Abstract: A rotor actuation system includes a swashplate assembly comprised of a stationary swashplate and a rotating swashplate operatively connected together for relative rotation about a rotor axis. A cyclic actuator is operatively connected to the stationary swashplate to tilt the swashplate assembly off axis from the rotor axis for cyclic control. A collective actuator is operatively connected to the swashplate assembly to move the swashplate axially along the rotor axis for collective control. The cyclic actuator and the collective actuator are operatively connected to the swashplate assembly to respectively actuate cyclic and collective control independent of one another.

Abstract: A hot air feed wheel, for a vehicle heater, includes a hub (44) to fix the hot air feed wheel (22) to a drive shaft and a feed area (50), adjacent to the hub (44), in a transition area (48). A plurality of feed blades (36) are arranged following one another about a feed wheel longitudinal axis (L) in the circumferential direction. The transition area (48) includes a plurality of connection webs (66) following one another about the feed wheel longitudinal axis (L) in the circumferential direction.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.46-0.59 inch (11.8-14.9 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.73-0.86 inch (18.6-21.9 mm). The airfoil element includes at least two of a first mode with a frequency of 5133±15% Hz, a second mode with a frequency of 8542±15% Hz, a third mode with a frequency of 15487±15% Hz, a fourth mode with a frequency of 18774±15% Hz, a fifth mode with a frequency of 24295±15% Hz and a sixth mode with a frequency of 27084±15% Hz.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 27.5-28.5 inches (699-724 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 34±10% Hz, a second mode with a frequency of 90±10% Hz, a third mode with a frequency of 178±10% Hz, a fourth mode with a frequency of 222±10% Hz, a fifth mode with a frequency of 307±10% Hz and a sixth mode with a frequency of 389±10% Hz.

Abstract: A particle separator adapted for use with a gas turbine engine includes an inner wall, an outer wall, and a splitter. The splitter cooperates with the inner wall and the outer wall to separate particles suspended in an inlet flow moving through the particle separator to provide a clean flow of air to the gas turbine engine.

Abstract: The invention relates to a wear-resistant shield for a rotating blade root of a rotating blade of a gas turbine, especially an aircraft gas turbine, having a base and two side walls connected to the base, wherein the side walls lie opposite each other and are shaped so as to be substantially complementary to an outer contour of a particular rotating blade root, and wherein the wear-resistant shield for this purpose is set up in such a way that, in an installed state, it is to be taken up between the respective rotating blade root and a rotating blade root mount of a rotor, especially between the respective rotating blade root and an axial securing element arranged in the rotating blade root mount.

Abstract: A centrifugal compressor includes a housing, a partition separating an empty space in a housing into a speed increaser chamber and an impeller chamber, an insertion hole provided in the partition to allow insertion of a high-speed shaft, a seal located in the insertion hole to seal a boundary between the partition and the high-speed shaft, and a bearing receptacle located in the partition. The partition includes a communication passage that allows communication between a portion of the insertion hole located closer to the speed increaser chamber than the seal and the bearing receptacle.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge and a trailing edge and defines a chord extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and includes a leading edge wall and a trailing edge wall and defines a tip shroud cavity. The tip shroud cavity includes a leading edge portion at least partially defined by the leading edge wall and positioned largely upstream of fifty percent of the chord. The tip shroud cavity also includes a trailing edge portion at least partially defined by the trailing edge wall and positioned largely downstream of fifty percent of the chord. An intermediate portion of the tip shroud cavity fluidly couples the leading edge portion of the tip shroud cavity and the trailing edge portion of the tip shroud cavity.

Abstract: An assembly of a first element with a second element includes an elongate thin lip belonging to the second element being inserted in an elongate narrow slot formed by three sides of an elongate flat plate fixed in parallel to a flat wall of the first element. At least one element forming a guide is secured to a long side of the elongate flat plate forming an edge of the slot. The element forming a guide includes a sliding surface extending in the continuation of the elongate flat plate and diverging from the flat wall away from the first element. The at least one element forming a guide cooperates with the lip so that the insertion of the lip into the slot begins with the sliding of the lip on the sliding surface and then continues as the lip advances, with progressive insertion of the lip into the slot.

Abstract: A thrust producing unit for producing thrust in a predetermined direction, comprising a shrouding and at least two rotor assemblies, wherein the shrouding defines an internal volume, and wherein a first rotor assembly of the at least two rotor assemblies defines a first rotor axis and a second rotor assembly of the at least two rotor assemblies defines a second rotor axis, the first and second rotor axes being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles with respect to the predetermined direction, the associated inclination angles being comprised in a range between ?60° and +60°, and preferably amounting to 0°, and wherein the first rotor assembly is arranged outside of the internal volume of the shrouding.

Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.

