentially segmented ring carried by the external casing and formed by a crown arranged radially on the outside of the bladed disc and by an annular deflector that is carried by an upstream edge of the crown and extends radially towards the inside from said upstream edge of the crown; characterized in that it comprises sealing members (56) between two circumferentially adjacent ring segments, these sealing members (56) comprising first circumferential sealing means (58) between two circumferentially consecutive deflector segments.

Abstract: A method of controlling at least one adaptable airflow regulating system, in particular spoiler and/or flap, of at least one rotor blade of a wind turbine having a wind turbine tower includes: determining a quantity related to a distance between the rotor blade and the wind turbine tower; controlling the airflow regulating system based on the quantity.

Abstract: A turbine housing has a scroll part, an outlet pipe, and an inlet pipe. A bypass passage is formed on an inner peripheral side of a twisting form leading from the inlet pipe toward the scroll part so as to allow communication between an inlet passage and an outlet passage. Viewing the turbine housing in an axial direction, an opening center of an outlet opening of the bypass passage is located in a quadrant where a mounting flange is located among four quadrants defined by a first imaginary plane that passes through a rotational center and that is parallel to a surface of the mounting flange, and a second imaginary plane that passes through the rotational center and that is orthogonal to the first imaginary plane.

Abstract: A turbomachine includes a rotor shaft having an outer surface, a seal carrier forming an annulus about the rotor shaft, and a seal member. The seal carrier at least partially defines a pressure chamber. The turbomachine further includes a seal member support system including a flex body having a contact portion in contact with the seal carrier, and a flex portion extending from the contact portion towards the outer surface of the rotor shaft. The flex portion is coupled to the seal member and is configured to hold the seal member at a radial distance away from the outer surface of the rotor shaft when a pressure inside the pressure chamber is equal to or below a minimum pressure threshold value, and to flex and move the seal member towards the outer surface of the rotor when the pressure inside the pressure chamber exceeds the minimum pressure threshold value.

Abstract: A ceiling fan blade assembly structure includes a blade holder, multiple fan blades, and multiple locking assemblies. Multiple fan blade assembly portions are disposed at an outer side of the blade holder. Each fan blade assembly portion includes two first side plates parallel to each other, a first radial positioning portion, and two first vertical positioning portions disposed on the two first side plates. Each fan blade has a fan blade connection portion that includes two second side plates, a second radial positioning portion, and two second vertical positioning portions. The second and the first radial positioning portions are engaged with each other, and the two second and first vertical positioning portions are engaged with each other. Accordingly, the fan blade connection portion is preliminarily positioned on the fan blade assembly portion. Through the locking assembly, the first and the second radial positioning portions are locked together.

Abstract: A platform assembly for a hub of a wind turbine is configured to provide a working surface inside the hub. The platform assembly includes a first platform coupled to a hub access structure, wherein the hub access structure extends in an axial direction between a nacelle of the wind turbine and the hub and provides access from the nacelle to the hub.

Abstract: A flow path component assembly includes a flow path component that has a platform that extends from a first circumferential side to a second circumferential side. The platform has a first radius of curvature between the first circumferential side and the second circumferential side. A coating is arranged on a portion of the platform near the first circumferential side. The coating has a second radius of curvature. The second radius of curvature is larger than the first radius of curvature.

Abstract: Disclosed is an energy converting apparatus for converting mechanical energy obtained by a fluid flow into electric energy. The energy converting apparatus comprises: a blade; a measuring device for measuring reaction of the blade when the fluid flow exerts an external force on the blade, and generating a measurement value corresponding to a measurement result; a memory for storing control values; a controller for reading a first control value among the control values from the memory in response to the measurement value output from the measuring device, and generating a control signal by using the first control value; and an actuator for changing a three-dimensional shape of the blade in response to the control signal output from the controller.

Abstract: A fuel system is disclosed for a gas turbine engine, which includes an augmentor pump having an inlet communicating with a fuel supply source and a discharge communicating with an augmentation stage of the engine, wherein the augmentor pump is connected to an accessory drive gearbox mounted to the engine, and a high speed clutch for selectively engaging and disengaging the augmentor pump and the accessory drive gearbox.

