Abstract: A stator vane assembly for a gas turbine engine includes an inner vane support defining a first aperture, an outer vane support defining a second aperture, a stator having an inner end that extends through the first aperture and an outer end that extends through the second aperture, and a first bracket. The first bracket is operatively connected to the inner vane support and extends over the first aperture. The first bracket and the inner vane support defining a first pocket.

Abstract: Methods for preparing ceramic products using liquid infusion technology and products formed from the same are provided. The methods and products include the incorporation of a particulate material and binder between ceramic fibers such that the fibers may be properly spaced during formation of the ceramic product. Ceramic matrix composite products can thereby be provided using near net shaping methods.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a housing mountable to an engine static structure, a seal carrier secured to the housing and configured to be selectively biased from the housing, and a wedge seal secured to the seal carrier. The wedge seal abuts against sealing surfaces of adjacent blade outer air seals in response to movement of the seal carrier relative to the housing. The wedge seal is separate and distinct from the seal carrier. A method of sealing between adjacent components of a gas turbine engine is also disclosed.

Abstract: An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same.

Abstract: An apparatus and method for a multiple layer fan casing surrounding a fan having a plurality of circumferentially spaced blades rotatable about a rotational axis and having a sub-portion defining a blade impact zone, the multiple layers comprising an inner fiber layer confronting the blades, an outer fiber layer overlying the inner carbon layer, a glass layer sandwiched between the inner and outer composite fiber layers.

Abstract: Functional components of spacecraft structures can be subject to detrimental impacts by energetic particles produced from an electric propulsion system. A graphene coating applied to a functional component can maintain electrical conductivity upon a surface of the functional component, thereby allowing charge dissipation to take place, while also resisting sputtering erosion resulting from impacts of the energetic particles. Accordingly, spacecraft structures can include an electric propulsion system, a functional component that is at least partially impacted by an outflow of the electric propulsion system, and a graphene coating upon the functional component. Methods for operating such spacecraft structures can include generating an outflow of energetic particles from an electric propulsion system of a spacecraft structure, and at least partially impacting the outflow of energetic particles upon a functional component of the spacecraft structure, where the functional component has a graphene coating thereon.

Abstract: A containment case includes a fan assembly including a hub having a plurality of fan blades extending radially outward between radially inward blade roots and radially outward blade tips. Containment case includes a radially outer shell circumscribing fan assembly and having a first radially inner surface and a radially outer surface, an inner structure having a second radially inner surface extending along first radially inner surface, and a trench extending circumferentially along second radially inner surface into inner structure from second radially inner surface. The trench is approximately axially aligned with the fan assembly. The containment case also includes, within the trench, a trench filler layer configured to dissipate impact energy from a released fan blade and having a plurality of sheets including a fibrous composite material having a plurality of fibers fabricated within each sheet, where the sheets are coupled together into a repeating pattern of hollow units.

Abstract: A fan containment case for a gas turbine engine is provided which includes a barrel having an outermost portion, an innermost portion, and an interior portion in-between the outermost portion and the innermost portion. The outermost portion has an outermost band of material made of carbon fiber composite and the innermost portion has an innermost band of material made of carbon fiber composite. The interior portion includes a first interior band and a second interior band adjacent the first interior band. The first interior band is made of poly p-phenylene-2,6-benzobisoxazole (PBO) and the second interior band is made of an aramid material. The innermost portion has an innermost band of material made of carbon fiber composite.

Abstract: According to one aspect, a fan containment case for a gas turbine engine is provided which includes a barrel having a first band of material on an outside of the barrel. The first band is made of carbon fiber composite. The barrel further includes a second band of material inboard of the fan case and made of poly p-phenylene-2,6-benzobisoxazole (PBO) composite. The barrel also includes a third band of material made of carbon fiber composite inboard of the second band.

Abstract: A centrifugal fan with an increased shutoff pressure maintains a negative pressure between a casing and a rotatable disk. The centrifugal fan includes an impeller including a rotatable disk and blades extending vertically from the rotatable disk and arranged radially about an axis of rotation of the rotatable disk toward a rim of the disk, a casing accommodating the impeller and including a base plate at its end face nearer the rotatable disk, and a motor mounted on the base plate externally and including a shaft fixed at a center of the rotatable disk to rotate the impeller. The rotatable disk has reflux holes at positions between inner rims and outer rims of the blades in its radial direction. The reflux holes allow a gas to reflux from between the rotating disk and the base plate inside the impeller as the impeller rotates.

