Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.

Abstract: A device includes a molten metal pump and a metal-transfer conduit. A clamp may be used to attach the metal-transfer conduit to the pump. The pump has a pump base including an indentation configured to receive the metal-transfer conduit and align the pump outlet with the transfer inlet. The pump outlet may be formed in the indentation and preferably near the center of the indentation in order to better align with the transfer inlet. As the pump operates it moves molten metal through a pump outlet that is in communication with a transfer inlet in the metal-transfer conduit. The molten metal enters the transfer inlet, moves upwards in a passage in the metal-transfer conduit, and out of a transfer outlet.

Abstract: A fluid pump assembly is provided. The pump has a pair of units magnetically coupled to each other. The first unit contains a drive motor and a magnetic assembly. The second unit contains a magnetic assembly and a blade of a propeller/impeller for imparting movement to a fluid. As the first unit is activated by the drive motor, a magnetic flux is created which in turn rotates the magnetic assembly in the second unit, driving the blade.

Abstract: A fan (1) has a rotor (10) and a fan impeller (20). The rotor (10) has a connecting portion (11) and the fan impeller (20) has a fastening portion (21). The impeller is centered relative to the rotor (10) with the fastening portion (21) on the connecting portion (11) by at least one centering element (40). The impeller is fixed to the rotor (10) by at least one fastening element (30). The fastening element (30) is a screw with a screw head (31), a threaded portion (33), and a shaft arranged between the threaded portion (33) and the screw head (31). A spacer sleeve (34) is arranged around the shaft. A thread (12) corresponding to the fastening element (30) is, respectively, formed in the connecting portion (11).

Abstract: A composite material blade molding method is for molding a composite material blade by curing a prepreg. The composite material blade has a back-side blade member and a belly-side blade member which are superposed and joined. The composite material blade molding method includes: a lamination step for forming a back-side laminate in a back-side molding die and forming a belly-side laminate in a belly-side molding die; an inner surface cowl plate disposition step for disposing an inner surface cowl plate for maintaining an inner space formed by the back-side laminate and the belly-side laminate; a die mating step for die-mating the back-side molding die and the belly-side molding die and disposing a foaming agent in the inner space maintained by the inner surface cowl plate; and a curing step for heating and expanding the foaming agent and heat-curing the back-side laminate and the belly-side laminate.

Abstract: An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine.

Abstract: A tie rod assembly structure, a gas turbine having the same, and a method of assembling tie rod are provided. The tie rod assembly structure includes a tie rod on which a plurality of rotor disks are mounted, a bearing support shaft mounted to the tie rod to support the rotor disks and on which a bearing is mounted, a first nut mounted on the tie rod on one side of the bearing support shaft, and a second nut that is fastened to the first nut to tension the tie rod and then is in close contact with the bearing support shaft to support the bearing support shaft.

Abstract: In an embodiment, a ducted fan assembly includes a housing that further includes a rotor. The ducted fan assembly also includes a rim that extends around at least a portion of a perimeter of the ducted fan assembly, where the rim defines an opening surrounding at least a portion of the housing. The ducted fan assembly also includes a skin that is attached to the rim and extends around the at least a portion of a perimeter of the ducted fan assembly to form a leading edge of the ducted fan assembly. The ducted fan assembly also includes a blade positioned on the rim underneath the skin.

Abstract: Apparatus and methods for pressurizing well operations fluids via a pressure exchanger. The pressure exchanger has a housing, a rotor within the housing, a first cap covering the rotor at a first end of the housing, and a second cap covering the rotor at a second end of the housing. The rotor includes chambers distributed around a central axis of the rotor and a first fluid passage. Each of the chambers and the first fluid passage extend through the rotor between a first face of the rotor and a second face of the rotor. The first cap includes a first fluid inlet, a first fluid outlet, and a second fluid passage, and the second cap includes a second fluid inlet and a second fluid outlet. The second fluid passage fluidly connects the first fluid passage with the first fluid outlet.

Abstract: An airfoil includes an airfoil section that has radially inner and outer ends and defines an airfoil profile. The airfoil profile has a leading end, a trailing end, a suction side, and a pressure side. The airfoil section includes a ceramic airfoil piece that defines a portion of the airfoil profile. The ceramic airfoil piece includes an exterior wall that has an internal cooling circuit.

