Abstract: A method for building centrifugal radial stages of turbines, in which the first and the second end of each blade (4) are connected to respective two support rings (2, 3) joining, by means of laser welding, at least a first semi-portion (10) belonging to the respective end of the blade (4) to a respective second semi-portion (10) belonging to the respective support ring (2, 3) so as to form a resilient yielding connecting portion (10, 15) along a radial direction, and providing at least a stop portion (11) belonging to the end of the blade (4) facing, along the radial direction, at least a stop element (14) of the respective support ring (2, 3). The resilient yielding connecting portion (10, 15) enables the stop portion (11) to enter into contact with the stop element (14) when the stage (1) is subjected to the functioning loads of the turbine.

Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.

Abstract: An airfoil has an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure. A swirl structure is operatively associated with the cooling passage and configured to impart a tangential velocity to the cooling medium flowing through the cooling passage. An airfoil has an airfoil structure that defines a first cooling passage and a second cooling passage for directing cooling medium through the airfoil structure, each cooling passage having a swirl structure that imparts tangential velocity on the cooling medium flowing through the associated cooling passage. A method of making an airfoil that includes forming an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure and forming a swirl structure that is operatively associated with the cooling passage and imparts tangential velocity to the cooling medium flowing through the cooling passage.

Abstract: A turbine vane for a rotary turbomachine has a turbine blade delimited by a concave pressure-side wall and a convex suction-side wall which are connected in the region of a vane front edge which can be assigned to the turbine blade and enclose a cavity which extends in the longitudinal extent of the vane front edge and is delimited on the inner wall by the pressure-side wall and the suction-side wall in the region of the vane front edge and by an intermediate wall which extends in the longitudinal direction to the vane front edge and connects the suction-side wall and the pressure-side wall on the inner wall. The intermediate wall has a perforation at least in sections in the connecting region to the suction-side wall and/or pressure-side wall, in order to increase the elasticity of the intermediate wall.

Abstract: A rotor blade comprises a root section, an airfoil section, a leading edge cooling cavity, an intermediate cooling cavity, and a trailing edge cooling cavity. The leading edge, intermediate, and trailing edge cooling cavities each extend spanwise through the airfoil section from a coolant inlet passage in the root section, and each terminate proximate the airfoil tip.

Abstract: A cooling system according to an embodiment includes: a three-pass serpentine cooling circuit; and an air feed cavity for supplying cooling air to the three-pass serpentine cooling circuit; wherein the three-pass serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum and a first set of near wall cooling channels of a multi-wall blade.

Abstract: A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

Abstract: A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor.

Abstract: A workpiece manufactured from an additive manufacturing system (AMS) having a particle separator and a method of operating includes modeling the workpiece into layers and modeling the layers into a plurality of regions. The AMS then deposits one of a plurality of particle types into a respective one of the plurality of regions. In this way, the surface finishes of the component may be controlled and material densities from one region to the next and from one layer to the next are also controlled.

Abstract: A structural guide vane for use in a gas turbine engine has a leading edge section, a trailing edge, a pressure surface and a suction surface. An erosion coating such as polyurethane resin is on the pressure surface and the suction surface. The leading edge of the vane is without the erosion coating and is bare metal. The vane is formed to include a plurality of pockets and bond shelves in the pressure surface side, and an epoxy bond line on the bond shelves holding a cover plate protected by the erosion coating.

Abstract: Implementations of the present disclosure are directed to turbine assemblies for turbocharger systems. In some implementations, turbine housings include a body that defines an inlet for fluid communication with a fluid source, and a wall, the wall dividing the inlet into an inner inlet and an outer inlet, and a fluid guide assembly disposed within the housing, the fluid guide assembly including a plurality of vanes that demarcate an inner volute and an outer volute within the housing, the inner volute being in fluid communication with the inner inlet and the outer volute being in fluid communication with the outer inlet, each vane of the plurality of vanes being fixed at a respective angle relative to a radial direction, the plurality of vanes guiding fluid flow from the outer volute to the inner volute.

