Abstract: A method is provided for designing an airfoil.

Abstract: The invention relates to a single-piece fan blisk (14) for a turbojet, this blisk (14) comprising a hub (16) with a general shape of revolution about a rotation axis (AX) and comprising an external peripheral face (18) of revolution extending radially towards the rotation axis at an upstream face (19) and a downstream face both of which are in the form of rings. This hub (16) supports radially oriented blades (17) at its external peripheral face (18), each comprising a base through which it is connected to this external peripheral face (18), each blade (17) having a leading edge (22) and a trailing edge (23) that are radially oriented. The spacing between the upstream face (19) and the downstream face of the hub (16) along the rotation axis (AX) is less than the distance separating the leading edge (22) from the trailing edge (23) of each blade.

Abstract: A turbine includes a top cover, a bottom cover and fans between the top cover and the bottom cover. The fans extend to connect the central shaft and do not overlap with each other in the axial direction. The air sucked in through the central air inlet can swiftly flow along the fans and then be expelled out of the turbine through the circumferential air outlets. Compared with the conventional centrifugal fan, the disclosed turbine can effectively increase the air draft efficiency of the turbine. Compared with the standard turbine, the disclosed turbine is simpler and easier to process, and thus the cost can be significantly reduced.

Abstract: A system for forming a cooling hole in an airfoil includes a liquid-jet guided laser. The liquid-jet guided laser generates a laser beam confined within a fluid column. The fluid column/laser beam is directed at an outer surface of the airfoil. The system also includes a purge medium supply that is fluidly coupled to an aperture of the airfoil. The purge medium supply provides a purge medium into an inner cavity of the airfoil. The purge medium flow is oriented to flow in a flow direction that is substantially parallel to an inner surface of the cavity. A cooling hole is formed in the airfoil and extends through the outer surface and penetrates the inner surface of the cavity. A centerline of the cooling hole forms an acute angle with respect to the purge medium flow direction. The system described herein provides a method for manufacturing an airfoil.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.

Abstract: An apparatus includes a disk, an attachment member, and a blade. The disk has an outer surface including a coupling portion. The attachment member has a coupling portion and defines at least a portion of an opening. The coupling portion of the first attachment member is configured to be coupled to the coupling portion of the disk. A portion of the blade is configured to be disposed within the opening when the coupling portion of the attachment member is coupled to the coupling portion of the disk.

Abstract: A high pressure BLISK includes at least one circular row of airfoils circumferentially disposed about, integral with, and extending radially outwardly from an annular rim having an annular flat aft facing face with coplanar radially outer and inner face portions radially separated by an annular undercut extending into the rim from the aft facing face. Airfoil roots including root fillets extend around the airfoil between the rim and pressure and suction sides of the airfoils. An axially aftwardly extending annular cylindrical section extends aftwardly from the flat face. The BLISK being a first of axially adjacent first and second rotor sections connected by a rabbet joint. A forward arm of the second rotor section includes an outer forward facing annular face spaced apart from the aft facing face radially outwardly of the annular undercut and a radially inner forward facing annular face contacting the aft facing face.

Abstract: The present invention provides a method of making a metallic shield for shielding an edge of a component e.g. an aerofoil component such as a gas turbine blade or vane. The method comprises: providing a mandrel with a mandrel edge having a shape conforming to the shape of the component edge, wherein the mandrel edge comprises a surface having a width, W1; providing a metal wire having a substantially triangular radial cross-section with a base surface of width W2, wherein W2 equals W1; aligning and affixing the base surface of the wire on the surface of the mandrel edge; electro-depositing metal onto the mandrel and metal wire to form the metallic shield comprising the deposited metal and the metal wire; and removing the metallic shield from the mandrel.

Abstract: A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.

Abstract: An air guide element of an aircraft gas turbine, including an external housing that is provided with an inflow opening, as well as with a flow channel that is arranged inside the housing, characterized in that a tubular intermediate element that is made of an elastic material is arranged inside the inflow opening, connecting the inflow opening to the flow channel in a sealing and position-adjusting manner.

