Abstract: An assembly for mounting an auxiliary component to an engine case for a gas turbine engine includes a support bracket and a locator comprising a guide pin extending at least partially into a first aperture disposed in the support bracket, and a catcher pin extending at least partially into a second aperture disposed in the support bracket. A first frangible ring member is disposed between the support bracket and the catcher pin, wherein the frangible ring member comprises a porous metal material (e.g., frothed aluminum or thin-walled honey combed aluminum or steel). The first frangible ring member is configured to collapse to absorb energy while limiting system displacement during and post an overload event, thus reducing the energy transmitted to the auxiliary component (e.g., a gearbox housing). The guide pin can be fused such that the catcher pin limits movement of the auxiliary component when the guide pin breaks.

Abstract: A multistage pump for installation on a sea ground includes a common housing, a pump unit arranged in the common housing, a drive unit arranged in the common housing, and a coupling. The common housing includes a pump inlet and a pump outlet, the pump unit including a plurality of impellers to convey a compressible fluid from the pump inlet to the pump outlet, and a pump shaft, on which each impeller is mounted, each impeller being a radial or semi-axial impeller. The drive unit includes a drive shaft to drive the pump shaft, and an electric motor configured to rotate the drive shaft about an axial direction. The coupling couples the drive shaft to the pump shaft. The pump unit conveys the fluid in a dense phase at the pump outlet, and at least two impellers of the plurality of impellers have a different specific speed.

Abstract: The present invention relates to a fan shroud provided in a cooling module, and an object of the present invention is to provide a fan shroud having a peripheral part configured to surround an outer periphery of a fan, and a planar part coupled to face a heat exchanger, in which a noise-reducing hole is formed at an appropriate position and defined by connecting a first hole, which extends in a circumferential direction of the peripheral part, and a second hole, which extends toward the planar part and is formed through the planar part, thereby effectively reducing BPF noise while minimizing deterioration in rigidity and durability of the fan shroud.

Abstract: A sub-assembly for a low-pressure compressor of an aircraft turbine engine includes a straightener provided with cantilevered vanes and a rotor hub having a cavity covered by an inner shroud opposite the vanes. Orifices are made in the inner shroud to allow an air flow to circulate in the downstream to upstream direction of the low-pressure compressor.

Abstract: Flow control devices and structures for turbomachines. In some examples, the flow control devices and structures include various arrangements of flow guiding channels, partial height vanes, and other treatments located on one or both of a shroud and hub side of a turbomachine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.

Abstract: A blower includes a first tower and a second tower spaced apart from each other each having discharge ports that face each other. A gate is movably installed in at least one of the first tower or the second tower to protrude into and out of the space between the first and second towers to change a flow of air discharged out of the discharge ports. A guide motor may be configured to move the gate. The discharge ports may be provided at a rear side of the space to discharge air toward a front of the space, while the gate may be moved to cover the front side of the space to guide air upward.

Abstract: A variable turbine geometry assembly includes an adjustment ring extending along and rotatable about an axis, at least one vane lever coupled to the adjustment ring, and at least one vane coupled to the at least one vane lever. The variable turbine geometry assembly also includes a biasing member coupled to the adjustment ring at a first circumferential location on the adjustment ring and coupled to the adjustment ring at a second circumferential location on the adjustment ring. The biasing member extends from the first circumferential location to the second circumferential location. The biasing member is operably in contact with the at least one vane lever between the first circumferential location and the second circumferential location to bias the at least one vane lever toward the adjustment ring and to reduce vibration between the adjustment ring and the at least one vane lever.

Abstract: A gear box includes a casing having an interior. A rotating component is arranged in the interior of the casing. A bearing including a rotating element, and a fixed element is connected with the casing in the interior. A submersible pump is arranged in the interior of the casing. The submersible pump includes a first housing portion extending about the rotating component fixedly mounted to the casing at the interior. A second housing portion is fixedly mounted to the casing at the interior and is aligned with the first housing portion. The first and second housing portions form a lubricant reservoir which holds lubricant. An impeller is mounted to the rotating component and arranged in the lubricant reservoir. One of the first and second housing portions includes an outlet through which the pumped lubricant is directed toward the rotating element.

