Abstract: A flow corrector (14) which includes a tubular body (40) with an entry end (42) and an exit end (44), and a plurality of parallel flow passages (54a, 54b, 54c, 54d) between the entry end and the exit end.

Abstract: Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan case liner having an outer surface, and a reclosable fastening system attaching the fan case liner to the fan case, the reclosable fastening system comprising two components, a first component being attached to the fan case inner surface and a second component being attached to the fan case liner outer surface.

Abstract: A fan case assembly is adapted to extend around blades of a fan rotor included in a gas turbine engine. The fan case assembly includes an annular case that extends around an axis, a fan track liner coupled to the annular case and extending circumferentially at least partway about the axis, and a bolting arrangement that couples the fan track liner to the annular case.

Abstract: A pump features a trimmed impeller having a trimmed impeller diameter that is less than a standard full-sized diameter of a standard full-sized impeller for a standard full-sized casing, and having a circumferential outer edge; and a modified standard full-sized casing having dimensions corresponding to the standard full-sized casing and configured to house the trimmed impeller for pumping a fluid, having an outer peripheral wall, and having an inner annular volute portion between the circumferential outer edge of the trimmed impeller and the outer peripheral wall configured with a volume of material deposited using an additive manufacturing process so as to fill in vacant space otherwise caused by the trimmed impeller diameter being less than the standard full-sized impeller diameter. The additive manufacturing process is a directed energy deposition.

Abstract: A pump for conveying a fluid includes a stationary housing, an impeller conveying the fluid from a low pressure region to a high pressure region, a shaft to rotate the impeller about an axial direction, and a separation device to restrict a flow of the fluid from the high pressure region to the low pressure region. The separation device includes a rotary part connected to the shaft, and a stationary part stationary with respect to the housing. The rotary and stationary parts face each other and delimit a gap between the stationary part and the rotary part. The gap is arranged between the high and low pressure regions. A recess is disposed in the stationary part or the rotary part, the recess including a bottom, and a non-metallic insert is disposed in the recess. A relief channel enables fluid communication between the bottom and the low pressure region.

Abstract: A compression ring for a shrouded compressor including a radially inner surface having one or more areas configured to mate flush with one or more portions of a radially outward surface of a shroud of the shrouded compressor, a radially outer surface located opposite the radially inner surface, a labyrinth seal located on the radially outer surface, a groove located within the radially inner surface, and a load ring located within the groove.

Abstract: A gas turbine engine comprising: a combustor configured to initiate combustion; and a turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes; wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring. A method of starting a gas turbine engine is also described.

Abstract: A composite case for a gas turbine engine includes an inner structure assembly defining an impact containment zone. The inner structure assembly is configured to circumscribe a plurality of rotatable blades of the gas turbine engine and to receive blade fragments in an event of blade failure. The inner structure assembly includes one or more layers containing a resin impregnated therein, and an outer structure assembly surrounding the inner structure assembly and integrally molded thereon. The outer structure assembly includes one or more layers containing a resin impregnated therein. One or more layers of the inner and the outer structure assemblies include resin reinforced by nanoparticles.

Abstract: A vertical member, which is preferably a support post used in a molten metal pump, includes a ceramic tube and tensioning structures to add a compressive load to the tube along its longitudinal axis. This makes the tube less prone to breakage. A device, such as a pump, used in a molten metal bath includes one or more of such vertical members.

Abstract: A containment system for a gas turbine engine includes an outer containment ring having a first projection that extends radially inward and an inner containment ring having at least a second projection that extends radially outward toward the outer containment ring. The second projection is offset and spaced apart from the first projection to define a chamber in a first state. The containment system includes a lattice defined within the chamber that spans the chamber, and the lattice is integrally formed with each of the outer containment ring and the inner containment ring. The second projection is configured to interlock with the first projection in a second state.

Abstract: Gas turbine engine (GTE) compressor sections and compressor intake ducts are provided having Soft Foreign Object debris (SFOD) endwall treatments, which reduce peak damage to GTE components in the event of SFOD ingestion. In embodiments, the GTE compressor section includes a compressor rotor and a compressor intake duct. The compressor intake duct includes an intake flow passage, which extends through compressor intake duct to the compressor rotor. A first duct endwall extends around a centerline of the flow passage to bound a peripheral portion of the intake flow passage. An SFOD endwall treatment includes topological features formed in or otherwise provided on the first duct endwall. The topological features of the SFOD endwall treatment are configured such that SFOD impacting the topological features is directed in a radially inward direction toward the flow passage centerline prior discharge of the SFOD from the intake flow passage and into the compressor rotor.