Abstract: An arrangement for an aircraft turbine engine, including a shaft and a follower element rotatably coupled to the shaft by a spline connection, the arrangement including upstream and downstream connections for radially centring the follower element relative to the shaft; means for spraying a lubricant into a collection cavity; a passage for receiving lubricant, which passage opens into the collection cavity and into a cavity for lubricating the splines which is partially defined by the upstream and downstream radial centring connections; and a passage for discharging lubricant, which passage opens into the cavity for lubricating the splines and outside the arrangement.

Abstract: A fresh air module and an air conditioner are provided. The fresh air module has a housing and a fan assembly. The housing has a fresh air duct inside the housing. The fan assembly has a motor and a wind wheel disposed in the fresh air duct. The motor has a motor body and a motor shaft. The motor shaft drives the wind wheel to rotate, so as to guide airflow to flow through the fresh air duct. The motor cover is arranged on the housing and outside of the fresh air duct. A motor accommodating cavity is defined in the motor cover and accommodates the motor body. A partition member is formed between the motor accommodating cavity and the fresh air duct to separate the motor accommodating cavity from the fresh air duct. The motor shaft penetrates through the partition to connect with the wind wheel.

Abstract: A flow control device for constraining fluid flow between axial flow turbomachines in series has a flow constrainer which constrains the fluid flow downstream of the first turbomachine in the series to the blades region of the second turbomachine, preventing fluid flow from impacting the hub or nosecone of the second turbomachine and providing more uniform fluid flow to the second turbomachine. The flow control device includes connective elements for positioning between the downstream region of the first turbomachine and the upstream region of the second turbomachine. The device may be equipped with stator vanes having a variety of optional configurations to further improve the uniformity of the fluid flow load on the second turbomachine.

Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A rigid connection between a fan case and an inner core housing includes a plurality of A-frames connected at a connection point to the fan case. Legs in the A-frames extend away from the connection point in opposed circumferential directions to be connected to a compressor wall of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes rigidly connected to the fan case. A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.

Abstract: The composite seal structure includes a carrier ring and a seal element housed in an annular groove formed between a circumferential outer wall and two side walls of the carrier ring. The seal element has a first region in surface-to-surface contact with the annular groove and a second, seal-ing region protruding from the annular groove. A fastening arrangement couples the seal element and the carrier ring to one another. The fastening arrangement comprises a plurality of fastening pins circumferentially arranged around the axis of the carrier ring. Also disclosed is a method for manufacturing the seal structure.

Abstract: A portable system for converting wind energy into electrical energy is disclosed. The disclosed system may include a frame hosting one or more conversion modules, arranged as desired. A given conversion module may include one or more wind energy conversion devices (WECDs), arranged as desired. The conversion modules may be electrically connected, directly or indirectly, with one or more downstream electrical energy storage elements (e.g., such as a battery or other capacitive element, optionally native to a host platform). In this manner, the disclosed system may be configured for use in storing and/or supplying electric power for downstream consumption by a host platform or otherwise. In a more general sense, the disclosed system may be utilized, for example, for micro-generation of renewable electrical energy from wind.

Abstract: A mastless vertical axis wind turbine that comprises a plurality of sails that rotate about a vertical axis under the influence of wind. A platform is connected to and in tension with the plurality of sails at one or more points about the bottom of the plurality of the sails. Also, an external frame is connected to and in tension with the plurality of sails at one or more points about the top of the plurality of the sails. The external frame itself comprises a plurality of legs that converge above the plurality of sails at a central point about the vertical axis of rotation and extend beyond the path swept by the plurality of sails. A coupling mechanism connects one or more of the plurality of legs to the plurality of sails and allows the sails to rotate about the vertical axis of rotation while the legs remain stationary.

Abstract: Provided is a method for identifying a blade malposition of a rotor blade of a wind power installation having one rotor and at least three rotor blades which in terms of the blade angles thereof are individually adjustable. For each rotor blade an actual angle is detected as the actual value of the blade angle; and the blade malposition is identified as a function of a blade angle deviation of the rotor blade and a rotational progress of the rotor. The blade angle deviation describes a deviation of the actual angle from a reference angle, and the rotational progress is representative of an angle about which the rotor has rotated onward after a start criterion. Blade malpositions in rotor blades which in terms of the blade angles thereof are individually adjustable are identified rapidly and reliably.