Abstract: An apparatus and method for cooling an engine component, such as an airfoil, for a turbine engine including an outer wall separating a cooling fluid flow from a hot fluid flow. A cooling circuit including a cooling passage having opposing sidewalls can be provided in the engine component. At least one turbulator can be provided between the opposing sidewalls, and can include a conduit having an inlet and an outlet passing through the at least one turbulator.

Abstract: The present disclosure is directed to a cooling system for a turbomachine. The cooling system includes a turbomachine component defining a turbomachine component cavity. The cooling system also includes an insert positioned within the turbomachine component cavity for cooling the turbomachine component. The insert includes an insert body and a spring body. The spring body includes a first portion fixedly coupled to the insert body, a second portion in sliding engagement with the turbomachine component, and a third portion in sliding engagement with the insert body.

Abstract: Disclosed is a turbine rotor device for a gas turbine, the turbine rotor device comprising a turbine rotor body, and a pre-stressed fiber-wound layer, wherein the pre-stressed fiber-wound layer is wound on the periphery of the turbine rotor body to exert a predetermined pre-loading force on the turbine rotor body. Additionally, a rotor, and a gas turbine and a turbine engine having the turbine rotor device are also provided.

Abstract: An air exhaust apparatus includes a housing, a shaft, a bearing part, a propeller, and an impeller disposed at a lower portion of the shaft. The housing has a space formed therein and an outlet formed at an upper portion thereof to discharge air flowed into the space. The shaft is installed inside of the housing in a vertical direction. The bearing part supports the shaft to revolve. The propeller is disposed at an upper portion of the shaft to be rotated by an exhaust suction flow in a duct. The impeller includes a rotating plate having a through hole for air inlet and a plurality of fins formed on the rotating plate, and is rotated with the propeller. A funnel-shaped vortex is formed under the impeller when the propeller and impeller revolve.

Abstract: A rotor positioning system for rotary pressure exchangers with a rotor with a central bore accommodating an axle affixed to end covers in each end having at least one pair of high and low pressure ports in communication with opposing end cover ports through coaxial rotor ducts.

Abstract: A vane device for a gas turbine is provided. The vane device includes a first airfoil having a first suction side and a first pressure side, a second airfoil having a second suction side and a second pressure side, an inner shroud and an outer shroud. The first airfoil and the second airfoil are arranged between the inner shroud and the outer shroud, wherein the first airfoil and the second airfoil are at least partially coated with a MCrAlY coating. At least the first suction side has a first coated surface section which is coated with a thermal barrier coating and which represents at least a part of the total surface of the first suction side. At least the inner shroud or the outer shroud has a further coated surface section which is coated with a further thermal barrier coating. A corresponding method of manufacturing is also provided.

Abstract: A hollow ceramic matrix composite (CMC) turbine bucket with an internal reinforcement lattice structure has improved vibration properties and stiffness. The lattice structure is formed of thin-walled plies made of CMC. The wall structures are arranged and located according to high stress areas within the hollow bucket. After the melt infiltration process, the mandrels melt away, leaving the wall structure to become the internal lattice reinforcement structure of the bucket.

Abstract: A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings.

Abstract: The invention relates to an electrical machine having a fan wheel which comprises an injection-moulded blade carrier ring with fan blades as well as an annular insertion part which is integrated into the blade carrier ring and which comprises passage openings via which the blade carrier ring is connected to the fan blades.

Abstract: Embodiments of an apparatus, system, method and techniques are described for an improved volumetric resistance blower and rotor. An apparatus may comprise, for example a motor, a casing having one or more inlets and one or more outlets, and a cylindrical rotor to create a volumetric resistance inside the casing, at least a portion of the rotor comprising a porous material. Other embodiments are described.