Abstract: An engine is provided with a cylinder block and a pump cover cooperating to define a volute chamber for a coolant pump. An impeller is connected to a drive shaft and positioned within the volute chamber. An insert is positioned within the volute chamber directly adjacent to a cutwater along a portion of the outer wall, with the insert positioned between the cutwater and the impeller. A method is provided where, in response to pre-determining a first coolant pump displacement, a first impeller is positioned within a volute chamber defined by a block and a cover. In response to pre-determining a second coolant pump displacement being less than the first displacement, an insert is affixed along the wall adjacent to the cutwater and a second impeller is positioned within the chamber.

Abstract: A gas turbine engine includes an annular structure disposed around an engine central longitudinal axis of the gas turbine engine. The annular structure defines an annular channel and comprises a first density, according to various embodiments. The gas turbine engine may further include a weight-saving filler disposed within the annular channel. The weight-saving filler may have a second density that is less than the first density. The gas turbine engine may further include an annular retention strap disposed around the engine central longitudinal axis of the gas turbine engine. The annular retention strap is at least partially embedded in the weight-saving filler, according to various embodiments.

Abstract: A fan case includes a composite fan case body including an outer surface and at least one attachment tool attached to the outer surface of the fan case body. The attachment tool includes a boss that has at least one fastener opening with a threaded insert. A channel extends from at least one interior cavity of the attachment tool through an outer wall of the attachment tool.

Abstract: An engine system has a crankshaft gear coupled to an engine crankshaft and a balance gear coupled to a balance shaft. The balance gear is formed by a disc having first and second opposite sides and a series of teeth. A first sector of the disc has at least one aperture therethrough, and a second opposite sector of the disc defines a recess intersecting the first side. The balance gear has a damper formed by a cover plate connected to the first side to enclose the recess and contain a plurality of particles therein. A gear and a method of forming a gear is also provided, with the gear having a first sector defining at least one aperture therethrough and a second sector defining a recess intersecting the first side. A plurality of particles are positioned in the recess, and a cover plate encloses the recess to form a damper.

Abstract: A reconfigurable pump includes a housing with inlet and outlet openings. An inlet adapter is mounted on the housing and includes an inlet passage communicating with the inlet opening. The inlet adapter is removably mounted on the housing and can be removed and repositioned for reconfiguring the pump between low-inlet and high-inlet configurations. In a low-inlet configuration the inlet passage is generally aligned with an impeller rotatably mounted in the housing. A check valve comprising a flapper valve is provided in the low-inlet configuration and prevents backflow. The flapper valve is removable for configuration in a high-inlet configuration with the inlet passage located generally above the impeller level. The inlet adapter can readily be repositioned from outside the pump housing between its low-inlet and high-inlet configurations.

Abstract: An apparatus for absorption of an impact energy from at least one blade fragment is disclosed. The impact energy acts on an element that is inserted into an opening in a turbo-machine. The opening passes radially through a housing section in a region of a row of rotating blades. The apparatus has a holder for holding the element in an ideal position and releasing the element beyond a preset maximum load and has a cage at a rear to secure the element in a radially outward-directed displacement. A turbo-machine having such an apparatus, as well as a method for multistage energy absorption, is also disclosed.

Abstract: A fan track liner assembly for ducted fan engine which provides for reduced strain and deformation of front of fan case in the event of a fan blade off event. Various assemblies are proposed. In one aspect, assembly includes fan track liner panel and plurality of fasteners which are arranged to secure panel to fan case of engine, wherein: a forward portion of panel includes hinged portion which operates as trapdoor to permit blade or blade fragment to pass through, and fasteners are arranged to fail in the event of blade or blade fragment passing through trapdoor causing panel to be displaced rearwards in fan case. Other aspects provide for reduced height of support on fan case for attaching fan track liner and for collapsible comb box.