Abstract: The invention relates to systems for transferring molten metal from one structure to another. Aspects of the invention include a transfer chamber constructed inside of or next to a vessel used to retain molten metal. The transfer chamber is in fluid communication with the vessel so molten metal from the vessel can enter the transfer chamber. A powered device, which may be inside of the transfer chamber, moves molten metal upward and out of the transfer chamber and preferably into a structure outside of the vessel, such as another vessel or a launder.

Abstract: In a casing for an electronic apparatus, a plurality of ribs are integrally formed on an inner surface of the casing, and the plurality of ribs form an isogrid structure in which a plurality of equilateral-triangular segments are arranged regularly adjacent to each other.

Abstract: The invention relates to a steam turbine rotor wherein the inter blade region rotor surface, the feed region rotor surface, the piston region rotor surface and the stress relief groove rotor surface of the rotor are configured and arranged as steam exposed surfaces during normal operation of the steam turbine rotor. The steam turbine rotor has a thermal barrier coating on at least the piston region rotor surface.

Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.

Abstract: A rotor for a gas turbine engine includes a hub having an outer periphery, a first plurality of blades arranged on the outer periphery of the hub, and a second plurality of blades arranged on the outer periphery of the hub. The first plurality of blades is made of a first material and has a first elastic modulus over density ratio. The first plurality of blades has a first natural frequency. The second plurality of blades is made of a second material and has a second elastic modulus over density ratio. The second elastic modulus over density ratio is different from the first elastic modulus over density ratio. The second plurality of blades has a second natural frequency different from the first natural frequency. A method of fabricating a bladed rotor is also presented.

Abstract: Assemblies and methods useful for mounting an engine to an aircraft structure are disclosed. An exemplary assembly comprises a body made of a magnesium-based material defining a socket formed therein and a liner disposed in the socket for receiving and interfacing with an engine mounting element of the aircraft. The liner comprises a peripheral side wall and a bottom wall having an outer periphery in sealing engagement with a lower portion of the peripheral side wall. The liner is made of a liner material that provides a galvanic potential between the liner material and a material of the engine mounting element that is lower than a galvanic potential between the magnesium-based material of the body and the material of the engine mounting element.

Abstract: A composite thermal barrier coating (TBC) may be applied to a surface of components within an internal combustion engine. The composite TBC provides low thermal conductivity and low heat capacity insulation that is sealed against combustion gasses. The composite TBC includes three layers, bonded to one another, i.e., a first (bonding) layer, a second (insulating) layer, and a third (sealing) layer. The insulating layer is disposed between the bonding layer and the sealing layer. The bonding layer is bonded to the component and to the insulating layer. The insulating layer includes hollow microspheres that are sintered together to form insulation that provides a low effective thermal conductivity and low effective heat capacity. The sealing layer is a thin film that is configured to resist the high temperatures, present within the engine. The sealing layer is impermeable to gasses and presents a smooth surface.

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan containment case assembly that has an outer case extending about an axis, and a thermally conforming liner assembly radially inward of the outer case. The liner assembly has a shell, a wrap radially outward of the shell, and a ballistic liner between the outer case and the wrap. The wrap has a first fiber construction, and the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness.

Abstract: A turbine engine has an engine case with an inlet and an interior of the engine. A bearing is disposed on a portion of the engine case. A fan is disposed within the engine and rotates with operation of the engine. The fan includes a plurality of fan blades, and each fan blade is secured at a first end to a disk. A second end of each fan blade is disposed adjacent to the bearing. The portion is oriented relative to the fan such that a reaction force of a fan blade impacting the bearing is directed axially or away from the inlet.

Abstract: A blade of a gas turbine engine may comprise a cavity defined, at least partially, by a first interior surface of the blade and by a second interior surface of the blade. A first rib and a second rib may extend from the first interior surface. A third rib may extend from the second interior surface and may be located between the first rib and the second rib. A bulkhead rib may traverse the cavity and may separate the cavity into a radially inward portion and a radially outward portion. A viscoelastic material may be disposed in the radially inward portion of the cavity.