Abstract: A centrifugal compressor comprises at least one stage suited to separate a liquid phase and a gas phase with the aid of at least one of a hydrophobic, super-hydrophobic, hydrophilic or super-hydrophilic surface layer, wherein the hydrophobic and/or super-hydrophobic surface layer is disposed on at least one of an inlet guide vane, impeller, return channel straight hub, or exiting hub bend; and the hydrophilic and/or super-hydrophilic surface is disposed on at least one of the impeller casing, diffuser casing, exiting casing bend, return channel straight hub, exiting hub bend, collection point, or drain.

Abstract: A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers.

Abstract: A turbomachine component of a stationary turbomachine includes a substrate made of high alloyed 10% to 18% chromium steels or titanium alloys or nickel base alloys or cobalt base alloys with a substrate surface and an erosion and corrosion resistant coating system. The coating system includes a first layer, which is deposited on the substrate surface of the turbomachine component and acts as a corrosion resistant layer and a second layer. The second layer is deposited on the first layer and acts as an erosion resistant layer, wherein the first layer is a Zr single layer and the second layer is a W/WC multilayer.

Abstract: Devices and methods provide for an impeller for use in a compressor. A method for manufacturing the impeller includes: attaching an intermediate layer to a base metal by placing a first metal powder into a gap between a first insert and the base metal; processing with hot isostatic pressing the base metal, the first metal powder and the first insert such that the intermediate layer is bonded to the base metal; attaching an external layer to the intermediate layer by placing a second powder into a gap between a second insert and the intermediate layer; processing the base metal, the intermediate layer, the second metal powder and the second insert via hot isostatic pressing such that the external layer is bonded to the intermediate layer; and removing the second insert to form the impeller, wherein the external layer is corrosion resistant.

Abstract: A method for increasing wear resistance of a turbocharger includes exposing at least a bearing surface of a center housing of the turbocharger to a gas nitrocarburizing process or a plasma nitrocarburizing process, thereby forming a conversion coating impregnated onto the at least the bearing surface.

Abstract: A centrifugal pump is provided having a volute casing having a discharge conduit, an impeller provided in the volute casing, and a suction sideliner enclosing the impeller in the volute casing, the suction sideliner being at least partially covered with sintered tungsten carbide tiles. In one embodiment, the impellor has a central hub, a plurality of vanes spacedly attached to the hub, and at least one side plate attached to the vanes, whereby each vane is individually wear protected prior to attaching each vane to the hub.

Abstract: A fan housing structure including a base seat and a sideboard. The base seat has a bed section and a mating section extending along a periphery of the bed section. The bed section has a bush made of a material other than the material of the bed section. The bush is disposed on the bed section to axially protrude therefrom. The sideboard is made of a material other than the material of the base seat. The sideboard is disposed on the mating section and integrally connected with the base seat. The sideboard and the base seat together define a space therebetween. The sideboard and the bush are made of a material other than the material of the base seat and are integrally connected with the base seat by means of insert injection molding. Accordingly, the fan housing structure has enhanced structural strength and thinner thickness to save room.

Abstract: A spline seal for a hot gas path component is provided. The spline seal may include a first metal layer and a second metal layer. The first metal layer may have a first volumetric thermal expansion coefficient. The second metal layer may be disposed adjacent the first metal layer and have a second volumetric thermal expansion coefficient. The second volumetric thermal expansion coefficient may be higher than the first volumetric thermal expansion coefficient. When the spline seal is exposed to a heat source, the first and second metal layers may deform to provide a seal between the hot gas path component and an adjacent hot gas path component.

Abstract: The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behavior of different components based on different heatings of the components.

Abstract: The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behavior of different components based on different heatings of the components.

Abstract: A turbocharger includes a center housing having a bearing surface configured to contact an inner surface of a unison ring. A conversion coating is impregnated onto at least the bearing surface of the center housing.

Abstract: Erosion- and impact-resistant ceramic coatings suitable for protecting surfaces subjected to collisions with particles, including nominally round particles that typically inflict impact damage and more aggressive irregular-shaped particles that typically inflict erosion damage. The ceramic coating is formed to have one of three compositions: at least one layer of titanium aluminum nitride (TiAlN) having a thickness of about 25 to about 100 micrometers; multiple layers of chromium nitride (CrN) and TiAlN, each layer having a thickness of about 0.2 to about 1.0 micrometers to yield a total coating thickness of at least about 3 micrometers; and at least one layer of titanium silicon carbonitride (TiSiCN) having a thickness of about 15 to about 100 micrometers. The ceramic coating preferably has a total coating thickness of up to about 100 micrometers, and is deposited by a physical vapor deposition process to have a columnar and/or dense microstructure.

