Abstract: A component for a turbomachine having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent. The intermetallic material is compacted and/or modified in microstructure by microplasticization at least partially at a surface or interface in a region close to the surface or interface.

Abstract: A gas turbine engine includes a bearing. A bearing support includes a first wall that extends between the first and second ends and is operatively supported by the bearing at a first end. An engine case is secured to the second end radially outward of the first end. A flexible support is provided by a second wall integral with and extending transversely from the first wall. The second wall has a first flange and a gear train component is secured to the first flange.

Abstract: A turbine engine includes a fan that provides an air flow to the turbine engine as compressor intake air and as compressor bypass air, a first stage compressor positioned to receive the compressor intake air and output a first stage compressed air, and a boiler positioned to cool the first stage compressed air using a fluid. A second stage compressor is positioned to receive the cooled first stage compressed air. A pump is configured to pump the fluid as a liquid into the boiler, extract energy from the first stage compressed air, and cause the cooling of the first stage compressed air.

Abstract: A method of fabricating a turbine engine shaft from a metal billet of generally cylindrical shape, the method including drilling the billet to form a through axial cylindrical bore therein, engaging a cylindrical insert in the bore, the insert being made of a material having yield stress close to that of the material of the billet so that the materials of the insert and of the billet have substantially the same behavior during forging, hot forging the billet to form a forged blank of length greater than that of the billet, withdrawing the insert, and machining the blank.

Abstract: A torque converter is provided. The torque converter includes a front cover for connecting to an engine crankshaft; a clutch plate; a clutch backing plate limiting axial movement of the clutch plate away from the front cover; and a connector rigidly connected to the front cover and including a rivet portion for fixing the clutch backing plate to the front cover. A method of forming a torque converter is also provided.

Abstract: A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.

Abstract: A drive module for a hydraulic hybrid vehicle includes two variable displacement over-center bent-axis hydraulic pump/motors with respective yokes that reside and pivot within a common fluid-filled case. The cylinder barrel of each pump/motor is connected to high pressure through fluid-conducting yoke legs, and is connected to low pressure through the fluid-filled case, which is connected by a port to a low pressure source. As a drivetrain for a vehicle, one pump/motor acts primarily as a pump driven by an engine and the other pump/motor acts primarily as a motor to propel the vehicle. A removable support structure facilitates installation to a variety of vehicle chassis.

Abstract: A gas turbine engine includes a fan including a plurality of fan blades rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a geared architecture arranged in a housing and driven by the turbine section for rotating the fan about the axis, and a support member that supports the geared architecture within the gas turbine engine. The support member includes an inner portion and an outer portion. One of the inner and outer portions is configured to be coupled to the geared architecture and the other of the inner and outer portions is configured to be coupled to the housing. A plurality of removal features each have at least one engaging surface to facilitate a pulling force on the support member in a direction parallel to the axis.

Abstract: A method for manufacturing an intake manifold is provided that is capable of suppressing deterioration in the dimensional accuracy by correcting warping and deformation caused during molding. When an intake manifold that is made of plastic and has a surge tank and intake pipes extending from the surge tank is manufactured, distal members, which form the distal ends of the intake pipes, are positioned on a jig. In this state, the distal members and the main bodies of the intake pipes are fixed to each other by vibration-welding.

Abstract: A thermal/electrical power converter includes a gas turbine with an input couplable to an output of an inert gas thermal power source, a compressor including an output couplable to an input of the inert gas thermal power source, and a generator coupled to the gas turbine. The thermal/electrical power converter also includes a heat exchanger with an input coupled to an output of the gas turbine and an output coupled to an input of the compressor. The heat exchanger includes a series-coupled super-heater heat exchanger, a boiler heat exchanger and a water preheater heat exchanger. The thermal/electrical power converter also includes a reservoir tank and reservoir tank control valves configured to regulate a power output of the thermal/electrical power converter.

