Abstract: A liquid-cooling pump and a flow channel structure thereof are disclosed. The flow channel structure includes a liquid pump mounting chamber. A bottom of the liquid pump mounting chamber is centrally formed with a liquid inlet. A peripheral side of the liquid pump mounting chamber is formed with a liquid outlet. An inner wall of the peripheral side of the liquid pump mounting chamber is convexly provided with a protruding boss corresponding to one side of the liquid outlet and surrounding an impeller, and is concavely provided with a guide groove corresponding to another side of the liquid outlet and surrounding the impeller. The protruding boss is gradually thinned along a rotating direction of the impeller. The guide groove is gradually deepened along the rotating direction of the impeller and communicates with the liquid outlet.

Abstract: A ceiling fan including a retention system and method of redundantly retaining a ceiling fan can include a ceiling fan motor assembly including a hollow motor shaft at least partially surrounded by a motor housing. A retainer plate is provided at the bottom of the motor housing including an opening. A retainer rod extends through the opening in the retainer plate and secures to the retainer plate. A support cable couples to the retainer rod to suspend the retainer plate from a structure, wherein the retainer plate is configured to redundantly retainer the ceiling fan.

Abstract: A turbine stator blade made of ceramic matrix composite material includes a hollow blade profile and has a trailing edge and a leading edge, the blade including a first portion including an extrados face and a second portion distinct from the first portion including an intrados face, the first and second portions being connected to one another by a connection interface present at least on the trailing edge or leading edge, the connecting interface including a region of overlap between the first and second portions present on at least one longitudinal end of the blade profile and intended to be present outside a flow path of a gas stream of the turbine, the blade also including a platform present at a longitudinal end of the blade profile and that includes a first portion integral with the extrados face and a second part integral with the intrados face.

Abstract: An exhaust gas turbocharger having a hydrodynamic plain bearing or a hydrodynamic plain bearing, comprising a rotor (10) and a counter-bearing part (50) assigned to the rotor (10), wherein a rotor bearing surface (17.1, 17.2, 17.3) of the rotor (10) and a counter-surface of the counter-bearing part (50) face each other to form a hydrodynamic plain bearing, wherein the rotor bearing surface and/or the counterface, when cut along and through the axis of rotation (R) in sectional view, form(s) a continuous bearing contour forming at least two contour sections (44.1 to 44.3; 53.1 to 53.3) to provide hydrodynamic load capacities in both radial and axial directions, and wherein the counter-bearing part (50) is mounted in a bearing housing (60) or housing part.

Abstract: A blade outer air seal assembly includes a support structure and a blade outer air seal having a plurality of segments extending circumferentially about an axis and mounted to the support structure. At least two segments have a base portion extending from a first circumferential side to a second circumferential side, a first protrusion extending from the first circumferential side and having a first slot, and a second protrusion extending from the second circumferential side and having a second slot. A feather seal is arranged in the first slot and the second slot between the at least two segments such that the feather seal is pivotable between first and second positions in response to relative movement between the first and second protrusions.

Abstract: A compressor wheel for a turbocharger includes a body having a top and a bottom, the body formed from a material comprising titanium, a central hub extending from the top to the bottom of the body of the compressor wheel, a central axis extending longitudinally through a center of the central hub of the compressor wheel, a central opening extending through the central hub of the compressor wheel, and a first set of vanes mounted to the body relative to the central axis such that each of the first set of vanes is off-axis relative to the central axis. Each of the first set of vanes having a top portion proximate a top of the central hub and extending downwardly along a curved path to a bottom portion proximate a bottom of the body. The compressor wheel further includes a second set of vanes mounted to the body having a top portion proximate a midpoint of the body and extending downwardly along a curved path to a bottom portion proximate the bottom of the body.

Abstract: A gear unit having a shaft, particularly an input shaft, a fan impeller being joined in rotatably fixed manner to the shaft, a fan cowl, which at least partially surrounds the fan impeller, being mounted on the gear housing, a separating plate for separating the pressure chamber of the fan from the suction chamber of the fan being joined to the fan cowl, the separating plate having an air inlet for the fan impeller and being disposed on the side of the fan impeller facing away axially from the gear unit.