Abstract: A sealing assembly may include a support, an engine component, and a seal. The engine component may be mounted relative to the support to define a gap between the engine component and the support. The seal may be arranged between the support and the engine component to block gasses from passing through the gap. The seal may be adapted to compress and expand to fill the gap during expansion and contraction of the adjacent components that occurs during operation of a gas turbine engine including the sealing assembly.

Abstract: A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.

Abstract: A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct.

Abstract: A guide blade for a gas turbine is disclosed. The guide blade includes a blade leaf having a receptacle in which at least one sealing element is arranged, where the sealing element is movable relative to the blade leaf between a sealing setting, in which the sealing element is at least partially moved out of the receptacle, and a storage setting, in which the sealing element is moved back into the receptacle. The guide blade further includes at least one fluid channel by which fluid under pressure can be routed into the receptacle in order to move the sealing element from the storage setting into the sealing setting. An inlet opening of the fluid channel is formed on a pressure-side surface of the blade leaf. A housing as well as a gas turbine having at least one guide blade is also disclosed.

Abstract: A power turbine unit includes a turbine housing, an exhaust duct, a turbine wheel with blades positioned in the exhaust duct, a shaft rigidly connected to the turbine wheel and rotatably supported in the housing, and an oil sealing system. The oil sealing system includes a sealing arrangement positioned in the vicinity of the turbine wheel for preventing oil from escaping from the turbine housing along the shaft to the exhaust duct. The oil sealing system further includes a buffer gas duct that is arranged to supply exhaust gas from the exhaust duct to the sealing arrangement for pressurizing the sealing arrangement.

Abstract: A fluid seal structure of a heat engine including a steam turbine includes an inner case which houses a turbine rotor rotatably inside, an outer case which houses the inner case and forms a space through which a fluid can flow between the outer case and an exterior surface of the inner case, a protruding portion protruding into the space from one of the exterior surface of the inner case or an interior surface of the outer case, and a partitioning plate extending into the space from the other one of the exterior surface or the interior surface and being formed annularly in a circumferential direction of the surface. The partitioning plate partitions the space into first and second space sections, and is flexurally deformable in the axial direction of the turbine rotor by an internal fluid pressure difference between the first and second space sections.

Abstract: A method, including receiving a turbine system operating parameter. The turbine system operating parameter includes an indication of a frequency variation of an electric power system associated with the turbine system. The method includes determining a correction factor to vary the output of the turbine system according to the frequency variation, wherein the correction factor is based on a droop power response and a nominal droop power ratio. The droop power response is calculated based on a gas turbine power output and a speed-load error. The method further includes varying the output of the turbine system based at least in part on the correction factor.

Abstract: An improved system, apparatus and method for controlling vane angles in a gas turbine engine, and more specifically, for correcting vane angle error in a gas turbine engine. An active synchronization ring comprises a plurality of micro-actuators coupled to the synchronization ring to correct distortion in the synchronization ring. The micro-actuators apply a bending moment to the synchronization ring to cancel or compensate for synchronization ring distortion. The micro-actuators may be controlled open loop or closed loop. Strain sensors measure ring distortion and provide signals to the controller for closed loop control.

Abstract: A sensor assembly is described herein. The sensor assembly includes a housing that includes an inner surface that defines a cavity within the housing, and a proximity sensor positioned within the cavity. The proximity sensor includes a first connector, a second connector, and a substantially planar sensing coil that extends between the first connector and the second connector. The sensing coil extends outwardly from the first connector such that the second connector is radially outwardly from the first connector.

Abstract: Assemblies and methods for monitoring turbine component deformation are provided. An assembly includes a first strain sensor configurable on the turbine component, the first strain sensor including at least two reference points and having a first dimension. The assembly further includes a second strain sensor configurable on the turbine component, the second strain sensor including at least two reference points and having a first dimension which corresponds to the first dimension of the first strain sensor. An initial value of the first dimension of the second strain sensor is different from an initial value of the first dimension of the first strain sensor. In accordance with another embodiment of the present disclosure, a method for monitoring turbine component deformation is provided.