Abstract: A stator assembly includes a first stator vane sub-assembly with a first platform and a first airfoil extending from the first platform, and a second stator vane sub-assembly with a second platform and a second airfoil extending from the second platform. A gap is defined circumferentially between the first stator vane sub-assembly and the second stator vane sub-assembly. The stator assembly also includes a shroud structure, a first chamber defined between the first platform and the shroud structure, a second chamber defined between the second platform and the shroud structure, and a damper spring seal structure. Also included is a plate having a first portion within the first chamber and a second portion within the second chamber, such that the plate extends from the first chamber across the gap to the second chamber.

Abstract: The present application relates to a segmented inner shroud of a low-pressure compressor for an axial-flow turbine engine. The shroud includes an axial tubular wall, and a row of apertures formed in the axial wall. Each aperture has opposing edges situated to either side of a stator vane positioned in the aperture for the purpose of its attachment. The axial wall includes a radial flange which passes through the apertures in the circumferential direction of the shroud, so as to form a mechanical link between the opposing edges of the apertures. This mechanical seal permits the opposing edges to be joined together through each aperture, which improves the rigidity and the sealing. The shroud exhibits an E-shaped profile forming a sandwich structure with the annular sealing fins of the rotor, or sealing lips. The present application also relates to a method for the assembly of stator vanes abutting radially against the transverse radial flange.

Abstract: A turbomachine including an accessory drive case, connected to the engine shaft via a radial shaft, wherein the accessory drive case also includes: a primary shaft which is driven by the radial shaft via a bevel gearbox, and assemblies for mechanically driving accessories, driven by the primary shaft and configured such that the related accessories lie at the upper portion and on at least one of the side edges of the engine case.

Abstract: A system for controlling an angular position of a component of an aircraft includes a component having a shaft that includes at least one magnet. The system also includes a housing configured to receive the shaft and including at least one coil configured to generate a magnetic field based on a current through the at least one coil.

Abstract: A gas turbine engine includes a fan, a nacelle arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow from the fan. A nozzle associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.

Abstract: A turbine, in particular a gas turbine, includes a rotor, a housing spaced from the rotor by a gap, and a system for monitoring structure-borne noise, permit rubbing of the rotor and the housing to be localised with the least possible technical complexity. In both a first and second axial region, one or more inwardly directed rubbing teeth of the housing and one or more outwardly directed rubbing edges of the rotor are arranged, wherein the one or more rubbing teeth and the one or more rubbing edges are distributed along the circumference such that contact of the particular rubbing teeth and rubbing edges at a specified rotational frequency of the rotor occurs at a different frequency in the first axial region than in the second axial region.

Abstract: A turbo-machine, which can be operated in an optimized driving range is provided. To this end, a method for operating a turbo-machine having at least one turbo-machine stage, which has at least one rotary shaft is disclosed. According to the method, the following method steps are carried out: a) determining a desired efficiency characteristic value ?soll of the turbomachine stage; b) determining an actual efficiency characteristic value ?ist of the turbo-machine-stage; c) determining a comparison efficiency characteristic value of the turbo-machine stage by comparing the actual efficiency characteristic value ?ist and the desired efficiency characteristic value ?soll to one another; and d) changing at least one operating parameter of the turbo-machine stage subject to the comparison efficiency characteristic value ?vgl, wherein in order to determine the actual efficiency characteristic value ?ist, a measuring of a torque of the rotary shaft of the turbo-machine-stage is carried out.

Abstract: A flow surface comprises a composite material formed of a plurality of layers of the composite, and a piezoelectric actuator located within the layers or on an outer surface of the composite material. The piezoelectric actuator is actuatable to vibrate the composite material and one of inhibit ice build-up or shed ice which has formed.