Abstract: The invention refers to a method for producing a near-surface cooling passage in a thermally highly stressed component, which includes: a) providing a component which has a surface on a hot side in a region which is to be cooled; b) letting a channel into the surface; c) inserting a cooling tube into the channel; d) filling the channel, with the cooling tube inserted, with a temperature-resistant filling material in such a way that the inserted cooling tube is embedded into the filling material, leaving free an inlet and an outlet; and e) covering the channel, with the cooling tube embedded, with an anti-oxidation, temperature-stable cover layer. The method is inexpensive and can be used in a flexible manner in the most diverse situations in order to save cooling medium or to reduce the thermal load.

Abstract: A wake reducing structure for a turbine system includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is an airfoil at least partially disposed in the wake region, the airfoil comprising at least one airfoil hole.

Abstract: An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

Abstract: A liquid gallery for a fuel injector of a gas turbine engine includes a gallery body, a liquid gallery scroll, a plurality of atomizer inlets, and a plurality of atomizer bosses. The liquid gallery scroll extends into the gallery body spanning from a first end to a second end in a circumferential direction. The liquid gallery scroll includes a taper with a cross-sectional area of the liquid gallery scroll reducing from the first end to the second end. Each atomizer inlet is in flow communication with the liquid gallery scroll. Each atomizer boss is aligned with one of the plurality of atomizer inlets.

Abstract: A waste or storm water pumping station and system used to pump water from a lower elevation to a higher elevation during the process of moving or managing the water is disclosed herein. The pumping station has a wet well collection chamber with a sloped floor and an integral valve vault chamber cast within the pump station body, which results in increased storage capacity in the wet well chamber for pump station components. Additionally, the pumping station may be installed as a single unit of equal depth to eliminate differential settlement and multiple or uneven excavations.

Abstract: An electrical unit comprises an electrical connector having a set of elongate electrical terminals which are each a one-piece component. The terminals extend into the unit such that first ends of the terminals are connected to multiple electrical conductors within the unit and second ends of the terminals project from a surface of the unit. A collar is formed at the surface of the unit to at least partially encircle the projecting second ends. This arrangement allows the unit to be electrically connected at the electrical connector by press fitting to a terminating region of a flexible electrical harness, the collar defining a recess in which the terminating region is located.

Abstract: Methods and apparatus for changing actuator output torques are disclosed. An example method includes decoupling a first end cap from a body of an actuator. A first spring assembly is positioned within a first outer chamber defined by the first end cap and the body. A first end of the first spring assembly is positioned adjacent a surface of a first piston. A second end of the first spring assembly is positioned adjacent the first end cap when the first end cap is coupled to the body. The method includes positioning a first spacer within the first outer chamber and coupling the first end cap to the body. The first spacer changes a distance between the first and second ends of the first spring assembly when the first end cap is coupled to the body to change an output torque of the actuator.

Abstract: A method for creating a connecting element, arranged between two components of a structure, or a turbojet engine structure, which is subjected to compressive and/or tensile loadings and which includes a hollow shaft immersed, at least partially, in a stream of air flowing between the two components, the method including: dimensioning a width of the main cross section associated with the shaft of the connecting element in a direction orthogonal to the longitudinal axis of the shaft according to desired mechanical strength and desired mass, and according to characteristics of the airstream; and working an external surface of the shaft of the connecting element, at least over part of this surface, to give it a surface finish with an arithmetic mean roughness at least equal to 20 microns, to reduce drag of the connecting element thus dimensioned by comparison with a smooth connecting element of the same diameter.

Abstract: A hybrid turbomachine enclosure includes a plurality of walls interconnected to form an interior configured and disposed to receive a turbomachine, the plurality of walls including a first wall having a panel on frame construction and a hybrid wall including a first portion having a panel on frame structure and a second portion having a stiffened frame panel structure.

Abstract: A hydraulic power system for a utility vehicle having an engine with a crankshaft. The system features first and second rotationally-driven power generating devices, one of which is a hydraulic pump and the other of which is an alternator and one of which is a hydraulic pump. The first device has a first rotational input for operative coupling to the crankshaft for driven rotation thereby. A secondary shaft has an input end portion arranged for rotational coupling to a rotationally driven member of the first device and an output end portion arranged for rotational coupling to a second rotational input of the second device for driving thereof under driven operation of the first rotationally-driven power generating device by the crankshaft. Higher power output of increased reliability is provided over prior art add-on hydraulic solutions using electric-over-hydraulic power packs.