Abstract: A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.

Abstract: A wind turbine comprising a support structure and one or more turbine blades is disclosed, that incorporates means for reducing the radar cross section (RCS), wherein the support structure is notionally divided into an upper section in the shadow of the blade sweep area, and a lower section beneath the upper section, wherein the upper section is adapted to have the means for reducing the RCS, and the lower section does not have the said adaptation. The invention makes use of the realization that the blade masking the tower as it rotates (or the blade being masked by the tower if facing away from a radar), contributes significantly to interference to radar systems, and so localized application of e.g. RAM can give good RCS reduction at a lower cost than treating the whole structure.

Abstract: The invention relates to a method of producing a low-pressure compressor stator for an axial turbine engine. The stator comprises an external shroud with stubs and an annular row of stator blades extending radially towards the inside from the stubs. The method comprises the following stages: supply or production of a starting bar; bending of the bar so that it makes a circle, in order to form an unwrought external shroud; turning to form an axial annular wall delimited by annular fixing flanges; orbital friction-welding of a row of blades onto the stubs of the external shroud. The stubs are realized during a milling stage of the bar or of the external shroud, the milling being carried out before or after the bending stage. The shroud and the blades can be produced in titanium or in a thermoplastic polymer.

Abstract: A carbon fiber material is coated with nanoparticles, where the coating contains from 0.01 to less than 10% by weight of nanoparticles, based on the dry weight of the coated fiber material, and the coating may optionally be involved in further reactions.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile, and a first endwall section with which the airfoil section is attached. First and second airfoil pieces form different portions of the airfoil profile. The first and second airfoil pieces include respective first ends. The first ends interlock with the first endwall section such that the first and second airfoil pieces are retained with the first endwall section.

Abstract: A composite fiber stator ring for a gas turbine engine compressor includes a plurality of composite fiber vane structures. Each of the composite fiber vane structures includes a plurality of fiber plies. All of the fiber plies flow in a single direction at each joint of the corresponding composite fiber vane structure. The plurality of composite fiber vane structures are arranged circumferentially in a ring.

Abstract: A vane assembly includes inner and outer rings, a plurality of segmented vane structures circumferentially-spaced around a central axis and between the inner and outer rings, and at least one spring that mechanically traps the segmented vane structures in radial compression between the inner and outer rings.

Abstract: An airflow system that has a fan spacer within a fan assembly is provided for use with equipment such as work vehicles, which may include agricultural implements or other agricultural equipment. The fan spacer influences a width dimension of a fan housing interior and airflow characteristics of the fan assembly, such as output pressure and flow rate, to optimize fan performance for a particular implementation. In this way, the fan spacer allows for highly customizable fan performances by using housing spacers to modify fan housing dimensions and provide performance characteristics that correspond to what is needed for particular implementations while using common fan housing segments.

Abstract: Described is a nozzle guide vane assembly may comprise: a plurality of nozzle guide vane passages arranged in an annular array, each nozzle guide passage comprising inner and outer radial platforms, a suction surface of a first vane, and a pressure surface of a second vane, wherein the nozzle guide passages are made from a plurality of layers of ceramic fibers held in a ceramic matrix, wherein a first nozzle guide passage includes at least one attachment lug attaching the nozzle guide passage to either or both of an engine casing and an adjacent second nozzle guide passage, the attachment lug being integral with the first nozzle guide passage.

Abstract: A progressive cavity positive displacement motor having a rotor and stator includes a measurements-while-drilling (“MWD”) tool disposed within the rotor. The motor may use one or more alignment members to measure the position of the rotor relative to the stator. The MWD tool can collect data regarding physical properties such as orientation, temperature, pressure, and other properties. The MWD tool incorporated in the rotor is configured to measure differential properties near or at the uphole and downhole ends of the motor.

Abstract: A blading member for fluid flow machines, for example, gas turbine engines. The blading member includes a platform member, at least one airfoil member, and at least one interlock member.