Abstract: A water jet intake grate mounted to an intake opening in the hull of a watercraft includes parallel stringer blades having sharp cutting edges which span between fore and aft base plates to shred water borne debris as the debris sucked through the intake opening. The base plates are anchored to the hull at opposite ends of the intake opening. A transverse knife blade having sharp cutting edges spans across the stringer blades and the aft base plate includes a transverse sharp cutting edge, both for crosscut shredding of debris. The aft base plate includes an inboard tail blade lying in a plane parallel to the stringer blades having sharp cutting edges for shredding any residual debris.

Abstract: A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element. A hook projects in a generally radially inward direction from the annular casing element and is positioned axially forward of an array of fan blades when the fan containment system is fitted around said fan blades. Tabs protrude from the hook in a generally rearward direction and are spaced circumferentially along the hook. Fasteners connect the fan track liner to the tabs. The fasteners are configured so as to permit movement of the fan track liner towards the annular casing element when the fan track liner is impacted by a released fan blade.

Abstract: A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.

Abstract: A hovercraft includes a lift air supply source having a dynamic air flow area in communication with a central lift air chamber to provide continuous air flow to the central lift air chamber and a static air flow area in communication with an inflatable skirt extending around a periphery of the hovercraft. Air flow from the static air flow area enters the skirt to replenish air leaking from the skirt. The static air flow area has less air flow than the dynamic air flow area. The static air flow area is located at a higher position than the dynamic air flow area to reduce the likelihood of water entering the inflatable skirt when the hovercraft is operated on water.

Abstract: The pump housing (2) includes a circumferential wall (3), a pump casing (20) and a shaft cover (40). The pump casing (20) is attached to the circumferential wall (3) by a plurality of connection elements. The pump casing (20) includes a central opening (27) to form an axial supply (14) of the pump housing (2) for material to be pumped. The circumferential wall (3) closes the pump housing (2) along its outer circumference. The pump (1) includes a plurality of connection elements (22) connecting the pump casing (20) to the circumferential wall (3). The connection elements (22) are positioned in groups along the circumference of the pump housing (2), wherein the groups are regularly distributed along the circumference of the pump housing (2).

Abstract: A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element. The fan containment system further includes an annular fan track liner comprising a plurality of adjacent arcuate fan track liner panels. Each of the plurality of fan track liner panels is connected to the fan case at the hook via one or more fasteners configured to permit movement of the fan track liner panel relative to the hook such that the fan track liner panel can pivot towards the annular casing element when a released fan blade impacts the fan track liner panel.

Abstract: An electric pump has a pump casing, a sealing plate, an impeller and a motor for driving the impeller. The pump casing has a main body. A recess is formed in the main body and with the sealing plate defines a pump chamber. A suction port is connected to the pump chamber by a suction channel and a suction passage formed in the main body. A discharge port is connected to the pump chamber by a discharge channel. The suction passage extends axially from the recess. The recess, suction passage, suction channel and discharge channel are all shaped in a manner allowing the pump casing can be molded as a monolithic structure in a single injection molding process.

Abstract: A centrifugal fan includes an impeller, a motor portion, and a housing. The housing includes an upper plate portion, a lower plate portion arranged to have the motor portion fixed thereto; and a side wall portion. A flow control member is arranged to extend in a line along a boundary between an inside surface of the side wall portion and one of a lower surface of the upper plate portion and an upper surface of the lower plate portion. The flow control member includes a flow control surface arranged to extend radially outward from the one of the lower surface of the upper plate portion and the upper surface of the lower plate portion to the inside surface of the side wall portion while becoming more distant from the one of the lower surface of the upper plate portion and the upper surface of the lower plate portion.

Abstract: A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads.

Abstract: A containment casing is provided comprising a radially outer layer; an intermediate energy absorbing layer, and a retention framework for retaining an aerofoil blade in the event of detachment of whole or part of the blade. The retention framework is distributed axially and circumferentially along the casing and extends substantially radially inwardly at least partially through the intermediate energy absorbing layer.

Abstract: Composite article includes a generally cylindrical body having an internal grid structure interleaved with casing layers formed of reinforcing fibers disposed in a resin matrix. The composite article may be utilized in a fan case containment system for aircraft engine applications. Methods for fabricating the composite article are also provided.

