Abstract: A blade root including of a plurality of lobes and fillets and flanks in between is provided. A shoulder is provided between the flanks and the fillets to increase the distance to a corresponding lobe of a corresponding rotor disc into which a blade with such a blade root is inserted. A rotor blade having such a blade root is also provided. Furthermore this feature may alternatively or additionally also be applied to a rotor disc slot of a rotor disc, such that a flank of the rotor disc slot merges into a fillet of the rotor disc slot via a soft shoulder to increase the distance to a corresponding lobe of a blade root. A shoulder could also be applied to both the blade root and the corresponding slot of the rotor disc.

Abstract: A linear motion mechanism (27) is provided with: a cylinder rod (312) into which a ball screw (30) can be inserted, said cylinder rod (312) including a base end section that is connected to a nut (311) within a piston casing (36) and a tip section (312a) that is exposed on the outside of the piston casing (36); a nut-side grease supply hole (321) that is formed in the nut (311) and that includes a discharge port (323) that opens toward the outer circumferential surface of the ball screw (30); and a cylinder rod-side grease supply hole (322) that is formed in the cylinder rod (312), that includes on one end thereof an inlet (324) that opens at a position that is exposed to the outer section of the piston casing (36), and that includes another end (322b) that is connected to the nut-side grease supply hole (321).

Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading edge and a trailing edge and a flow channel that extends between the pressure side surface and the suction side surface.

Abstract: A wind turbine blade with a flow guiding device attached to a profiled contour on a pressure side of the blade is described. The flow guiding device has a front surface facing toward an oncoming airflow and comprises at least a first portion, which is angled towards the oncoming airflow and a leading edge of the wind turbine blade.

Abstract: A detachable blade structure has a blade seat, a motor, a cover plate, a spherical cover, a blade, a detachable member and first and second screws. The spherical cover has a cover slot, a cover positioning hole and a cover screw hole. The cover plate has a chamber. The blade is inserted through the cover slot and inserted into the chamber. The blade seat has a first seat lug, a first seat screw hole, a second seat lug and a second seat screw hole. The motor has a motor positioning hole and a motor screw hole. The first seat lug is inserted into the motor positioning hole. The first screw is screwed into the first seat screw hole and the motor screw hole. The second seat lug is inserted into the cover positioning hole. The second screw is screwed into the second seat screw hole and the cover screw hole.

Abstract: A rotor shaft for a high speed motor that has a coating that is secured to a shaft body. The coating and the shaft body are formed from dissimilar materials. More specifically, the coating may be an alloy material, such as, for example, a copper alloy, while the shaft body may be a steel material. According to certain embodiments, the alloy material of the coating may be secured to at least a portion of a rotor body blank in a solution treated condition via a low temperature welding procedure. Additionally, the coating may be hardened, such as for example, through the use of an age hardening process. The coating and the rotor body blank may be machined together to form the rotor shaft. According to certain embodiments, such machining may configure the rotor shaft for use with a turbo-compressor that is configured for air compression.

Abstract: A disc for a fan rotor (with a pilot to connect to a rotating shaft, a hub and a plurality of blades) includes a flat circular portion connecting to the pilot at an inner edge and to the hub at an outer edge; a plurality of first circular cooling holes of a first diameter located around the inner edge of the disc; and a plurality of second circular cooling holes of a second diameter located around the outer edge of the disc, wherein the second diameter is larger than the first diameter.

Abstract: A suction diffuser or arrangement is provided featuring a main suction diffuser body and a flow conditioning arrangement. The main suction diffuser body is configured with an inlet to receive an incoming fluid flow, an interior cavity to receive the incoming fluid from the inlet, and an outlet to receive the incoming fluid from the interior cavity and provide an outgoing fluid. The flow conditioning arrangement is configured in relation to the inlet and also comprises a flow conditioning portion having at least one inwardly contoured surface, configured to extend into the interior cavity, diffuse the incoming fluid passing from the inlet into the interior cavity, and provide a flow conditioning that produces a uniform flow of the outgoing fluid by directing the incoming fluid towards the outlet, based at least partly on a contoured design corresponding to the at least one inwardly contoured surface.

Abstract: A seal for sealing a gap between a vane and a liner of an outlet guide vane is provided. The seal includes: a joint section for joining with the liner; a flexible fillet section elongated from the joint section and tapering toward a tip so as to form a round corner between the vane and the liner when the tip is placed in contact with the vane; and a flexible rib section projecting from an inner surface and so dimensioned as to get in contact with an upper surface of an external structure for securing the vane to keep gas tightness.