Abstract: A turbocharger bearing assembly of a split turbocharger for an engine is disclosed in which key rotational parts are rotatably supported by a pair of spaced apart bearings located in a bore of a tubular bearing housing forming part of a bearing assembly. The rotational parts of the turbocharger bearing assembly are balanced as a unit before the turbocharger bearing assembly is assembled to a cylinder block of the engine by insertion into a bore formed in the cylinder block.

Abstract: A bearing support assembly includes a squirrel cage defining a longitudinal axis and having a cylindrical portion defining a bearing seat. The squirrel cage is configured and adapted to provide a first level of radial support stiffness between a housing and a bearing seated in the bearing seat. A damper sleeve is operatively coupled to the cylindrical portion of the squirrel cage through a fluid film to dampen relative radial motion between the damper sleeve and the squirrel cage. A radial spring component is operatively connected to a side of the damper sleeve radially opposite the cylindrical portion of the squirrel cage to provide a second level of radial support stiffness.

Abstract: An exemplary method of lubricating a turbomachine interface includes, among other things, securing a carrier relative to a torque frame using a flexure pin, and lubricating an interface of the flexure pin using a lubricant that has moved through a lubricant passage in the carrier and a lubricant passage in the flexure pin.

Abstract: The present disclosure relates to a hot section gas turbine engine component assembly and a method for forming such.

Abstract: Aspects of the disclosure are directed to a system that includes a boot configured to attach to a chevron of an aircraft nacelle, and an attachment mechanism configured to attach the boot and the chevron. In some embodiments, a boot includes a first surface and a second surface, where the surfaces are attached by inwardly tapering sidewalls that form an opening that is configured to surround a chevron of an aircraft nacelle. In some embodiments, a repair of a chevron on an exhaust nozzle of an aircraft engine includes placing a chevron-shaped boot with a pocket over at least a portion of a chevron structure on an exhaust nozzle of an aircraft engine, the pocket having a shape that generally conforms to an external surface of the chevron, covering the portion of the chevron structure with the boot, and fastening the boot to the chevron through at least one of bonding or mechanical fastening.

Abstract: A front section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan hub. The fan hub includes a hub diameter supporting a plurality of fan blades including a tip diameter. A transitional entrance passage is configured to communicate flow between the fan section and a compressor section. The transitional entrance passage includes an inlet disposed at an inlet diameter and an outlet to the compressor section disposed at an outlet diameter. A method of designing a gas turbine engine is also disclosed.

Abstract: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.

Abstract: A method of recovering waste heat includes pressurizing a flow of working fluid and transferring heat from a hot gas stream to the flow of working fluid in at least two successively arranged heat transfer sections. At least some of the working fluid is converted to a superheated vapor by the transfer of heat, and passes through an expander to recover useful work. A portion of the flow of working fluid is directed along a branch after having passed through at least one of the heat transfer sections, and bypasses the expander and at least one of the heat transfer sections before being recombined with the working fluid that has passed through the expander. The total flow rate of working fluid can be adjusted to regulate the temperature of the hot gas stream downstream of the heat transfer sections, and the amount of fluid that bypasses along the branch can be adjusted to regulate the temperature of the superheated vapor.

Abstract: A system includes a heat recovery steam generator (HRSG) including a first pressure economizer, a first pressure evaporator that may receive a first portion of a feed water from the first pressure economizer at a first pressure, a re-heat section that may receive the first portion of the feed water from the first pressure economizer as a first steam flow, and a flash system including a first flash vessel that may receive a second portion of the feed water from the first pressure economizer and to generate a first flash steam flow. The system may combine the first flash steam flow with the first steam flow of the feed water at a second pressure less than the first pressure.

Abstract: A method of controlling a turbine of an exhaust heat recovery system in which heat of exhaust gas evaporates a working fluid through a heat exchanger provided in an exhaust pipe and the working fluid is supplied to the turbine may include measuring an internal temperature of the heat exchanger, and rotating the turbine in a reverse direction when the measured internal temperature is a predetermined temperature or less.