Abstract: The present disclosure provides methods and systems for in situ cleaning of hot gas flowpath components of a turbine engine that form portions of a hot gas flowpath extending through the turbine. The hot gas flowpath components may include a layer of accumulated contaminants on first portions thereof that form a respective portion of the hot gas flowpath. The first portions may include a thermal battier coating (TBC), and the layer of accumulated contaminants may overlie the TBC and at least partially infiltrate into the TBC. The accumulated contaminants may include CaO—MgO—Al2O3-SiO2 (CMAS) partial melt. The methods may include introducing an acid-including detergent into the hot gas flowpath of the turbine engine and onto the hot gas flowpath components to clean the accumulated contaminants from the first surfaces of the components.

Abstract: A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine. The compression rod may transmit loads between halves of the core cowl. The spring may cause the plunger to extend and contract in response to vibrations or other relative movement between halves of the core cowl.

Abstract: Embodiments of the present disclosure provide cooling systems for turbomachinery and methods of installation. In an embodiment, an apparatus of the present disclosure can include a ventilation conduit for routing a cooling air from a compressor of a power generation system to a turbine component of the power generation system; and a nozzle in fluid communication with the ventilation conduit, wherein the nozzle delivers water from a water supply into the ventilation conduit.

Abstract: A bypass engine bearing holder (1) that holds an upstream bearing (6) and defines, with said upstream bearing, an oil chamber (100) and an air chamber (200), comprising a frusto-conical portion (11) defining an upstream bearing chamber (160) and a downstream inner chamber (150), and includes an outer collar (13) connected, by a weld (135), to a flange (15) that extends outward from the frusto-conical portion (11). The outer collar (13) has a sealable gimlet (131) engaging with the upstream bearing (6) such as to seal the oil chamber (100). The bearing holder (1) includes a plurality of oil recovery ducts (8) leading to the downstream inner chamber (150) and to the upstream bearing chamber (160). The oil recovery ducts (8) lead to the upstream bearing chamber (160), downstream from the weld (135) of the outer collar (13) on the flange (15), the weld (135) of the outer collar (13) being axisymmetric.

Abstract: A gas turbine engine is provided including a shaft coupling a compressor of a compressor section to a turbine of a turbine section. An aft bearing assembly, including at least two bearings, is positioned at least partially in an aft sump and supports the shaft within the turbine section. The aft sump is configured to receive lubrication oil from a lubrication oil supply extending through at least a portion of a turbine center frame of the turbine section, and provide such lubrication to the at least two bearings of the aft bearing assembly.

Abstract: A lubricating fluid damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation and a radial aperture, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a lubricating fluid jet configured to propel a lubricating fluid through the radial aperture toward the contact portion.

Abstract: A shaft for a gas turbine engine includes a shaft bore along an axis, a circumferential groove within the shaft bore, a multiple of first axial grooves from said circumferential groove and a multiple of second axial grooves from said circumferential groove.

Abstract: A method includes controlling a bearing fluid supply system to provide the bearing fluid to a hydrostatic bearing of the turbopump assembly. The bearing fluid includes a supercritical working fluid. The method also includes receiving data corresponding to a pressure of the bearing fluid measured at or near a bearing fluid drain fluidly coupled to the hydrostatic bearing, determining a thermodynamic state of the bearing fluid at or near the bearing fluid drain based at least in part on the received data, and controlling a backpressure regulation valve to throttle the backpressure regulation valve between an opened position and a closed position to regulate a backpressure in a bearing fluid discharge line to maintain the bearing fluid in a supercritical state in the hydrostatic bearing and/or at or near the bearing fluid drain.

Abstract: A waste heat recovery apparatus, for use with an internal combustion engine, includes a working fluid circuit to circulate working fluid, a boiler connected on the working fluid circuit and adapted to recover waste heat from a source to heat working fluid, an expander connected on the working fluid circuit to receive working fluid from the boiler, and, a heating jacket associated with the expander. The working fluid circuit downstream of the boiler includes a first branch connecting to an inlet of the expander and a second branch connecting to the heating jacket. A valve is connected on the working fluid circuit to selectively control working fluid flow to one of the first branch for expansion and recovering work or to the second branch to heat the expander responsive to a temperature of the working fluid.