Abstract: This invention relates to a Dry Running Flexible Impeller Pump and Method of Manufacture that is specifically designed to provide a flexible impeller pump that is capable of being run dry for extended periods of time without damaging the impeller. The pump's housing and end plates are coated with a low friction industrial coating to limit the heat of friction created by the flexible impeller while in use. Additionally the flexible impeller is cast from a pre-molding silicone substrate that contains no mold release and is cast in a mold that is treated with a low friction industrial coating and is cast without mold release. Once the flexible impeller is removed from the mold it is cleaned with alcohol, baked in a vacuum at a temperature of at least 100° C., and then coated with a Paralene N coating by vacuum deposition.

Abstract: An object is to provide a method for forming a superior corrosion-resistant plating layer by sealing penetrating pinholes formed in an electroless plating layer. There are provided a first plating step of performing electroless Ni—P plating on a base material (1); an etching step of etching a surface of a first plating layer (3) formed by the first plating step; and a second plating step of performing electroless Ni—P plating to form a second plating layer (5) on the first plating layer (3) processed by the etching step.

Abstract: The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behavior of different components based on different heatings of the components.

Abstract: A turbine airfoil having an improved impact and erosion resistance. The airfoil comprises: (a) a base segment having an impact resistant leading edge section proximate to the leading edge comprising a material having having a yield strength of least about 250 ksi and an elongation percentage of about 12% or less; and (b) an erosion resistant coating overlaying the base segment at least in the leading and trailing edge portions of the pressure side, the erosion resistant coating comprising at least one ceramic layer having at least one of the following properties: (1) an erosion value of at least about 200 g. of erodent to cause a thickness loss of about 15-20 microns; (2) an erosion volume loss value (V) of about 1.9 or less as defined by the equation V=H?0.18×E0.75×F?1.65 where H is hardness, E is elastic modulus and F is fracture toughness; and (3) an F value of at least about 1.5 MPa*m1/2.

Abstract: The invention relates to a machine component with a base made of a base material, a part of the surface of which has been equipped with armor-plating, made of a plating material with greater hardness in comparison to the base material, with the armor-plating being segmented and made up of a number of armor-plating segments.

Abstract: A turbine airfoil having an improved impact and erosion resistance. The airfoil comprises: (a) a base segment having an impact resistant leading edge section proximate to the leading edge comprising a material having having a yield strength of least about 250 ksi and an elongation percentage of about 12% or less; and (b) an erosion resistant coating overlaying the base segment at least in the leading and trailing edge portions of the pressure side, the erosion resistant coating comprising at least one ceramic layer having at least one of the following properties: (1) an erosion value of at least about 200 g. of erodent to cause a thickness loss of about 15–20 microns; (2) an erosion volume loss value (V) of about 1.9 or less as defined by the equation V=H?0.18×E0.75×F?1.65 where H is hardness, E is elastic modulus and F is fracture toughness; and (3) an F value of at least about 1.5 MPa*m1/2.

Abstract: A sanitary centrifugal pump with a hygienic mechanical seal flushing system. The pump has a housing with a pumping chamber defined therein. An impeller is at least partially contained in the housing and is connected to a shaft for rotation. The rotation of the impeller creates a first liquid flow path through the pumping chamber between the inlet port and the outlet port, and the first liquid flow path creates a high pressure area in the pumping chamber. The pump includes additional seal flushing passages by which liquid is delivered to the seal cavity from the pumping chamber and returned back to the pumping chamber, to cool and flush at least a portion of the mechanical seal in the seal cavity.