Abstract: An exhaust heat recovery system may a condenser having a working fluid introduced thereinto and recovering heat of the introduced working fluid, the introduced working fluid receiving heat of exhaust gas through a heat exchanger provided in an exhaust pipe, and a reservoir receiving the working fluid from the condenser, wherein the condenser and the reservoir are provided with a coolant channel through which a coolant for cooling the working fluid flows.

Abstract: Various embodiments relate to combined heat and power (CHP) systems. A CHP system can include a turbine system, a turbocharger system, and a refrigeration system. The refrigeration system can receive combustion products from the turbine system and compressed air from the turbocharger system. The refrigeration system can cool the combustion products and the compressed air to generate a cooled combustion product mixture that is provided to the turbine system.

Abstract: An exhaust heat recovery system includes an exhaust pipe through which exhaust gas exhausted from an engine moves, a heat exchanger mounted in the exhaust pipe and inducing heat exchange between the exhaust gas and a working fluid flowing therein, a plurality of reservoirs supplying working fluids to the heat exchanger, and channel adjusting valves allowing any one of the plurality of reservoirs to be in communication with the heat exchanger.

Abstract: At least one aspect of the technology provides a self-contained processing facility configured to convert organic, high water-content waste, such as fecal sludge and garbage, into electricity while also generating and collecting potable water.

Abstract: An adjustable camshaft can be used in valve drives of internal combustion engines, amongst other places. The adjustable camshaft may include an outer shaft and an inner shaft that is concentric with and rotatably supported in the outer shaft. A cam having a cam bore may be rotatably supported on an outer surface of the outer shaft so as to form a slide bearing gap between the cam and the outer shaft. The cam may be rotatably-fixed to the inner shaft so that the inner shaft and the cam rotate with one another. Furthermore, the adjustable camshaft may include an oil channeling groove disposed beneath the cam in the outer surface of the outer shaft. In many cases, at least one side of the oil channeling groove may be exposed such that it extends beyond the slide bearing gap and the cam.

Abstract: A method of precision manufacture of an outer arm of a rocker arm assembly is performed by determining structures of a rough outer arm that would require precision processing and locations to support the structures as they are processed. Starting with at least one structure requiring precision processing, locations on the outer arm close to the structure to hold the outer arm during processing are determined that would cause minimal distortion of the outer arm during processing. The outer arm is then provided with clamping lobes at these locations. The clamping lobes of the outer arm are clamping into a fixture for manufacturing. The slider pad may now be precision ground while the outer arm is clamped in the fixture with minimal risk of distortion of the outer arm.

Abstract: A method of remanufacturing a rocker arm having a body defining a contact surface is provided. The contact surface is configured to engage with a braking member and having a worn portion thereon. The method includes machining the contact surface to remove the worn portion and to form an opening configured to receive an insert member therein. The insert member includes an upper surface configured to engage with the braking member. The method further includes coupling the insert member to the opening.

Abstract: A variable valve lift system may include a roller finger follower having an end connected with a valve and a roller mounted thereto. A hydraulic lash adjuster supports another end of the roller finger follower and has operating modes which are changed to a high lift mode or a low lift mode according to supplied hydraulic pressure to change a height of the hydraulic lash adjuster. A hydraulic pressure supplying portion supplies the hydraulic pressure to the hydraulic lash adjuster. A cam is mounted to a camshaft and contacts the roller of the roller finger follower. The cam has a first ramp and a second ramp formed thereon.