Abstract: A rotator may be configured to be accommodated in a casing of a pump for sucking a fluid into the casing and discharging the fluid outside of the casing. The rotator may comprise an insert portion configured to insert a rotating shaft and one or more communicating openings. The one or more communicating openings may be disposed in a vicinity of the insert portion, and pierce the rotator in a direction along the rotating shaft. The rotator may be made of resin. A flow direction of the resin located around the insert portion and the one or more communicating openings may extend at least in the direction along the rotating shaft.

Abstract: An inter-turbine duct includes a first annular wall with a ceramic composite material and including a first plurality of layers and a second plurality of layers, the first plurality of layers including a slot extending therethrough; and a first vane with a material of a metal alloy or a ceramic material. The first vane has a first end and a flange extending through the slot with the flange extending away from the first end and being retained between the first plurality of layers and the second plurality of layers of the first annular wall.

Abstract: A turbine engine rotor shaft includes at least one portion having an outer periphery having a determined diameter forming a free surface for heat exchange with the environment of said rotor. The outer periphery includes a plurality of irregularities which are designed to provide a heat exchange surface of the shaft of the rotor which is greater than a surface of the periphery of a cylinder having the same determined average diameter.

Abstract: Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. in the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

Abstract: Composite materials having carbon reinforcement fibers impregnated with a matrix material are augmented with functionalized graphene nanoplatelets having amine groups formed on a surface of the graphene nanoplatelets and epoxide groups formed on at least one edge of the graphene nanoplatelets as a supplement to or a replacement for resin matrix material to increase strength of the composite materials. Related methods of increasing strength of composite materials include mixing the functionalized graphene nanoplatelets into the matrix material prior to impregnating the carbon reinforcement fibers, depositing the functionalized graphene nanoplatelets onto the matrix material to form an interlayer, and depositing the functionalized graphene nanoplatelets onto a bed of carbon reinforcement fibers with no resin matrix material. The composite materials and related methods for increasing strength of composite materials may include graphene nanoplatelets having holes formed through the graphene nanoplatelets.

Abstract: A turbine component includes an airfoil-shaped core having an outer peripheral surface. A plurality of channels is formed in the core, each opening to the outer peripheral surface. The channels extend substantially radially to be elongated in the radial direction. A first platform is attached to the core. The component also includes an airfoil-shaped non-permeable skin having a hollow interior, an inner peripheral surface and an outer peripheral surface. The skin is sized so that the core can be received in the hollow interior of the skin. A second platform is attached to the skin. The core is received in the hollow interior of the skin such that the outer peripheral surface of the core engages the inner peripheral surface of the skin such that a plurality of generally radial cooling channels are formed between the channels in the core and the inner peripheral surface of the skin.

Abstract: A turbine engine fan case (48) comprises a composite body member (300) circumscribing an axis (500) and having an annular mounting portion (310, 410), a segmented polymer member (320, 330, 420, 440) along the annular mounting portion, and integrated therewith.

Abstract: A method of constructing the nozzle guide passage may include the steps of: providing a tubular pre-form having a plurality of layers of unconsolidated CMC fibers in which the internal walls of the tubular preform provide either working surfaces which define the main gas path walls of the assembled nozzle vane, or extraneous wall portions which do not provide working surfaces of the assembled nozzle guide vane arrangement; cutting the wall portions to provide one or more flaps which remain attached to the pre-form via a connecting portion of wall; and, displacing the flap from a first pre-cut position, to a second consolidation position to provide one or more ancillary features.

Abstract: A nozzle for a gas turbine engine, including an airfoil having an exterior surface, flange and radially compressive contact face. Also included is an airfoil support frame having a mating face positioned in engagement with the contact face. A non-orthogonal engagement angle is provided in order to transmit a compressive force to the airfoil.

Abstract: A ceramic component is generally provided that includes a silicon-based layer comprising a silicon-containing material (e.g., a silicon metal and/or a silicide) and about 0.001% to about 85% of a Ga-containing compound. For example, the silicon-based layer can be a bond coating directly on the surface of the substrate. Alternatively or additionally, the silicon-based layer can be an outer layer defining a surface of the substrate, with an environmental barrier coating on the surface of the substrate. Gas turbine engines are also generally provided that include such a ceramic component.