Abstract: An axial turbine (100) with two supply levels for the expansion phase of a working fluid in a thermodynamic vapor cycle or in an organic Rankine cycle comprising a shaft (2), a plurality of rotor blade arrays (R1-Rn) and corresponding support disks (21, 22), a plurality of stator blade arrays (S1-Sn), further comprising a first inlet opening (5) and a second inlet opening (7?). The second volute (4) is positioned inside the first volute (3), the working fluid of the second supply level reaching upstream of a stator blade (S2,Sn) that is are immediately upstream of one of the rotor blade arrays that extends radially into both of the first and second supply levels.

Abstract: A torque converter comprising a cover arranged to receive torque, an impeller having an impeller shell non-rotatably connected to the cover, and a turbine in fluid communication with the impeller and including a turbine shell is provided. In embodiments, the torque converter includes a piston plate; and a seal plate disposed axially between the piston plate and the turbine, wherein the piston plate is sealed to the seal plate at an outer diameter thereof. A pilot flow plate is disposed axially between the cover and the seal plate, wherein the pilot flow plate is fixed to the cover on a first axial side and fixed to the seal plate on a second, opposite axial side.

Abstract: A turbine casing has a front casing segment around a turbine longitudinal axis with first and second front casing part-segments, and a rear casing segment, around the longitudinal axis with first and second rear casing part-segments. The rear casing segment is downstream of the front casing segment in the direction of flow and fastened to the front casing segment via a rear vertical flange of the rear casing segment and a front vertical flange of the front casing segment, forming a cross-shaped joint. A protrusion surrounding the longitudinal axis is formed on the front casing segment in a region of the front vertical flange and extends parallel to the longitudinal axis and protrudes from the front vertical flange in the flow direction. A circumferential seal device is on an outer side, facing away from the longitudinal axis, of the protrusion, and seals the protrusion against the rear casing segment.

Abstract: A centrifugal compressor includes an impeller rotatably disposed and having a plurality of first blades and a shroud cover disposed on a leading edge side of the first blades partially in a rotational axis direction of the impeller and connecting the first blades circumferentially adjacent to each other. The shroud cover is shaped such that a position of at least one of an upstream edge or a downstream edge of the shroud cover in the rotational axis direction changes along a circumferential direction of the shroud cover.

Abstract: A flap for a cage for holding electronic devices in a computing system is disclosed. The flap includes a main segment, a first vertical extension, a second vertical extension, a lateral ledge, and a tapered ledge. The first vertical extension and the second vertical extension extend from a first side of the main segment. The lateral ledge extends from a third side of the main segment. The tapered extensions extend from a second side of the main segment and include a flat section and an angled section. The flap has a deployed position and a stored position in the cage. The flap engages with at least two sides of the cage in the deployed or the stored position. The flap may be in the stored position when an electronic component is present. The flap blocks airflow through the cage in the deployed position.

Abstract: A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.

Abstract: A torque converter comprises a front cover, an impeller including an impeller shell fixed to the front cover, and a turbine including a turbine shell axially movable to frictionally engage the impeller shell such that the turbine shell forms a piston of a lock-up clutch. A reaction plate is positioned axially between the front cover and the turbine shell. A first pressure chamber is defined axially between the reaction plate and the turbine shell, a second pressure chamber is defined axially between the turbine shell and the impeller shell, and a third pressure chamber is defined axially between the reaction plate and the front cover. An output hub includes a first bore and a second bore radially offset from each other, wherein the first bore is in fluid communication with the first pressure chamber and the second bore is in fluid communication with the third pressure chamber.