Abstract: A novel cylinder head arrangement for an in-line four cylinder or eight cylinder engine. A modified arrangement allows additional space for installation of wider rocker arm assemblies used for variable valve lift (VVL), cylinder deactivation (CDA) and other types of variable valve actuation (VVA). In one embodiment, cam towers adjacent the end two cylinders are not used. At least one end support is used, which may be an outboard bearing on a camshaft for each end. The wider rocker assemblies may then be installed. In another embodiment, cam towers adjacent the inner two cylinders are eliminated and a single camshaft support piece with a support bearing is installed between the inner cylinders to provide support for the camshafts. The wider rocker assemblies may then be installed on at least one of the middle cylinders. A novel oil control valve operates latches in switching rocker arm assemblies.

Abstract: A variable valve lift apparatus that changes a lift of a valve in an engine may include an outer body selectively pivoting based on rotation of a cam, having a first end configured to be connected with a valve and a second end mounted with a pivot shaft, and having an internal space formed in the outer body, an inner body pivoting based on rotation of the cam, disposed in the internal space of the outer body, and having a first end rotatably connected to the first end of the outer body, a connecting shaft disposed through the first end of the outer body and the first end of the inner body and connecting the outer body and the inner body to each other, and a lost motion spring having a portion fixed to the outer body and another portion fixed to the inner body.

Abstract: An adjustable camshaft can be used in a valve drive of an internal combustion engine. The adjustable camshaft may include an inner shaft rotatably supported by and concentric with an outer shaft. A cam element may be rotatably supported on the outer shaft such that the outer shaft extends through a cam bore of the cam element. The cam element may be rotatably-fixed to the inner shaft, in some cases, by way of a bolt. Further, a bearing sleeve that is rotatably-fixed to the cam element may be inserted within the cam bore such that a slide bearing gap is formed between the bearing sleeve and the outer shaft. Furthermore, in some examples the cam element may be a collared cam that has a cam base body and a cam collar adjacent to one another.

Abstract: There is provided an internal combustion engine, provided with a crankshaft and one or several cylinders provided on the wall thereof with exhaust ports and closed at the top by a cylinder head provided with intake ports; each cylinder accommodating an engine piston connected to the crankshaft and a coaxial auxiliary piston opposite the engine piston, defining an intake chamber and a combustion chamber; said auxiliary piston axially determining on the side of the combustion chamber a housing that communicates with the intake chamber via transfer ports, the housing of which includes a secondary piston which opens and closes the transfer ports in a back-and-forth movement between a rear position and a forward position.

Abstract: A vehicle may include an internal combustion engine having a crankcase and a supercharging apparatus, and a crankcase ventilation apparatus having at least one oil-separating apparatus including at least one oil separator. An oil return line may communicate separated oil from the crankcase ventilation apparatus to the crankcase. An ejector pump may be driven via a compressed air flow of the supercharging apparatus and may be configured to generate an underpressure for driving a blow-by gas. The crankcase ventilation apparatus may include a pump control valve configured to at least one of regulate and control the compressed air flow through the ejector pump.

Abstract: An oil separator includes a housing into which mixed gas in which unburned gas and engine oil are mixed with each other is introduced from a crank case; a centrifuge mounted in the housing and generating centrifugal force to the mixed gas to thereby separate the engine oil from the mixed gas; and a filter separator mounted in the housing and filtering the engine oil in the mixed gas. Since the engine oil is primarily separated through the centrifuge and secondarily separated through the filter separator, engine oil separation efficiency is improved as compared to the related art, and the same amount of gas may be treated even with a small size as compared to the related art.

Abstract: The invention relates to an accessory gearbox (10) for a turbomachine, said gearbox being equipped with an air/oil separator (12) and comprising a casing (24) in which intermeshing pinions are mounted, one (18) of which is solidly connected to a coaxial shank (22) for driving at least one membrane filter (35) of the separator, characterised in that the membrane filter is mounted directly on a web of the pinion (18) inside the casing.

Abstract: An oil-separating device for crankcase ventilation of an internal combustion engine may include a hollow member that extends axially in a longitudinal axis and through which a gas flow charged with oil can flow. The gas flow may flow against an oil separation ring disposed within or formed in the hollow member. The hollow member may contain a substantially rotationally symmetrical flow guiding member that has a flow projection located in the longitudinal axis and that has a flow contour that radially increases in a downstream direction so that gas can flow around the flow guiding member and so that the gas flow between the flow contour and the inner side of the hollow member can strike the oil separation ring in an accelerated manner.

