Abstract: A rotor wheel for an aircraft turbine engine has a disc with a main axis and cells at its outer periphery. The cells extend along the axis, and each has a bottom and two side flanks. Vanes are mounted in the cells of the disc, each vane including a blade connected by a platform to a root mounted in one of the cells. Each root includes, at its radially inner end, a lobe with a first axial end having a circumferential notch and a second axial end having a radially inward facing stop configured to axially bear on a first face of the disc. An annular ring engages the notches of the vanes and is axially clamped against a second face of the disc. Each lobe has a radially inward facing projecting bulb configured to radially bear on the surface of the bottom of the corresponding cell.

Abstract: An air handler unit for use with residential heating, ventilation, and air conditioning (HVAC) systems. The air handler unit has high resistance mediums (HRMs) coupled closely to a wide-angle vane-diffuser mixed-flow fan system. The HRMs are placed immediately upstream and downstream of the wide-angle vane-diffuser mixed-flow fan to form a closely coupled, compact air handler that provides significant efficiency and noise benefits.

Abstract: A rotor of an aircraft engine has a plurality of blades extending radially from a disc. At least one of the blades has an airfoil, a root and a tip. The airfoil has a crack-mitigating rib extending chordwise along the airfoil. The crack-mitigating rib is disposed radially closer to the root than to the tip.

Abstract: A variable displacement exhaust turbocharger according to at least one embodiment comprises: a plurality of nozzle vanes; an annular drive ring; and a lever plate fitted at one end in a groove portion disposed in the drive ring via a connecting pin portion and connected at another end to each nozzle vane. The value of dimensionless slippage S between the groove portion and the connecting pin portion is equal to or less than 0.0016. The dimensionless slippage S is represented by a certain equation.

Abstract: A control arrangement for a variable-speed wind turbine includes a loading analysis module configured to analyse a number of environment values to establish whether the momentary wind turbine loading is lower than a loading threshold when the rotational speed of the aerodynamic rotor has reached its rated value; and a speed boost module configured to determine a speed increment for the rotational speed of the aerodynamic rotor if the wind turbine loading is lower than the loading threshold.

Abstract: A bracket assembly and a fan with a bracket assembly include: an installation bracket, the installation bracket being equipped with an installation part; and at least one bendable and shapeable supporting leg, the supporting leg being connected to the installation part. Therefore, users can connect the installation bracket to an external device, thereby attaching the bendable and shapeable supporting leg to the external device, so that the external device can be suspended or supported on an external object through the bendable and shapeable supporting leg. At the same time, a support angle of the supporting leg can be adjusted by bending the supporting leg to adjust an angle of the external device. Moreover, a total number of the supporting legs can be set to 3-10, so that the supporting legs can be combined with each other to form an octopus shape to provide stable support.

Abstract: A load mitigation arrangement of a non-mounted rotor blade, includes at least one actuatable lift-modification device arranged on a surface of the rotor blade; a monitor configured to estimate the magnitudes of loads acting on the non-mounted rotor blade; a controller configured to actuate the lift-modification device on the basis of the estimated magnitudes to mitigate the loads acting on the non-mounted rotor blade. Further provided is a rotor blade assembly, and a method of performing load mitigation on a non-mounted rotor blade.

Abstract: An air moving device has a housing with a primary flow path and a secondary flow path that extends from a secondary inlet of the housing and empties into an inner outlet adjacent the primary flow path. An impeller assembly rotates a blade to cause air to enter the housing and flow along the primary flow path. The flow of air through the primary flow path creates a low pressure region at the inner outlet of the secondary flow path, causing air to flow through the secondary flow path and mix with the air in the primary flow path. The mixture of air flows through a downstream portion of the primary flow path having an expanded width compared to an upstream portion of the primary flow path and exits the housing. Stator vanes may extend longitudinally within the housing to cause columnar air flow. The device may be used for destratification of thermal gradients of air within an enclosure, such as a home or warehouse.

Abstract: A hydraulic turbine motor has a rotor housing and a rotor rotatably supported in the rotor housing that defines a plurality of rotor chambers arranged circumferentially about the rotor in which each rotor chamber has a respective outlet port. Injectors are supported at circumferentially spaced locations about the housing so as to be arranged to inject hydraulic fluid in a generally tangential direction relative to the rotor axis into selected ones of the rotor chambers in which the injectors include first and second injectors. A valve mechanism is configured to open any outlet port in which the respective rotor chamber is in communication with one of the first injectors and to maintain closed any outlet port in which the respective rotor chamber is in communication with one of the second injectors.

Abstract: A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots.

Abstract: A component for a gas turbine engine includes a matrix composite component having a radially outer end and a radially inner end. The ceramic matrix component having an internal chamber defined by an inner surface. A spar is received within the internal cavity, and spaced from an inner surface of the matrix component defining a chamber with the inner surface. Flow guides are formed on one of an outer surface of the spar and the inner surface of the matrix component. The flow guides direct airflow towards a portion of the inner surface. An air inlet chamber is formed at one radial end of the spar and an air outlet chamber formed at an opposed radial end of the spar. The air inlet chamber is defined such that air will flow into the internal chamber, outwardly of the spar, and inwardly of the inner surface of the matrix component. A gas turbine engine is also disclosed.