Abstract: A blower housing comprises first and second blower housing pieces for surrounding a blower fan. The first blower housing piece comprises a blower discharge section comprising an inner tubular portion, an outer tubular portion, and a drain hole. The inner tubular portion defines a blower discharge passage. The inner and outer tubular portions define an exhaust pipe cavity adapted to receive an end margin of an exhaust pipe. The tubular portions are adapted to enable condensate water that forms on the inner surface of the exhaust pipe to flow into the exhaust pipe cavity. The drain hole extends through the outer tubular portion. The drain hole is configured to enable condensate water flowing into the exhaust pipe cavity to drain from the blower housing. The first blower housing piece is a molded one-piece member.

Abstract: The invention relates to a fan blade (1) comprising: —an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and —a structural shield (10) fitted and attached to the leading edge (4) or the training edge (5), and —at least one stiffener (20) formed integrally and in one piece with the structural shield (10), said stiffener (20) extending in a cavity (15) formed between the shield (10) and the leading edge (4) or the trailing edge (5) so as to increase a stiffness of the blade (1).

Abstract: A ceiling fan mount assembly having a downrod assembly with a downrod and a motor assembly comprising motor and including a motor shaft. The ceiling fan mount assembly further includes a downrod plate coupled to the downrod and a shaft coupler coupled to the motor shaft and coupled to the downrod plate, whereby coupling the downrod plate to the shaft coupler suspends the motor from the downrod.

Abstract: The present disclosure relates to an impeller and a method of manufacturing the same. The impeller includes: a hub in which a plurality of spiral first slots are formed; a shroud which is positioned opposite the hub, and has a plurality of spiral second slots formed therein; and a plurality of blades which is coupled to the hub and the shroud, and have an upper protrusion formed on one side and a lower protrusion formed on the other side; and wherein the upper protrusion is inserted into and coupled to a second hole formed in the second slot, and the lower protrusion is inserted into and coupled to a first hole formed in the first slot.

Abstract: The invention relates to acoustic management, on an aircraft turbomachine (3,12) or on a nacelle (1,10), via a panel (30,32). On a support (38) is reserved a recess (34), recessed with respect to a surrounding general surface (36) for contact with moving air. The recess (34) is adapted to receive the panel, as another so-called surface for contact with moving air. The support (38) and/or the panel comprise removable connecting elements for, in the recess (34), mounting it removably with respect to the support, the panel being an acoustic panel or a non-acoustic panel.

Abstract: Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: an airfoil having an airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.

Abstract: A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.

Abstract: The invention relates to a profiled structure elongated in a direction in which the structure has a length exposed to an airflow and transversely to which the structure has a leading edge and/or a trailing edge, at least one of which is profiled and has, along said direction of elongation, geometric serration patterns defined by a succession of peaks and troughs. Along the profiled leading edge and/or trailing edge, the serration patterns have a geometric pattern that is repeated in the direction of elongation, the shape of which is stretched and/or contracted transversely to the direction of elongation and/or in the direction of elongation.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

Abstract: A journal support pin to support intermediate gears for use in gas turbine engine comprises a titanium body, and an outer surface outside of the titanium body having a surface hardness that is harder than the body. A gas turbine engine and a method of forming a journal support pin to support intermediate gears for use in gas turbine engine are also disclosed.

Abstract: A method is provided for monitoring a pitch control system for a rotor blade of a wind turbine. The method comprises a step of receiving a blade pitch signal representative of a pitch position of the rotor blade, a step of determining a pitch deviation, based on the blade pitch signal and a blade pitch reference. If the determined pitch deviation exceeds a first pitch deviation threshold, a pitch deviation variable is increased by an amount that depends on the determined pitch deviation, the first pitch deviation threshold, and a duration of a time period during which the determined pitch deviation has been exceeding the first pitch deviation threshold. An error signal is provided when the increased pitch deviation variable exceeds a pitch deviation variable threshold.

Abstract: A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.

Abstract: Provided is a method of controlling a pitch angle of at least one blade of a wind turbine by use of a hydraulic system, the hydraulic system including at least one reservoir configured to store a hydraulic fluid, and at least one pump configured to supply the hydraulic fluid from the reservoir to at least one accumulator, if a hydraulic fluid pressure in the accumulator falls below a lower threshold value and till the hydraulic fluid pressure in the accumulator exceeds an upper threshold value. The accumulator is configured to store the pressurized hydraulic fluid supplied by the pump and to supply the pressurized hydraulic fluid to at least one pitch control cylinder of the hydraulic system via at least one output valve of the hydraulic system. The pressurized hydraulic fluid in the pitch control cylinder drives at least one piston to change the pitch angle of the blade.