Abstract: A laser spark plug, in particular for an internal combustion engine, having a combustion chamber window through which laser radiation may be emitted from an interior of the laser spark plug toward an exterior, the laser spark plug having a component which surrounds at least part of the beam path of the laser radiation in the area of the exterior. In particular, the laser spark plug, in the area of the component, has at least one channel which has at least two orifice sections and which allows fluid communication between the orifice sections, a first orifice section being situated in the area of an outer surface of the combustion chamber window, and a second orifice section being situated in a radially outer area of the laser spark plug, in particular of the component.

Abstract: The embodiments herein disclose a high degree of freedom (DOF) compliant nano-positioners and a method to fabricate the high DOF compliant nano-positioners. The system comprising a central stage and a plurality of micromanipulators is connected to the central stage. Each of the plurality of micromanipulators comprises a micro-actuator, a primary long beam and a primary micro beam. The micro-actuator comprises a pair of conducting pads, a secondary micro-beam, a secondary long beam and a box spring. A preset amount of the non-zero voltage is applied on the conducting pads to cause a displacement in the micromanipulator. The embodiments herein also disclose a fabrication method of developing a bi-planar structure for a high degree of freedom nano-positioner.

Abstract: In some two-stroke engines, a stationary ring is disposed in a groove in the cylinder liner. However, it is a challenge to install such a stationary ring while maintaining a narrow gap to minimize gas flow through the gap. A ring system for an internal combustion engine is disclosed that includes an L-shaped, split ring with a reentrant angle and a nested, split ring with a convex quadrilateral cross section nested with the L-shaped ring proximate the reentrant angle. The two rings are affixed so that the two gaps of the split rings cannot align. Or, in other embodiments, the two are allowed to rotate relative to each other over a predetermined angle.

Abstract: A repair method of a plate member disposed so as to separate a high-pressure space and a low-pressure space and having a cooling passage provided inside thereof along a surface thereof, comprising: removing a damaged portion generated in the plate member so as to expose the cooling passage; primarily filling an area where a material is removed so as to block the cooling passage and form an external shape of the plate member having no missing portion as compared to its original external shape; forming a first opening through which the cooling passage communicates with the low-pressure space on an upstream side, in a flow direction of a refrigerant in the cooling passage, of a position where the cooling passage is blocked; and forming a second opening through which the cooling passage communicates with the high-pressure space on a downstream side of the position where the cooling passage is blocked.

Abstract: A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend outward from the engine case to the fan case. A front frame assembly includes a plurality of vanes extending radially across the gaspath. A transmission couples a shaft to a fan shaft to drive the fan. A bearing assembly couples the shaft to the front frame assembly. A bearing support extends aftward and radially inward from the front frame assembly to the bearing assembly.

Abstract: A method of assembling a fuel pump on an engine is disclosed. The method includes a timing pin installed between a pump flange of the fuel pump and a flywheel housing of the engine. The pump flange is moved towards the flywheel housing. The timing pin is further removed which is installed between the pump flange and the flywheel housing of the engine. Further, the pump flange is abutted with the flywheel housing of the engine.

Abstract: Hollow curved plates (20, 50, 70) include first plate members 241-243 having a first groove 22 and second plate members 341-343 having a second groove 32 of approximately the same width as the first groove 22, the second plate members 341-343 being bonded to the first plate members 241-243 by diffusion bonding. The hollow curved plate is formed of the first plate members 241-243 and the second plate members 341-343 curved by bending in a state where the first plate members 241-243 and the second plate members 341-343 are bonded together. The first groove 22 faces the second groove 32, a position of the first groove 22 substantially coincides with a position of the second groove 32 in a width direction, and hollow parts 401-403 are formed by the first groove 22 and the second groove 32.

Abstract: One aspect of the present disclosure includes a ceramic matrix composite airfoil having a shaped ceramic matrix composite core, a cooling fluid flow network having ceramic foam components, and a ceramic lamina skin disposed about the shaped core and the cooling fluid flow network.