Abstract: The invention relates to a component of a gas turbine engine which has a fiber-composite material having a multiplicity of rovings, wherein at least one roving of the fiber-composite material along the spatial extent thereof has a variable cross section, at least two rovings have in each case a dissimilar cross section and/or the at least one roving follows a variable direction and the at least one roving is deposited by means of tailored fiber placement. The invention also relates to a method of a component.

Abstract: Baffles for installation within airfoils include a baffle body defining a feed cavity and extending between inner and outer diameter ends. A forward standoff shelf is formed along an exterior surface of the baffle and defined by a depression, bend, or channel in a material of the baffle body extending between the inner and outer diameter ends. The forward standoff shelf is configured to engage with a forward rail of the airfoil body, and an aft standoff shelf is formed along an exterior surface of the baffle body and configured to engage with an aft rail of the airfoil body. A surface of the baffle body between the forward standoff shelf and the aft standoff shelf defines a side channel surface extending in a radial direction along the baffle body between the outer diameter end and the inner diameter end.

Abstract: A compressor section includes a compressor disk having a slot receiving a blade with an airfoil extending from a platform and the compressor disk having an upstream end and a downstream end. A cover plate at one of the upstream end and the downstream end covers an area between the blade and the compressor disk across a circumference of the compressor disk. The cover plate covers an area between an inner peripheral surface of the platform to a radially innermost end of the slot in the disk. The compressor disk has hooks, and there is a retention ring mounted in a cavity between the hooks and the compressor disk. The cover plate is mounted between the retention ring and the compressor disk. The retention ring retains the cover plate against the compressor disk. A gas turbine engine is also disclosed.

Abstract: A gas turbine engine includes a compressor section, a combustor section and a turbine section for rotation on an axis. The turbine section includes at least one row of rotating turbine blades each having a radially outer tip. A blade outer air seal is positioned radially outwardly of the radially outer tip. The blade outer air seal has a central web positioned radially outwardly of the radially outer tip. The blade outer air seal has an upstream mount arm and a downstream mount arm receiving mount structure from a static structure. The static structure has sealing members engaging an upstream outer surface of the upstream mount arm at an upstream seal material and a downstream outer surface of the downstream mount arm at a downstream seal material. A method is also disclosed.

Abstract: A cooling jacket for a hollow airfoil of a turbine nozzle of a turbomachine, includes a main body including a central intake duct central defining a first ventilation air circulation area and connected to suction and pressure faces including at least two rows of drill holes by two separating walls defining second and third ventilation air circulation areas, an outer plate including first, second and third holes to allow the ventilation air respectively into the first, second and third ventilation air circulation areas, and an inner plate including a central opening to expel air from the first ventilation air circulation area, the outer and inner plates being secured by respectively soldering to the main body to form a one-piece unit with three ventilation air circulation areas, independent and airtight with respect to one another, before its installation in the hollow airfoil of the nozzle.

Abstract: A system and method are configured to monitor changes associated with an air gap in a brake assembly of a wind turbine yaw drive by: (1) receiving one or more sensor signals from one or more sensors that are indicative of changes associated with the air gap; and (2) comparing the changes associated with the air gap to certain thresholds to determine if the air gap is in need of attention. The system includes at least one proximity sensor arranged adjacent to the air gap, to monitor the air gap, and a controller. The controller is configured to receive the sensor signal(s) indicative of the changes associated with the air gap. The controller also is configured to compare the changes associated with the air gap to one or more air gap thresholds, and to implement a control action based on this comparison.

Abstract: An air turbine starter for starting an engine, comprising a housing having an interior surface defining an interior, at least one turbine member rotatably mounted within the interior about a rotational axis, and having a plurality of circumferentially spaced blades, and a containment structure radially overlying and circumferentially surrounding the at least one turbine member extending between an outer surface and an inner surface to define a radial direction.

Abstract: A turbine ring assembly extending about an axis, includes a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure held by a turbine casing, each ring sector including a base from which an upstream lug and a downstream lug spaced axially from each other extend radially outwardly, the ring support structure including a spacer having a clamp against which the downstream lug of the ring sectors is held, a first upstream flange against which the upstream lug of the ring sectors is held, and upstream of the first upstream flange, a second upstream flange for absorbing forces against which the first upstream flange is held.

Abstract: A rotor for a turbomachine has at least one blade and has at least one rotor main part, which has at least one recess, in which a blade root of the least one blade is interlockingly received, wherein the blade root comprises at least one depression, in which at least one protrusion of the at least one rotor main part, which protrusion delimits the at least one recess in regions is received, wherein the at least one depression is delimited by a first delimiting face on the blade root side and the at least one protrusion is delimited by a second delimiting face on the rotor main part side. At least the first delimiting face has at least one elevation which narrows a gap at least in regions, which extends between the first delimiting face and the second delimiting face.