Abstract: An oil separator may be used in a variety of contexts, one of which is for crankcase ventilation of an internal combustion engine. The oil separator may include a hollow member that extends along a longitudinal axis and is configured to receive a gas flow that is charged with oil. The oil separator may also include an oil separation member disposed within the hollow member and against which the gas flow flows. A redirection member may be disposed proximate the oil separation member in the hollow member, wherein the redirection member redirects at least a portion of the gas flow traveling substantially along the longitudinal axis radially outwards so as to impact an inner side of the oil separation member. As a result of an impactor effect from the gas flow striking the oil separation member as well as the inertia of the oil, the oil may remain in and/or pass through the oil separation member.

Abstract: Methods and systems are provided for diagnosing a particulate filter located in an exhaust runner of an engine cylinder. In one example, a method may include flowing exhaust from a first cylinder through a first particulate filter in a first runner, and flowing exhaust from a second cylinder through a second particulate filter in a second runner. The method may further include adjusting engine operation in response to particulate filter degradation, the particulate filter degradation distinguishing between degradation of the first and second particulate filters based on an exhaust pressure pulsation timing relative to combustion events.

Abstract: An exhaust gas purification filter includes an inflow/outflow passage through which exhaust gas flows in/out, and a partition. The outflow passage and the inflow passage is alternately arranged. The partition is configured to divide the inflow passage and the outflow passage from each other, and being porous. The partition includes a coated zone where a surface of a base of the partition is covered with a first coating layer having an average pore diameter smaller than an average pore diameter of the base, and a non-coated zone where the surface of the base is not covered with the first coating layer on a downstream side of the coated zone. The average pore diameter of the base is large enough for ash to pass through the partition, and the first coating layer is constituted by a plurality of particle groups with different average particle diameters from each other.

Abstract: A device to trap and remove particulate matter from exhaust of internal combustion engines, without increasing resistance to the flow of engine exhaust is disclosed herein. The system is provided with a single or a plurality of ducts (1 & 2) through which exhaust gases enter tangentially into a hollow chamber (3), causing the gases to spin at high speeds. The spinning gases generate centrifugal force resulting in separation of particulate matter from the exhaust gases. The hollow chamber (3) contains ports (4) and radial projections (5) on its axial surface to allow the separated particulate matter to enter into a trap (6). The particulate matter entering the trap (6) gets stuck to a fine mesh of high temperature resistant porous material that may or may not be electrically charged. The trap (6) is enclosed in a cover (7) that encases the fine mesh which surrounds the ports (4) and radial projections (5).

Abstract: A urea backflow prevention apparatus of SCR in an SCR system which injects a urea solution into an exhaust pipe may include: a urea tank to store the urea solution; a nozzle to be installed in the exhaust pipe to inject the urea solution; a supply pump to pump the urea solution; a suction line connecting the urea tank to the supply pump; a pressure line connecting the supply pump to the nozzle; a return line connecting the supply pump to the urea tank to return un-injected urea solution back to the urea tank; and a backflow prevention line connecting the pressure line to the return line. The backflow prevention line keeps pressures of the pressure line, the supply pump directly connected to the pressure line and the suction line indirectly connected to the pressure line equal to an atmospheric pressure after an operation of the SCR system ends.

Abstract: The condensed water treatment device obtains (S1) the storage water quantity (QW) of a condensed water tank, and drains (S4) condensed water in the condensed water tank when the storage water quantity (QW) is larger than a threshold value (tu) and also urea water is supplied to an exhaust passage for a selective-reduction type NOx catalyst. Thereby, the condensed water is neutralized and then drained to the outside of an internal combustion engine through the exhaust passage.