Abstract: An object is to provide a motor drive device in which the maintenance accessibility of a fan motor is excellent. A motor drive device includes a second turning engagement unit which is engaged with a first turning engagement unit, which is engaged with the first turning engagement unit and is disengaged therefrom by movement of a first fan unit in a direction intersecting a horizontal direction and in which in an engaged state, where the second turning engagement unit is engaged with the first turning engagement unit, the second turning engagement unit pivotally supports the turning movement of the first fan unit, and in the engaged state, the first fan unit is engaged with a housing such that the first fan unit can be moved to be turned about a predetermined turning axis both to a non-fitting position in which a first connector is not fitted to a second connector and to a fitting position in which the first connector is fitted to the second connector.

Abstract: An impeller includes a hub and blades. In radial direction, an upper surface of the blade near the outer edge includes a groove structure, a lower surface of the blade relating to the groove structure includes a peak structure, the lower surface of the blade includes a recess structure aside the trailing edge or the leading edge. The recess structure is connected to the peak structure. The blade has at least five airfoils from the inner edge to the outer edge. The blade is defined by continuously connecting the at least five airfoils at different sections in sequence so as to form the groove structure and the peak structure respectively on the upper surface and the lower surface. The groove structure and the peak structure are aside the outer edge of the blade.

Abstract: A suction-and-discharge flow path includes a circumferential flow path that extends in an arc shape about an axis and an external communication path that is connected to both ends of the circumferential flow path. The circumferential flow path has a uniform flow path cross-sectional area in a circumferential direction, and a convex curved surface having a convex curved surface shape is provided between an outer peripheral wall surface of the circumferential flow path and a second inner wall surface of the external communication path. In a case where, when viewed in the axis direction, a curvature radius of the convex curved surface is defined as R and a radial dimension of the circumferential flow path is defined as W, a relationship of W?R?3W is established.

Abstract: A volute assembly including a volute and a cover plate. The volute includes a cavity. The cover plate is disposed on the volute and covers the cavity. The cover plate includes an air inlet; the volute includes an exhaust duct. The exhaust duct includes an air outlet. The exhaust duct includes a first part, a second part, and a third part sequentially connected in that order. The first part is directly connected to the volute. The air outlet is disposed on the third part. The inner diameter of the second part increases in the direction from the first part to the third part.

Abstract: An impeller includes a central, shaft or a tube for mounting on a shaft, a hollow hub is located around the shaft or tube, and a series of blades are attached to the outside of the hub by their bases. A reinforcing rib is provided for each blade, and extends on the shaft or tube in a radial direction and forms a facial connection between the shaft or tube and the inside of the hub at a position opposite the attachment of the base of a blade concerned.

Abstract: A vane for a gas turbine engine according to an example of the present disclosure includes, among other things, first and second endwalls each having a radially facing surface that bounds a gas path, an airfoil section extending in a radial direction between the first and second endwalls, extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and extending in a circumferential direction between pressure and suction sides. The radially facing surface of each of the first and second endwalls is axially sloped such that the gas path converges in the axial direction between the airfoil leading and trailing edges. The first endwall has an axisymmetric contour at least partially swept in the circumferential direction from each of the pressure and suction sides.

Abstract: The invention relates to a multistage pump (1), including a pump body (4), at a lower end of which a base element (2) is arranged, and at an upper end of which a head element (3) is arranged. At least the base element (2) is made from sheet steel and has an inlet port (5) and an outlet port (16). The inlet port (5) and the outlet port (16) are mechanically connected to each other by a pipe (6) running through the base element (2).

Abstract: A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.

Abstract: A housing (100) for a box fan (1), the box fan (1) and an assembly method therefor are provided. The box fan (1) includes a housing (100) and a fan blade. The housing (100) includes two shields (111, 112) and a frame. The two shields (111, 112) are arranged opposite to and spaced apart from each other. The frame is arranged between the two shields (111, 112). The frame and the two shields (111, 112) are joined and mounted through their own structures respectively, and at least one of the shields can be attached to or detached from the frame by pushing or pulling. The fan blade is rotatably installed in the housing (100). The box fan is easy to assemble and low in cost.