Abstract: The invention is directed to a method for making an equipotential bonding connection between two components of a lightning protection arrangement of a wind turbine rotor blade. The method includes providing a wind turbine rotor blade having two rotor blade half shells having respective connection and fastening units connected to corresponding ones of the two components of the lightning protection arrangement. A space is present in the interior of the rotor blade between the two connection and fastening units. A connection conductor is introduced from outside of the rotor blade through a through opening in one of the two connection and fastening units into the interior space of the wind turbine rotor blade. The two ends of the connection conductor are fastened to corresponding ones of the connection and fastening units such that the connection conductor bridges the interior space along an essentially linear imaginary line.

Abstract: A casing for a subsea compressor comprises a main body having a central axis; a plurality of interconnection flanges attached to the main body; wherein the main body comprises an inner layer made of corrosion resistant material; an outer layer applied over the inner layer and made of a composite material; wherein the outer layer extends along the entire length of said main body.

Abstract: A box frame hub arm structure is provided and includes a body having an outboard surface, which is disposable to abut with an inboard surface of an outboard arm of an aircraft rotor head, and lead/lag sides. The body is formed to define a first cavity, an aperture communicative with the first cavity through the outboard surface and second and third cavities. The second and third cavities extend outwardly in opposite lead/lag directions from the first cavity to the lead/lag sides.

Abstract: A blade of a cross-flow fan including leading and trailing edge portions arranged on inner and outer peripheral sides of the cross-flow, and a base portion formed between the edge portions. The edge portions are arc shaped. The base portion has a pressure surface and a suction surface. A radius of the leading-edge portion is greater than a radius of the trailing-edge portion. A maximum thickness is at a position of maximum thickness that is closer to the leading-edge portion than to the trailing-edge portion. A first thickness is at midpoint of a blade chord. A second thickness is at a position set apart from an outer-peripheral end of the blade chord by 5% of the chord length. A value obtained by dividing the first thickness by the maximum thickness that is greater than a value obtained by dividing the second thickness by the first thickness.

Abstract: A folding and unfolding structure of blade of a ceiling fan includes a driving device, a rotary member, multiple connection arms, multiple fixed arms, multiple extension arms, multiple elastic members and multiple blades. The rotary member rotates synchronously with the driving device. One end of the connection arm is connected to the rotary member, and the other end of the connection arm is pivotably connected to one end of an extension arm by a first pivot. One end of the fixed arm is connected to a blade, and the other end of the fixed arm is pivotably connected to the other end of an extension arm by a second pivot. The elastic members are provided between the extension arms and the connection arms to restricting outward expansion of the extension arms, such that the extension arms are pivoted upward about the first pivots and move close to the rotary member.

Abstract: A gas turbine includes: a first cavity inside a stationary body and supplied with cooling air; a second cavity between the stationary body and a rotating body; a first cooling passage between the first and second cavities and having a swirl flow guide nozzle therein by which the cooling air of the first cavity is supplied to the second cavity while being swirled along a rotation direction of the rotating body; a second cooling passage in the rotating body, in communication with the second cavity, and supplied with the cooling air of the second cavity; and a flow regulating passage, different from the first cooling passage, between the first cavity and the second cavity and through which the cooling air is supplied from the first cavity to the second cavity, wherein the flow regulating passage has a flow regulator for regulating a flow rate of the cooling air.

Abstract: A composite spar having an upper and lower wall region connected by leading and trailing edge regions is provided including a plurality of first laminates and a plurality of second laminates. The plurality of first laminates includes one or more intermediate modulus graphite plies having an intermediate modulus. The plurality of first laminates is arranged in one or more intermediate modulus layers to form at least a portion of the upper wall region, lower wall region, leading edge region and trailing edge region. The plurality of second laminates includes one or more high modulus graphite plies having a high modulus. The plurality of second laminates is arranged in one or more high modulus layers. The high modulus layers are generally interposed between intermediate modulus layers.

Abstract: A gas turbine casing with an internal heat exchange system. The gas turbine extends between an inlet section and an exhaust section and defines a downstream direction from the inlet section to the exhaust section. The casing includes a forward end, an aft end downstream of the forward end, a first exterior surface facing radially outward, a second exterior surface facing radially inward, and an internal body at least partially defined between the first exterior surface and the second exterior surface. The heat exchange system includes an inlet and an outlet formed in an exterior surface of the casing proximate the aft end, a supply bore extending upstream from the inlet through the interior body of the casing, and a return bore extending downstream to the outlet through the interior body of the casing.

Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge, the leading edge and the trailing edge define a chord distance. The airfoil includes a tip portion extending between the pressure sidewall and the suction sidewall. The tip portion includes a planar section and a recessed section. The recessed section extends adjacent to the planar section such that a thickness of the planar section is less than a thickness of the airfoil. The recessed section is offset a predetermined distance from the leading edge and the trailing edge along the chord distance.