Abstract: A coupling pin for use in a pump housing, the pump housing including an outer casing and an inner pump liner, the coupling pin being suitable for locating the liner and casing relative to one another, the coupling pin including a shank and a head at one end of the shank. The head includes a cammed surface thereon which is adapted to co-operate with a follower on the liner, and a locating section on a remote or terminal end of the head which is adapted to be positioned against a seat in the outer casing when fitted. The arrangement is such that rotation of the coupling pin causes the follower to track along the cammed surface so as to cause relative movement between the outer casing and the inner pump liner.

Abstract: The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behavior of the elements.

Abstract: A turbomachine casing assembly including a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element is provided. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof.

Abstract: An example gas turbine engine shroud includes a first annular ceramic wall having an inner side for resisting high temperature turbine engine gasses and an outer side with a plurality of radial slots. A second annular metallic wall is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs in communication with the slot of the first annular ceramic wall. The tabs of the second annular metallic wall and slots of the first annular ceramic wall are in communication such that the first annular ceramic wall and second annular metallic wall are affixed.

Abstract: A gas turbine engine fan section includes first and second composite layers providing a generally cylindrical case. Axially spaced apart rings are arranged between the first and second composite layers and form reinforcing ribs that provide a fan containment area axially between the rings. A belt is arranged over and spans the fan containment area between the reinforcing ribs. A fan blade has a tip in proximity to the first composite layer without any intervening structural support between the tip and the first composite layer, which provides a fan blade rub resistant surface. A method of manufacturing a fan containment case includes wrapping at least one first composite layer around a mandrel. Axially spaced apart rings are arranged circumferentially about the first composite layer. At least one second composite layer is wrapped around the rings and first composite layer to provide reinforcing ribs at the rings.

Abstract: A liner panel, such as a cassette 120 of a fan track liner of a gas turbine engine, is secured to a casing of the engine at flanges 124 and 126. Foam pads 42 are disposed between the casing 40 and the cassette 120 to support the cassette 120 from the casing 40. The pads 42 may be made from a reticulated polyurethane foam which is sufficiently resilient to be compressed and to expand to remain in contact with the cassette 120 and the casing 40 as the cassette 120 moves towards and away from the casing 40 during the assembly process. The foam is impregnated with a hardener composition which is uncured during installation of the cassette 120, but subsequently cures to increase the rigidity of the pads 42.

Abstract: A pump casing for a centrifugal pump, which comprises an inlet opening, a discharge outlet, and a transition surface extending between an inner peripheral surface of the main pumping chamber and an inner peripheral surface of the discharge outlet, the transition surface arranged for separating an in use exit flow of material in the discharge outlet from an in use recirculation flow of material in the main pumping chamber. The transition surface has a cutwater having a profiled section which comprises a protrusion which extends irregularly from an otherwise generally rounded arched or U-shaped transition surface and is configured such that, in use, the velocity and/or turbulence resulting from the in use flow of the material being pumped in the main pumping chamber is reduced.

Abstract: A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.

Abstract: The nacelle of the invention includes an air-inlet front section, a middle section for encasing the fan of the turbofan (7) and a rear section including means for connection to a pylon to be connected to the rigid structure or an airplane. The rear section includes a structural framework (18) having at least one aerodynamic smoothing and acoustic panel (21). The acoustic panel (21) is secured on the structural framework (18) by floating or elastic fixation means so that said acoustic panel (21) can be deformed in a direction (31) essentially centrifugal and radial relative to the turbofan (7) in the presence of overpressure air (3) in the engine compartment.

Abstract: A variable inlet area turbine employs a volute with a discharge area for flow of exhaust gas carried in the volute into a turbine inlet area. A flexible dividing wall having an end is movable along a path defined adjacent the turbine inlet area and transitioning in a smooth curve into an outer wall of the volute. The dividing wall is selectively positionable by insertion and withdrawal along the path to vary the discharge area from substantially closed to substantially open.

Abstract: A gas turbine engine includes a fan including a plurality of circumferentially spaced rotatable blades, and a fan casing for containing fragments of fan blades in the event of blade release, the fan casing having a shell surrounding the blades and circumscribing a containment zone of the fan. The shell is made of a fiber reinforced polymer composite material which includes nanoparticles.