Abstract: A turbocharger includes a waste gate valve, a compressor, a turbine, a turbine housing which houses the turbine, a bypass channel which includes an opening cross-section, the bypass channel bypassing the turbine, a bypass channel portion formed in the turbine housing, an actuator housing which includes a separate first coolant channel having a coolant inlet port and a coolant outlet port, an electric motor arranged in the actuator housing, a transmission which includes an output shaft, the transmission being arranged in the actuator housing, and a control body coupled to the output shaft. The actuator housing is formed separately and is secured to the turbine housing. The control body controls the opening cross-section of the bypass channel.

Abstract: The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion chamber (13) of said turbomachine. The device is characterized in that it comprises: —at least two particle deflectors (3, 3a, 3b, 3c), —a member (5) for collecting and storing the particles deflected by said deflector, —and means (6) for attaching said trapping device (2) to a part of the turbomachine.

Abstract: The present disclosure relates to a blade structure and a fan and a generator having the same. In accordance with the present disclosure, there is the effect that can ultimately enhance efficiency of the generator by forming the sweep structure or the spline structure on the blade in the inflow direction side of fluid to reduce a low-speed region around the tip of the blade.

Abstract: A boundary layer ingestion engine comprising a fan, the fan comprising a disc and a plurality of blades integrally formed with the disc.

Abstract: A nacelle is provided comprising, a thrust reverser comprising a translating sleeve configured to translate between a stowed position and a deployed position, the translating sleeve comprising a slat cutout for clearance, and a slat door disposed at least partially in the slat cutout in response to the thrust reverser being in the stowed position, wherein the slat door is configured to move in response to the thrust reverser being in the deployed position to expose a portion of the slat cutout to accept a portion of a deployed forward wing slat.

Abstract: Systems and methods are provided for an aircraft propulsor with a fan cowl with one or more tangential restraints. The tangential restraints may be configured to contact one or more tangential receiving portions of a fixed portion of the aircraft propulsor. The fan cowl may receive a load that may include a bending load. The tangential restraints may be configured to convert the bending load to membrane tension and thus decrease deflection of the fan cowl.

Abstract: An automatic inflation device includes a valve body, a miniature motor and a centrifugal impeller. The valve body is provided with an air inlet and an inflation inlet, a check valve that is unidirectionally opened outwards the valve body is provided at the inflation inlet, a wind chamber and a wind guide path connected with the wind chamber are configured in the valve body, the miniature motor and the centrifugal impeller are installed in the wind chamber, the centrifugal impeller is actuated by the miniature motor, the wind chamber is communicated with the inflation inlet via the wind guide path, and the air inlet is communicated with a wind inlet of the wind chamber. The structure of the device is compact and reduced, which is applicable to directly install into inflation products. The device can inflate automatically and efficiently, and the structure is simplified and easy to actualize.

Abstract: The invention relates to an aircraft turbofan type engine (1) comprising an air intake duct (2) having an inner face provided with an acoustic attenuation shroud (11) located upstream from a fan (3) of this engine (1). This acoustic attenuation shroud (11) comprises a regular alternation of first portions and second portions with different first and second thicknesses along the radial direction, the number of alternations being greater than twice the number of passing azimuth acoustic vibration modes occurring in the engine (1) without the acoustic attenuation shroud (11) operating under conditions corresponding to a landing phase and a take-off phase.

Abstract: A centrifugal blower includes a rotation shaft, an impeller, a casing. The impeller includes a plurality of blades and a side panel. The casing accommodates the impeller and includes an air intake portion positioned adjacent to the side panel. The air intake portion includes a downstream end portion and an inner wall surface. The side panel includes an upstream end portion and an inner panel surface that is an inner surface of the side panel. The downstream end portion and the upstream end portion face each other across a space in an angular range. A difference between a smallest inner radius of the inner wall surface of the air intake portion and a smallest inner radius of the inner panel surface is smaller than or equal to a thickness of the side panel in the angular range.