Abstract: In one aspect the present subject matter is directed to a system for supporting a turbine shroud. The system includes a shroud support at least partially defining a first piston sleeve and a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head. The first piston head is slideably engaged with an inner surface of the first piston sleeve. The second piston head is slideably engaged with an inner surface of a second piston sleeve. The system also includes a turbine shroud that is fixedly connected to the piston assembly and that extends radially inwardly from the shroud support. The piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a change in a radial force applied to a hot side surface of the turbine shroud.

Abstract: To solve the problems of compressor wheel blade flow separation causing surge type noises when a compressor return or recirculation valve is opened or closed, recirculation airflow from a compressor recirculation valve is fed into an annular volume, defined between inner and outer walls or shaped as a radially expanded, axially flattened cylindrical space in the compressor inlet, so that the generally unidirectional radial flow from the compressor recirculation valve is re-directed and organized as it is turned from generally radial to generally axial, merging with the general inlet flow and presenting the compressor wheel with airflow of“circumferentially uniform” flow velocity.

Abstract: A rotor for a supercharging device may include a compressor wheel and a turbine wheel. A sealing disc may be arranged between the compressor wheel and the turbine wheel. The sealing disc may include a first side interfacing with the compressor wheel and a second side interfacing with the turbine wheel. The compressor wheel and the turbine wheel may each define one of a holding contour and a counter-holding contour, which respectively interact with a corresponding one of a holding contour and a counter-holding contour defined on each of the first side and the second side of the sealing disc. The respective holding contour may correspond to the respective counter-holding contour, which may engage in one another and secure the compressor wheel, the sealing disc and the turbine wheel to one another.

Abstract: A mounting bracket for mounting an accessory to a gas turbine engine, the mounting bracket including a space frame structure. The space frame structure including a plurality of struts joined to one another at nodes.

Abstract: A rotor disk includes a ring shaped rotor body defining a radially inward opening, rims protrude radially outward from the rotor body, and outwardly facing rotor blade retention slots are defined between circumferentially adjacent rims. Each slot is operable to receive and retain a corresponding rotor blade, and each rim of the rims includes an anti-vibratory feature. The anti-vibratory feature includes a structure defining an isogrid pattern intruding into a surface of the rim.

Abstract: Dishwasher drain assemblies having overmolded volutes are disclosed. A disclosed example drain assembly for a dishwasher having a tub, a sump fluidly coupled to the tub, and a discharge outlet includes a drain pump having an impeller to pump fluid from the sump to the discharge outlet, and a resilient member overmolded onto at least a portion of the drain pump, the resilient member defining a volute for the drain pump.

Abstract: A progressive vortex pump comprises an inlet housing in contact with the pumped fluid, a pump housing connected to the inlet housing, and an outlet housing connected to the pump housing and connected to a pumping pipe. The pump housing comprises a disc-shaped rotor having a central bore and a rim with vanes. Each rotor comprises at least one through hole along the axial direction, the through hole being positioned between the central bore and the rotor rim. Advantageously, the presence of a through hole on the rotor enables, under operating conditions, fluid exchange from the posterior fluid film to the anterior fluid film, thus promoting a pressure balance between the posterior and anterior fluid films, therefore enabling the rotor to work evenly, preventing rubbing on adjacent diffusers.

Abstract: A turbine exhaust case (28) comprises a one-piece fairing (120) defining an air-flow path through the turbine exhaust case, and a multi-piece frame (100). The multi-piece frame is disposed through and around the one-piece vane fairing to support a bearing load, and comprises an inner ring (104), an outer ring (102), a plurality of covers (110), and a plurality of radial struts (106). The outer ring is disposed concentrically outward of the inner ring, and has hollow bosses (114) with strut apertures (SA) at vane locations. The covers are secured to the hollow bosses. The radial struts pass through the one-piece vane fairing and through apertures in the outer angled ring, and are radially fastened to the inner ring and the flat caps.

Abstract: A fiber structure includes a blank portion formed as a single part by three-dimensional weaving between a first plurality of yarn layers and a second plurality of yarn layers, the blank portion corresponding to all or part of a fiber reinforcement preform for a part made of composite material. Outside the blank portion, the fiber structure includes one or more two-dimensional fabric layers, each two-dimensional fabric layer grouping together the yarns of a single layer belonging to at least the first plurality of yarn layers and situated outside the blank portion.