Abstract: A turbofan engine having one or more heat exchangers tied to an accessory gearbox is provided. The accessory gearbox is mechanically coupled with a spool, and a hydraulic pump is mechanically coupled with the accessory gearbox. The one or more heat exchangers have a heat exchanger capacity defined by a product raised to a half power, the product being determined by multiplying a resultant heat transfer surface area density of the one or more heat exchangers by a heat conductance factor that relates an accessory gearbox heat load, a power of the hydraulic pump, a diameter of a fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 23.9 and 97.7 for a rotational speed of the spool between 7,500 and 35,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 4,000 m2/m3 and 13,000 m2/m3.

Abstract: A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.

Abstract: An aircraft turbomachine rotor has a rotor disc extending transversely with respect to a longitudinal axis X, a plurality of blades, and a damping device. The damping device having: a support ring arranged transversely with respect to the longitudinal axis X and mounted on the outer periphery of the rotor disc, and has a plurality of damping members that are attached to the support ring and project upstream from the support ring, each damping member being configured to extend at least under a platform of a blade so as to exert a radially outward force to dampen the radial movement of the blade when the turbomachine is in operation.

Abstract: A rotor assembly comprises a rotor hub and rotor-blade assemblies. The rotor hub comprises rotor-blade supports. Each rotor-blade assembly is coupled to a respective one of the rotor-blade supports and comprises a flap axle, a hub connector, a rotor blade, and a torsion strap. The flap axle extends through a respective one of the rotor-blade supports and has a central flap-axle axis. The hub connector is pivotable relative to a rotor-blade support about the central flap-axle axis and defines a central hub-connector axis. The rotor blade is coupled to and is pivotable relative to the hub connector, and, together with the hub connector, is pivotable relative to a respective one of the rotor-blade supports about the central flap-axle axis. The torsion strap has a first end, coupled to the rotor blade, and a second end, through which the flap axle passes.

Abstract: A fan casing for an aircraft turbomachine, the casing including a one-piece annular body, the one piece annular body including a radially internal annular surface, a first annular portion of which is made of an abradable material, wherein a second annular portion of the internal surface comprises blind holes conferring acoustic properties to the second portion.

Abstract: A blade for a rotor of a wind turbine having a longitudinal direction with a tip end and a root end and a transverse direction, comprising: a profiled contour that when impacted by an incident airflow, generates a lift, wherein the profiled contour is divided into: a root region having a substantially circular or elliptical profile closest to the hub, an airfoil region having a lift-generating profile furthest away from the hub, and a transition region between the root region and the airfoil region, the transition region having a profile gradually changing in the radial direction to the lift-generating profile of the airfoil region, and further comprising a shoulder, wherein the shoulder is located in the airfoil region, thus yielding a slender and relative thick blade maximizing energy output, reducing bearing loads and facilitating transportation.

Abstract: There is provided an axial flow turbine capable of realizing a reduction in gland leakage amount. The axial flow turbine in an embodiment is of a single flow type and includes an upstream-side gland part located on an upstream side of a working medium in an axial direction of a turbine rotor and a downstream-side gland part located on a downstream side of the working medium in the axial direction of the turbine rotor. The axial flow turbine is configured such that a cooling medium lower in temperature and higher in pressure than the working medium is extracted in a middle of flowing from the inside to the outside of the turbine casing in the upstream-side gland part, and the extracted cooling medium is introduced into the stationary blade.

Abstract: A ceiling fan blade fastening structure includes a base and a fan blade. The base is fixed to a rotor of a motor of a ceiling fan. The base has a bottom wall and a peripheral wall. The peripheral wall has a slot. The bottom wall is provided with a guide rail portion adjacent to the slot. The bottom wall is provided with a bracket and a positioning block behind the guide rail portion. The fan blade has a tongue portion to be inserted into the slot and pressed against the positioning block, so as to position the fan blade. The tongue portion is provided with a stop block to be against the rear of the bracket, so that the fan blade is unable to be disengaged from the slot.

Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

Abstract: A distribution element intended to be fixed to a support structure for supplying cooling fluid to a wall to be cooled facing the distribution element, the distribution element including a body defining a cooling fluid distribution internal volume and a multi-perforated plate which delimits the internal volume and includes a plurality of outlet through-perforations which put the cooling fluid distribution internal volume into communication with the wall to be cooled, the distribution element including an inlet orifice opening into the cooling fluid distribution internal volume, wherein for directing the cooling fluid from the inlet orifice to the plurality of outlet through-perforations the cooling fluid distribution internal volume includes directional fins.

Abstract: A nozzle vane of a variable geometry turbocharger comprises: a nozzle vane body rotatably disposed in an exhaust gas passage defined between a shroud surface and a hub surface; and a fin disposed on at least one of a pressure surface or a suction surface of the nozzle vane body and disposed within a range of 0.6L from a trailing edge of the nozzle vane body, where L refers to a chord length of the nozzle vane body. The fin satisfies a relationship of 0.3L?X, where X refers to a length of the fin along a chord direction of the nozzle vane body.

Abstract: Provided is a method and an arrangement of fatigue testing of a wind turbine rotor blade, the method including: operating an actuator attached to the rotor blade, thereby moving a mass connected to the actuator in a reciprocating manner. The mass may be a hanging mass, for example, hanging down from the actuator.

Abstract: A fan section includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor is a four-stage low pressure compressor. The low pressure turbine is a three-stage low pressure turbine. A high spool including a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine-stage high pressure compressor. The high pressure turbine is a two-stage high pressure turbine. An exhaust gas exit temperature of greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.

Abstract: A rotor vane for an aircraft turbine engine, the vane having an axis of rotation once it has been rigidly connected to a rotor and a stacking axis. The vane includes a blade extending between an internal platform and an external platform bearing at least one projecting lip. The external platform is configured to cooperate in a form-fitting manner with the complementary side edges of adjacent vanes. The rotor vane has wear-resistant covering of a lower side edge which extends over one wall of a substantially rectilinear first ridge of the platform and over one wall of a second ridge of the platform. The second ridge extends at least partially inside the lip and is inclined relative to the first ridge in a direction substantially parallel to a transverse axis of the lip.

Abstract: A wind power installation with an azimuth bearing having an azimuth gearing, and at least one azimuth drive, which is coupled to an azimuth gear mechanism corresponding to the azimuth gearing. The azimuth gear mechanism has a drive pinion which is rotatable about a pinion axis, wherein the drive pinion is configured to engage in the corresponding azimuth gearing of the azimuth bearing, wherein the pinion axis has a predefined reference orientation. The wind power installation comprises at least one sensor device which is configured to detect a deviation of the orientation of the pinion axis relative to the reference orientation.

Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a turbine engine component that includes a sidewall and a cooling aperture. The cooling aperture includes an inlet, an outlet, a meter section, a diffuser section and a transition section between and fluidly coupled with the meter section and the diffuser section. The cooling aperture extends through the sidewall from the inlet to the outlet. The meter section is at the inlet. The diffuser section is at the outlet. The transition section is configured to accommodate lateral misalignment between the meter section and the diffuser section.

Abstract: Ceiling fans typically include a motor including a rotor and a stator, blades, a downrod, and a mounting assembly for suspending the fan from a structure. The mounting assembly includes fasteners and brackets to secure the ceiling fan to the structure. The bracket receiving the downrod is fastened to a plate that is secured to the ceiling.

Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom are described. The core assemblies having a leading edge hybrid skin core positioned relative to a plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil. The leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less.

Abstract: A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.

Abstract: Provided is a wind turbine rotor blade flow guiding device that includes a first portion including a rear surface for facing a surface of a wind turbine rotor blade and a second portion connected to the first portion and extending from the first portion in a first direction along a length, the second portion including a top surface angled at an angle between 90° and 180° with respect to the rear surface of the first portion. The second portion includes a plurality of corrugations extending along the length. The second portion further includes a plurality of openings configured to allow a flow to pass through the second portion. Further disclosed is a wind turbine and a wind turbine rotor blade each including the wind turbine rotor blade flow guiding device.