Abstract: A gas turbine engine includes a compressor section, combustion section, and turbine section. The turbine section includes a turbine component stage, the turbine component stage including a plurality of turbine components together including a flowpath surface along a circumferential direction of the gas turbine engine. The flowpath surface defines in part a core air flowpath of the gas turbine engine and further defines a contour along the circumferential direction. The contour repeats less frequently than once per turbine component to accommodate a hot gas streak through the turbine section.

Abstract: A propeller formed along the lines of a vortex, i.e. a Fibonacci spiral projected onto a surface formed by a square hyperbola. Fluid flows evenly along the length of the propeller with less turbulence allowing it to operate at a higher pitch without stalling and resulting in reduced power requirements for a given flow rate. The underlying geometric shape of a vortex is an equiangular logarithmic spiral also known as golden spiral or Fibonacci spiral as is often found in natural objects ranging from sea shells to spiral galaxies. When viewed three dimensionally, the fluid flow in a vortex can be drawn as a projection of a golden spiral onto a surface of revolution of a square hyperbola where the vertex is equal to one and the focus is equal to the square root of 2.

Abstract: A pre-sintered preform (114) and a repair process (100) utilizing the pre-sintered preform (114) are disclosed, each of which result in a brazement (116) comprising a replacement protective coating (118) deposited on a component surface (110). The protective coating (118) exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component (102).

Abstract: A nozzle for use with a rotor blade for a reaction drive type helicopter includes a first wall, a second wall opposing the first wall, and sidewalls extending between the first wall and the second wall enclosing a cavity having an upstream end and a downstream end. The nozzle includes an inlet section for receiving a gasflow at the upstream end. The distance between the first wall and the second wall reduces to a throat downstream of the inlet section. An expansion section extending from the throat, downstream thereof.

Abstract: A turbine engine rotor blade including an airfoil defined by plane airfoil sections stacked in a radial direction, each airfoil section being positioned radially at a height H, where height H is expressed as a percentage of the total height of the airfoil, and being identified by its sweep angle ? and its dihedral angle ?, wherein the sweep angle ? varies as a function of height H in such a manner that the sweep angle ? reaches a maximum at a height H?M, the value H?M lying in the range 5% to 40%, and the sweep angle ? increases from 0% to H?M, and wherein the dihedral angle ? varies as a function of H, the dihedral angle ? being a decreasing function of height H for heights H lying in the range 0% to H?1, H?1 lying in the range 10% to 40%.

Abstract: A cooling system that includes two or more fans that each have a chassis. The chassis includes a first face, a second face, and a sidewall. The fans then can be attached to each other by attaching a sidewall of a first fan chassis to a sidewall of a second fan chassis. An adjustable vane is attached perpendicularly and approximately equidistant between the fans, with an angular control element that is attached to the first fan chassis. The vane can be oriented such that the vane divides the airflow distributed to the fans. The vane then can be adjusted radially by the angular control element, which is attached to the fan chassis. If an impeller of a fan chassis fails the vane can be adjusted radially using an angular control element to distribute more airflow to the failed fan superimposing the non-failed fan chassis.

Abstract: A ducted cowl support includes an annular structure configured to be mounted to an annular turbine engine frame and including one or more bypass ducts integrally formed therein.

Abstract: The present disclosure relates generally to a system for handling a gas turbine engine fan case. The system includes a composite fan containment case including a case outer surface, a case inner surface, and at least one main case aperture extending from the case outer surface through the case inner surface, and at least one shear puck, the at least one shear puck including a shear puck protrusion; wherein the shear puck protrusion of each of the at least one shear pucks is disposed within a respective one of each of the at least one main case apertures.