Abstract: A self-adjusting liner assembly for installation within a centrifugal pump of the type having an impeller and a pump casing having a suction inlet is provided, comprising a liner having a sealing end, the sealing end having at least one substantially planar outer most surface for contacting an outer surface of the impeller; and a resilient member disposed in the liner, said resilient member providing a force so that the at least one outer most surface remains in substantially continuous contact with the outer surface of the impeller.

Abstract: A turbofan engine comprising an annular inner wall surrounding tips of the fan blades, a layer of insulating material surrounding the inner wall, and an outer casing including an annular outer wall surrounding the insulating material and concentric to the inner wall and at least two annular rub elements extending radially inwardly from the outer wall through only part of a radial thickness of the layer of insulating material, at least two of the rub elements being in axial alignment with the blade tips at every point around a circumference of the fan, each rub element having a radially inner end spaced apart from the inner wall and made of a material harder than that of the blades, and a containment fabric layer wrapped around a support structure of the outer wall.

Abstract: A turbine engine fan case assembly includes a structural case and a liner assembly. A radially accommodating attachment system connects the liner assembly to the structural case. The attachment system comprises a circumferentially-distributed plurality of longitudinally elongate radially outwardly open channels mounted to the liner assembly. The attachment system further comprises an associated plurality of inwardly-projecting tongues mounted to the structural case. Each tongue is accommodated in an associated said channel.

Abstract: Embodiments of the invention provide a pump with a housing including a pump chamber and an impeller positioned within the pump chamber. The pump also includes a socket with a wear plate, an inner ring, and an outer ring. The wear plate at least partially defines the pump chamber. The impeller is in contact with the wear plate. An outer surface of the outer ring is coupled to the housing. An inner surface of the outer ring receives a bearing. The inner ring receives a seal. A portion of the housing is molded over an end of the socket.

Abstract: A fan casing (2) for a jet engine has a burst protection arrangement (7) made up of layers at least in an area of fan blades (5). To contain detached fan blades (5) within a fan casing (2) of a jet engine by use of a low-weight and easily manufacturable burst protection arrangement (7), the fan casing (2) is made of a fiber-composite material which itself forms at least one layer provided with at least one inorganic, non-metallic protective layer (8).

Abstract: A cooling fan includes a housing, a cover on the housing and an impeller received in a space between the housing and the cover. The housing includes a bottom wall and a sidewall projecting upwardly from an outer periphery of the bottom wall. The sidewall defines an air outlet therein. The impeller includes a hub and a plurality of blades extending radially out from the hub. A porous layer extends into the space between the housing and the cover from the sidewall at a location adjacent to the air outlet.

Abstract: Turbine components are often shipped individually and are not shipped assembled into a turbine. To this end, the turbine blade has to be protected of external stresses and external damage. This is done by an easily removable protective coating that easily evaporates during the first operation of the newly produced or restored component, so that the protective coating does not have to be removed in an additional operational step before installation.

Abstract: An axial turbo-compressor for a gas turbine having a stator vane assembly that is formed by stator vanes having vane tips exposed on the hub side and a stationary shaft cover on the hub side and delimits the flow channel of the axial compressor is provided. A radial gap is designed between the shaft cover and the van tips that is minimally sized such that the axial turbo-compressor may still be assembled, and there is a plurality of recesses in the shaft cover, wherein one of the recesses is allocated to each vane tip that is arranged directly neighboring the vane tip allocated thereto and is sized such that during operation of the axial turbo compressor every vane tip may be plunged into the recess allocated thereto without one of the vane tips significantly contacting the shaft cover.

Abstract: A fluid intake assembly adapted for use with a turbo-machine is provided. The fluid intake assembly provides an efficient fluid inlet assembly including a casing adapted to guide fluid into the turbo-machine. The casing includes an inner wall, the inner wall having a lining of a resin infused composite material. A method of producing a fluid intake assembly for use with a turbo-machine is also provided.

Abstract: Composite containment casing including a body having an interior, an abradable system integrally joined to the interior of the body of the containment casing wherein the abradable system comprises, a sandwich structure including a first facesheet and a second facesheet position about at least one core layer, and at least one abradable layer applied to the sandwich structure wherein the at least one core layer comprises any of a cell configuration, a columnar configuration, or a truss configuration and wherein the sandwich structure is strong radially and weak circumferentially.