Abstract: An oil supply system for an aircraft engine having a rotating shaft comprises a retaining nut including a unitary annular body having an outer surface and an inner surface extending around a central axis between a first end and a second end. The inner surface has a threaded portion at the second end. The threaded portion is configured for threaded engagement with a corresponding threaded portion of the rotating shaft. The outer surface of the unitary annular body includes a series of teeth distributed around the central axis of the retaining nut. The teeth are configured for engagement with a tightening tool. A first tooth of the teeth has a first radial oil scoop formed thereon. The first radial oil scoop defines an oil passage extending from the outer surface to the inner surface of the nut at an axial location between the first end and the threaded portion.

Abstract: A method for sizing a section of a junction by orbital friction welding with an eccentric e, between a blade and a stub of a bladed disk for a turbomachine. The sized section has a rounded contour at one or two ends of said section along a chord of the blades, each corresponding to a leading edge or a trailing edge of said blades, said rounded contour(s) having over a sector of at least 120° an average radius of at least twice the eccentric e.

Abstract: An outboard motor includes a power source disposed, a propeller shaft, a drive shaft, a gear mechanism, a lower case having an internal space in which gear oil is stored, a gear oil gauge configured to check a level or a state of the gear oil stored in the internal space, a gauge mounting hole provided configured to removably mount the gear oil gauge to the lower case such that one end side of the gear oil gauge is immersed in the gear oil stored in the internal space, a gauge insertion portion configured to insert the gear oil gauge into the gauge mounting hole, an oil supply and discharge passage provided in the lower case, and a pump connecting portion configured to connect a pump. The gauge insertion portion and the pump connecting portion are arranged side by side.

Abstract: A method includes forming a moulded component that is axisymmetric about a component axis; segmenting the moulded component into a plurality of segments, each pair of adjacent segments including a pair of surfaces that is formed during segmentation of the moulded component; providing, via computerised numerical control machining, complementary finger joint profiles on the pair of surfaces of the each pair of adjacent segments; providing a plurality of slots on at least one of the pair of surfaces of the each pair of adjacent segments; positioning a plurality of blades partially within the plurality of slots; mating the complementary finger joint profiles provided on the pair of surfaces of the each pair of adjacent segments; and joining the each pair of adjacent segments to each other, such that the plurality of blades is retained within the plurality of slots.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: Embodiments provide a propeller ground stop mechanism configured to keep an unpowered propeller of an aircraft (e.g. when the aircraft is on the ground and not operating) static. The propeller is prevented from rotating due to external forces (e.g. an air flow caused by wind, manual rotation of the propeller). When the propeller is powered, and the propeller is providing thrust, the propeller ground stop mechanism automatically disengages and does not provide any drag. Among various benefits, the propeller ground stop mechanism provides added safety to the ground support personnel.

Abstract: An air blower and a combustion device including the air blower are provided. An air blower includes an impeller housed in a casing and rotating. The impeller includes multiple blades to form multiple inter-blade passages, and a central space portion. When the impeller rotates, air flowing into the central space portion through an air intake port of the casing passes through the inter-blade passages at an outward side. To reduce noise generated when the air passes through the inter-blade passages, each blade includes: multiple first concavo-convex portions, with a first surface side being concave and a second surface side on the other side being convex, from among a first and a second surface corresponding to a front and a rear surface of each blade; and multiple second concavo-convex portions, with the second surface side being concave and the first surface side being convex, contrary to the first concavo-convex portions.

Abstract: A compressor assembly for a gas turbine engine comprising an outer case, a shroud arranged circumferentially around the axis to direct compressed air through an impeller, and an actuator coupled with the outer case and the shroud to vary the position of the shroud axially relative to the outer case. The actuator includes a mount arm, an actuator body, and a travel stop. The mount arm is coupled with the outer case. The actuator body is coupled with the mount arm and the shroud to control axial movement of the shroud relative to the outer case. The travel stop is coupled to the mount arm and extends away from the mound arm and is configured to limit a forward most axial position of the shroud relative to the outer case.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: An HVAC blower assembly includes a scroll housing, which includes an annular scroll channel provided by an outer ring wall and an inner ring wall extending from a scroll housing wall. A blower wheel is disposed within the scroll housing. The blower wheel includes an inlet end and an opposite end axially spaced from an inlet end with respect to an axis of rotation of the blower wheel. The blower wheel includes a plurality of circumferentially spaced blades, and a channel at the inlet end having a radially inner annular wall and a radially outer annular wall. A plurality of circumferentially spaced ribs are within the channel. The radially outer annular wall is radially between the outer ring wall and the inner ring wall, and the inner ring wall is radially between the radially inner annular wall and the radially outer annular wall.

Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: The method is for operating a wind turbine having a wind turbine component and a setting system for executing at least two different measures for reducing the likelihood of overloading the component. First trigger information is provided, which is representative of whether the likelihood of overloading the wind turbine component exceeds a first threshold. If this is the case, a first output signal is generated which is configured to cause the setting system to execute a first measure for reducing the likelihood of overloading the wind turbine component. Second trigger information is provided which is representative of whether the likelihood of overloading the wind turbine component exceeds a second threshold after the first measure was executed. If so, a second output signal is generated which is configured to cause the setting system to execute a second measure for reducing the likelihood of overloading the wind turbine component.

Abstract: To provide an axial fan motor increasing the mounting area of a circuit board and further improving heat dissipation as compared with the axial fan motor in the related art. A fan device as an axial fan motor includes: a casing having a hollow tubular shape and provided with an intake opening at one end in an axial direction and an exhaust opening at another end in the axial direction; an impeller including a plurality of blades and accommodated in the casing; a motor accommodated in the casing and configured to rotate the impeller; and a plurality of circuit boards arranged along the axial direction at a side close to exhaust opening in the casing.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: Methods, systems and apparatuses including systems and methods that can be used for operating a water turbine such as along one or more flow channels of a tidal estuary for power generation is disclosed. The water turbine can be positioned within the one or more flow channels and can be turned by the flow of the water from the estuary.

Abstract: A composite airfoil with an airfoil core and a wall surrounding the airfoil core. The wall including a first set of stacked plies including a first type of ply having directional fibers extending in a first direction, and defining at least a portion of an exterior surface, the exterior surface extending between a leading edge and a trailing edge to define a chordwise direction and between a root and a tip to define a spanwise direction. At least one stiffener located between the airfoil core and the wall, the at least one stiffener having a second set of stacked plies.

Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion. The leading edge protector includes at least one projection extended past a base of the airfoil to a root of the airfoil.

Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.