Abstract: The present invention provides a method of designing a manufacturing geometry for a tip portion of a rotary blade for a gas turbine engine. The method comprises first devising a theoretical hot running geometry of the tip portion at a specified design condition. Next, the theoretical operational forces acting on the theoretical hot running geometry at the specified design condition are calculated e.g. using CFD software. Then, the manufacturing geometry is determined (e.g. using FEA analysis) using the calculated theoretical operational forces.

Abstract: A liquid pump has a pump housing defining a pump chamber. A motor is accommodated within the pump housing and separated from the pump chamber by an end cap. An impeller disposed within the pump chamber is driven by the motor. The pump chamber has an inlet and one or more outlets. The outlets are located on a sidewall of the pump chamber and extend in a direction substantially tangential to an outer circumference of the pump chamber. Each outlet has a first end near the pump chamber, and a second end remote from the pump chamber. A cross-sectional area S1 of the first end is smaller than a cross-sectional area S2 of the second end, forming a diffuser within the outlet.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Abstract: A centrifugal fan includes: a casing having an upper casing with an air suction opening, a lower casing, and a plurality of support members disposed between the lower casing and the upper casing with air discharge openings provided between the support members; an impeller disposed between the upper and lower casings, and including an annular upper shroud provided on an upper casing side, a base plate integrally formed with the annular upper shroud, and a plurality of blades arranged along a circumferential direction between the annular upper shroud and the base plate; and a fan motor which rotates the impeller. A plurality of recesses are provided on the upper surface of the upper casing, and formed to surround the air suction opening, and a plurality of ribs are radially provided around the air suction opening and between the adjacent recesses.

Abstract: A turbine comprises a turbine housing defining a turbine inlet upstream of a turbine wheel and a turbine outlet downstream of the turbine wheel; a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state and a closed state. The valve member is mounted to an actuation member passing through an actuator conduit of the turbine housing, and movable so as to move the wastegate valve between the open and closed states. The turbine further comprises a sealing arrangement configured to provide a seal arranged to substantially prevent gas from passing from the turbine outlet into the actuator conduit. The sealing arrangement is configured such that when the valve member is urged into the closed state by the actuator member the sealing effectiveness of the sealing arrangement is increased.

Abstract: A circuit layout includes two or more high performance processing nodes that are cooled by a cooling fan. The cooling fan resides in a cooling fan assembly that relies on principles of aerodynamics to maximize airflow. The cooling fan assembly is coupled to the opposite side of a backplane to which the circuit layout is mounted. The backplane includes large ventilation holes to permit the cooling fan to induce significantly more airflow across the circuit layout than possible with conventional designs. At least one advantage of the approaches discussed herein is circuit layouts can be constructed to meet the competing objectives of high node performance and high node density. Accordingly, data centers can be built that offer high performance computing without requiring a significant increase in physical real estate.

Abstract: A system may include a reversible fan module that creates an airflow. The reversible fan module may include a set of attachment members, disposed on a face of the reversible fan module, that secure the reversible fan module a first orientation or a second orientation. The system may further include a chassis that include a divider that divides an interior region of the chassis into a front compartment and a rear compartment, a window, disposed on the divider, that allows airflow between the front compartment and the rear compartment, a first opening in the chassis that opens the front compartment to a first external region, a second opening in the chassis that opens the rear compartment to a second external region, and a bay that receives the reversible fan module.

Abstract: A method for manufacturing a turbomachine casing from composite material including: creating a semi-rigid protective layer from dry glass fibers that protects against galvanic corrosion, arranging the protective layer on a profiled mandrel by applying the protective layer against the annular radial flange thereof, forming and densifying the fibrous reinforcement on the mandrel while covering the protective layer.

Abstract: A multi-stage centrifugal pump assembly includes at least two impellers (2, 6) and two impeller groups (4, 8) which are consecutive in a flow direction and each with at least one impeller (2, 6). A backflow channel (24) connects an exit side of the first impeller group (4) to an entry side thereof is located in a first impeller group (4) of the two impeller groups (4, 8).