Abstract: A combustion chamber includes an inner wall, an outer wall surrounding the inner wall, and a flow passage between the inner wall and outer wall that permits forward flow and restricts reverse flow. The inner wall has a plurality of effusion holes in fluid communication with the inside of the combustion chamber. The outer wall has a plurality of cooling side holes in fluid communication with a cooling source. The inner wall and the outer wall define a flow passage therebetween that fluidly connects one or more of the cooling side holes with one or more of the effusion holes. The flow passage has a geometric configuration to permit forward flow of gases through the flow passage from the cooling source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside of the combustion chamber to the cooling source. The permitted flow rate is greater than the restricted flow rate.

Abstract: A method of controlling flutter of a fan nozzle includes, for a given design of a fan nozzle, determining a vibration mode that causes a flutter characteristic of the fan nozzle and, in response to the determined vibration mode, establishing a wall thickness distribution of at least one wall of the fan nozzle to include local thick portions and local thin portions that alter the flutter characteristic.

Abstract: A method and apparatus for restoring displaced features on a turbine vane segment for a gas turbine engine, such as a vane segment in a low pressure turbine, and more specifically, the inner shroud thereof relative to the outer shroud thereof to meet the original design position and dimensions.

Abstract: Centrifugal compressors, methods of forming centrifugal compressors, and methods of designing diffuser vanes in centrifugal compressors are provided herein. In an embodiment, a method of designing diffuser vanes includes providing an initial two-dimensional diffuser vane layout including initial diffuser vane peripheries radially spaced about an axis. The initial diffuser vane peripheries are rotated using a computer processor to produce rotated diffuser vane peripheries having offset trailing ends relative to the initial diffuser vane peripheries. The rotated diffuser vane peripheries are circumferentially shifted about the axis to produce shifted diffuser vane peripheries. Leading ends of the shifted diffuser vane peripheries are offset from the leading ends of the initial diffuser vane peripheries. Diffuser vane surfaces are generated that connect the shifted diffuser vane peripheries to the corresponding initial diffuser vane peripheries to form diffuser vanes in a twisted configuration.

Abstract: A bearing lubrication tube for an APU is mounted on a bearing to permit expansion and contraction of the tube along its length while preventing rotational movement of the tube. The bearing lubrication tube is held by a bracket attached to a flange outside the engine. The bracket includes a double hex ring with the outer hex ring engaging the bracket and an inner hex ring engaging the tube to prevent rotation of the tube. A cover on the bracket maintains the double hex ring in position.

Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

Abstract: One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.

Abstract: A steam turbine inlet assembly and method of constructing the same are disclosed. In an embodiment, an annular ring is provided, along with a body affixed to a distal face of the annular ring and extending distally therefrom. The body portion has a curved entrance geometry at the proximal end adjacent the annular ring, and transitions to a substantially polygonal exit geometry at a distal end.

Abstract: A system and method for aligning a gas turbine engine. The system and method includes installing an alignment mount, determining whether the gas turbine engine is aligned and/or in a sufficiently aligned condition, and modifying a vertical position of the gas turbine engine at the alignment mount in response. The alignment mount includes an engine attachment, a ground attachment, and an expansion member configured to allow the engine attachment and the ground attachment to move relative to each other and maintain a load path therebetween.

Abstract: A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture. The guide vane is secured to the outer surface of the casing such that the guide vane can be serviced from an outer part of the casing.

Abstract: Example embodiments are directed to fluid turbines that include a turbine shroud and a rotor assembly disposed within the turbine shroud. The rotor assembly includes a nacelle pivotally engageable with a tower structure and a slip ring disposed within the nacelle. The slip ring electrically connects one or more cables in the nacelle to one or more cables in the tower structure. The slip ring is engaged with the nacelle by a mounting apparatus which allows movement of the slip ring along at least one of an x-axis, a y-axis and a z-axis. Example embodiments are further directed to methods of maintaining untwisted electric cables in a fluid turbine.

Abstract: A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.

Abstract: The present invention relates to an element (1) that works sliding, of an internal combustion engine and/or a compressor that undergoes friction and receives a coating of chrome nitride having an equiaxial morphology, with low porosity (lower than 1%) and with a crystallographic orientation predominantly (111), maintaining some reticulate in the orientation (200), so as to improve its resistance to wear and its toughness, prolonging the useful life of the element (1) that works sliding.