Abstract: A turbine vibrator including a housing having a first end and a second end and a generally cylindrical internal surface forming a cylindrical central chamber. An end cap is attached to each end of the housing including one or more outlet ports in fluid communication with the central chamber. A turbine wheel is located within the central chamber of the housing and is rotatably supported by the end caps. The turbine wheel includes a central shaft, a cylindrical wall extending concentrically about the central shaft, and an eccentric weight extending between the shaft and the cylindrical wall. A rotor including a plurality of teeth formed from an elastomeric material extends around the cylindrical wall. A cap cover including one or more outlet ports is attached to each end cap with a muffler member disposed between the outlet ports in the end cap and the outlet ports in the cap cover.

Abstract: A vacuum pump has a pump case having a gas suction port at an upper surface thereof, a rotor shaft mounted in the pump case for undergoing rotation, and a rotor connected to the rotor shaft for rotation therewith. The rotor has inner and outer circumferential surfaces coated with a corrosion-resistant film treated by nonelectrolytic plating. Rotor blades are disposed in the pump case and are integrally connected to the outer circumferential surface of the rotor. Stator blades are integrally connected to the pump case so that the rotor blades and the stator blades are alternately positioned and arranged. A balancing body is disposed on the inner circumferential surface of the rotor for balancing the rotor during rotation thereof.

Abstract: To provide a rotor material preferable for a steam turbine of which main steam temperature is 675° C. or more, particularly exceeding 700° C., and a steam turbine plant having a rotor formed by the material, the invention provides a steam turbine plant including a very-high-pressure turbine of which steam inlet temperature is 675 to 725° C. and steam outlet temperature is 650° C. or less, a high-pressure turbine, and a medium-low-pressure turbine, wherein a rotor of the very-high-pressure turbine is formed from a forged material of NiFe-base alloy containing: 14 to 18 weight % Cr, 15 to 45 weight % Fe, 1.0 to 2.0 weight % Al, 1.0 to 1.8 weight % Ti, C and N of which the sum is 0.05 or less weight %, and Nb in the range specified by the formula: 3.5−(Fe weight %)/20<(Nb weight %)<4.5−(Fe weight %)/20.

Abstract: An impeller shaft assembly, coupler and molten metal pump are described, in which a coupling member is configured to be secured to a pump drive shaft and includes a socket part that is defined by a socket wall formed about and extending along an axis. The socket wall includes a plurality of coupling shaft engaging surfaces and a plurality of socket corner surfaces joining the shaft engaging surfaces. The socket corner surfaces are disposed radially outward from adjacent shaft engaging surfaces with respect to the axis.

Abstract: A gas turbine component includes a platform having a first coating on at least a portion thereof, where the first coating is a diffusion aluminide coating. An airfoil extends from the platform and has an external surface and an internal surface defining cooling passages therethrough. The airfoil has an airfoil shape made of a substrate alloy, a second coating on the external surface of the airfoil shape, the second coating comprising an overlay coating, and a third coating on the internal surface of the airfoil shape, the third coating comprising a diffusion aluminide coating different in composition from the second coating.

Abstract: A gas turbine airfoil includes an internal cooling passage defined by an internal airfoil surface, and an external airfoil surface. The gas turbine airfoil is protected on both the internal airfoil surface and the external airfoil surface. The internal airfoil surface is protected by forming a diffusion aluminide protective layer at the internal airfoil surface of the internal cooling passage, with substantially no aluminum deposited on the external airfoil surface during the step of forming. The external airfoil surface is protected by depositing an overlay protective coating on the external airfoil surface, with substantially no aluminum or diffusion aluminide between the overlay protective coating and the external airfoil surface. The gas turbine airfoil is operated in a gas turbine engine, and may later be removed for repair.

Abstract: A molten metal impeller having a base portion including a circumferential notch. The notch having a generally radial wall and a generally axial wall, at least one of the radial or axial walls including a plurality of grooves. A ceramic bearing ring is cemented into the notch.

Abstract: A nonmetallic pump for pumping molten metal includes a base with an impeller chamber, at least one molten metal inlet opening to the base, at least one molten metal outlet opening from the base, and an impeller connected to one end of a motor driven shaft and rotatable in the impeller chamber. The base includes an impeller opening in which the impeller is disposed and a wall extending so as to form a spiral-shaped opening around the impeller opening. An egress channel extends from the spiral-shaped opening toward the molten metal outlet opening.