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured to conduct a medium in its interior. In order to conduct the medium in the interior with low flow losses, it is provided that a rotor disk of the compressor has holes, in order to feed the medium from outside into the rotor interior. For improved temperature control of the rotor disk, the holes conduct the medium through the rotor disk counter to the flow direction in the compressor.

Abstract: Multiple propeller blades may be joined by tip connectors to form a closed propeller apparatus. The tip connectors may create continuous structure between adjacent tips of a first propeller and a second propeller. Use of the tip connectors may reduce vortices created near the tips of the propeller blades, which cause drag and slow the rotation of the propeller blades. The tip connectors may also reduce noise caused by rotation of propeller blades. Further, the tip connectors reduce or eliminate deflection of the propeller blades by creating a support structure to counteract forces that would otherwise cause deflection of the propeller blades, thereby improving propeller blade loading. In some embodiments, the tip connectors may be formed of a malleable material and/or include one or more joints that enable at least one of the propellers to modify a pitch of blades of the propeller.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. A fan shaft support supports the fan shaft and defines a support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.

Abstract: Disclosed is a speed reduction apparatus including: a casing that accommodates a speed reduction mechanism; an input shaft including a protruding portion protruding from the casing to the outside; a fan provided on the protruding portion of the input shaft; and a fan hood that covers the fan. The fan hood includes a cylindrical portion, and a trumpet-like portion that is connected to the cylindrical portion, and includes an inner surface inclined to be separated away from the input shaft toward a load side. A flow straightening fin is provided on an inner surface of the trumpet-like portion.

Abstract: The use of different ceramic layers allows different configurations of gas turbines to be produced each of which is optimized for a respective use of base load operation or peak load operation.

Abstract: Apparatuses are disclosed including a first article, a second article, a sewing member and a thermal break. The second article includes a second material composition having a second thermal tolerance greater than a first thermal tolerance of a first material composition of the first article. The sealing member is disposed between and contacts the first article and the second article, and includes a third material composition having a third thermal tolerance less than the second thermal tolerance and less than an operating temperature of the second article. The thermal break is defined by the second article, and is proximate to the sealing member and partitioned from the sealing member by a portion of the second article. The thermal break interrupts a thermal conduction path from the second article to the sealing member. The first article and the second article compress the sealing member, forming a thermal gradient-tolerant seal.

Abstract: A discharge conduit suitable for use with a turbine engine. The discharge conduit includes an air intake end, an air outlet end and a tubular duct for guiding air between the air intake and air outlet ends. The air intake end is equipped with attachment elements for attachment to an intermediate casing of the turbine engine. The attachment element can be of the resilient snap-in type.

Abstract: A gas turbine engine includes a geared architecture with a multiple of intermediate gears, and a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears. A geared architecture and method are also disclosed.

Abstract: A fan with a nozzle mounted to a base plate, wherein the base plate has on its rear wall a mounting device with an upper and lower holding device for mounting the fan on a top-hat rail. The upper holding device and the lower holding device reach over an upper edge or a lower edge respectively of the top-hat rail in the mounted state and are arranged offset from one another in a direction running parallel to the longitudinal axis of the top-hat rail in the mounted state of the fan.

Abstract: A turbine engine assembly includes a first component, a second component and a third component arranged along an axis. The first component houses at least a portion of the third component. The assembly also includes a seal carrier, a seal land and a seal element, which seals a gap between the seal carrier and the seal land. The seal carrier is connected to the first component, and includes a groove surface and a groove. A first portion of the seal carrier seals a gap between a second portion of the seal carrier and the second component. The seal land is connected to the third component and includes a seal land surface. The seal element extends radially into the groove. The seal element is axially engaged with the groove surface and radially engaged with the seal land surface.

Abstract: The present disclosure is directed to a rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade having a blade root section and a rigid ring insert. The rotor blade has pressure and suction sides extending between leading and trailing edges. The blade root section includes an end face configured to attach the rotor blade assembly to a hub. Further, the blade root section includes a span-wise end portion defined by inner and outer circumferential components separated by a radial gap. The radial gap includes a first laminate material embedded between the inner and outer circumferential components at a first span-wise depth and a second laminate material embedded between the inner and outer circumferential components at a second span-wise depth. Thus, the rigid ring insert is disposed in the radial gap and embedded between the first and second laminate materials.