Abstract: A rotary actuator includes a piston housing assembly including a cavity, a fluid port in cavity, and an open end. A rotor assembly is rotatably journaled in the piston housing assembly and includes a rotary output shaft, a rotor arm extending radially outward from the rotary output shaft, an arcuate-shaped piston disposed in said piston housing assembly for reciprocal movement in the piston housing assembly through the open end along a radius of curvature. A seal, the cavity, and the piston define a pressure chamber, and a portion of the piston connects to the rotor arm at an end portion.

Abstract: An inner shell assembly for a steam turbine includes an inner shell with a plurality of grooves of preset dimensions, and a plurality of nozzle carriers respectively securable in the plurality of grooves. Each of the nozzle carriers supports at least one nozzle and bucket for a turbine stage via a dovetail, where the inner shell, the plurality of nozzle carriers and the nozzles and buckets define a steam path. A radial position of the dovetails in the nozzle carriers within its corresponding grooves is selectable according to the steam path, and an axial width of each of the nozzle carriers is selectable according to the steam path.

Abstract: The invention uses a car's speed to gather ambient air in an air accumulator to create a fast-moving flow of that air and injecting that air to the exhaust piping in a direction to assist exhaust motion away from the engine.

Abstract: Apparatus and method for integrating an actuator into turbo-machinery and operating the actuator based on process fluid associated with the turbo-machinery. The integrated actuator mechanism includes an actuator casing; a balance drum, with labyrinth seals, and recovery spring, configured to apply force to the balance drum, in the actuator casing; an actuation bar connected to the balance drum and configured to move linearly in the direction of the balance drum; and a connection mechanism connecting a diverted portion of turbo-machinery process fluid to the actuator casing for applying force, in an opposite direction of the spring force, to the balance drum. The labyrinth seals allow the diverted turbo-machinery process fluid to bleed through and return to the turbo-machinery.

Abstract: A bearing foil assembly includes a top foil, an intermediate foil, and a bump foil. The bump foil is provided with corrugations at circumferentially spaced locations. The bump foil has an end that is bent radially outwardly from a center of the foil assembly. The top foil has a bent portion extending radially outwardly and adjacent to the bent end of the bump foil. A first radius of curvature is defined to a curved portion leading into the bent portion at a first end adjacent to the bent end. A second radius of curvature is defined at an end of the bent portion on an end opposed to the bent end. A ratio of the first radius of curvature to the second radius of curvature is between 0.6 and 10. A bearing assembly, a shaft sub-assembly, an air machine, and a method of assembling a bearing into an air machine are also disclosed.

Abstract: A fluid pump device is operable by a drive and actuating system. The fluid pump device includes a pump manifold, a plurality of pump cylinders, a plunger reciprocally operable in each of the pump cylinders, and at least one inlet selector valve. The pump cylinders may extend proximally from the pump manifold and are in selective fluid communication with the pump manifold via, for example, respective inlet and outlet check valves. The plungers are reciprocally operable within the pump cylinders and are independently and reciprocally operable by respective piston linear actuators provided in the drive and actuating system. The inlet selector valve is used to establish selective fluid communication between one or more fluid source containers and the pump manifold to control fluid flow into the pump manifold. The inlet selector valve may be located laterally outboard of the pump cylinders and extend generally parallel to the pump cylinders.

Abstract: Disclosed is an austenitic stainless steel alloy that includes, by weight, about 16% to about 21% chromium, about 4.5% to about 5.5% nickel, about 2% to about 5% manganese, about 1% to about 2% silicon, about 0.8% to about 1.2% tungsten, about 0.4% to about 0.8% molybdenum, about 0.4% to about 0.6% niobium, about 0.4% to about 0.5% carbon, and a balance of iron. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 1020° C.

Abstract: A method of assembling a gas turbine engine includes locating a consumable assembly tool clip within the engine

Abstract: A vehicle fuel delivery system, includes: a first line configured to deliver fuel from a fuel tank to an internal combustion engine (ICE); a second line configured to return fuel from the ICE to the tank or the first line; a heat exchanger in thermal communication with the second line; and a latent material in the heat exchanger configured to change from a solid state to a liquid state when fuel in the second line reaches a predetermined temperature.