Abstract: A waste heat recovery system (100) for an engine (101) comprises a fluid supply (104); one or more evaporators (120, 121) adapted to transfer waste heat from the engine (101) to fluid from the fluid supply (104) to heat the fluid to a superheated vapor; a condenser (134) having a condenser inlet (134?) in fluid communication with the one or more evaporators; and a pressure regulator (200) configured to limit the vapor pressure at the condenser inlet (134?).

Abstract: A valve train for a reciprocating piston internal combustion engine with a transmission element in the form of a rocker arm (1) or pivot arm that can be actuated, on one hand, at least indirectly by a cam of a camshaft and is in active connection, on the other hand, through an intermediate connection of a valve bridge (4), with gas-exchange valves (7, 8). The valve bridge (4) has hydraulic valve lash compensation elements (“HVAs”) allocated to each gas-exchange valve (7, 8).

Abstract: A valve timing control device for an internal combustion engine includes: a driving rotation member; a driven rotation member fixed to a cam shaft; an electric motor; a speed reduction mechanism; a power feeding brush; and a power feeding plate which is provided to the driving rotation member, and which includes a slip ring on which the power feeding brush is abutted, the power feeding plate including a rigidity plate portion whose outer circumference portion is fixed to the driving rotation member, and a resin portion formed by molding an outer surface of the rigidity plate portion, and the rigidity plate portion including a holding hole which holds the power feeding brush through the resin portion, and being integrally formed with a reinforcement portion which is formed at a portion except for the holding hole, and which extends in a radially inward direction.

Abstract: A valve timing controller includes: an outer rotor; an inner rotor relatively rotating inside of the outer rotor; a torsion coil spring having a fixed end connected with the inner rotor, and a free end connected with the outer rotor; and a bush rotor coaxially projected from the outer rotor or the inner rotor to support the torsion coil spring in a radial direction. The torsion coil spring biases the inner rotor while being connected with the outer rotor by being torsionally deformed according to a relative rotation of the inner rotor to the outer rotor. A load acting from a first turn of the torsion coil spring adjacent to the free end is smaller than a load acting from a wound part of the torsion coil spring between the first turn and the fixed end.

Abstract: An iron-based alloy includes (in weight percent) carbon from about 1 to about 2 percent; manganese up to about 1 percent; silicon up to about 1 percent; nickel up to about 4 percent; chromium from about 10 to about 25 percent; molybdenum from about 5 to about 20 percent; tungsten up to about 4 percent; cobalt from about 17 to about 23 percent; vanadium up to about 1.5 percent; boron up to about 0.2 percent; sulfur up to about 0.03 percent; nitrogen up to about 0.4 percent; phosphorus up to about 0.06 percent; niobium up to about 4 percent; iron from about 35 to about 55 percent; and incidental impurities. The chromium/molybdenum ratio of the iron-based alloy is from about 1 to about 2.5. The alloy is suitable for use in elevated temperature applications, such as valve seat inserts for combustion engines.

Abstract: The present invention teaches a method and apparatus to quickly and inexpensively implement advanced, bypass grade, fine, or additional filtration to engines and hydraulic systems using any filter media through a single conduit means. The present invention has the ability to make quick hydraulic connection to the engine or hydraulic system, where oil is super cleaned, without major modifications as is the paradigm by traditional bypass filtration systems and without removing any lubricant from the engine or system that the present invention is connected to, as is the paradigm of traditional bypass filtering systems.

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 exhaust gas aftertreatment device for a combustion engine is disclosed. The device includes an exhaust pipe element having an exhaust duct through which exhaust gas of the combustion engine is flowable and a dosage device which opens into the exhaust duct at a feed point, where the dosage device is configured to introduce a reduction agent into the exhaust pipe element at the feed point. A baffle is arranged in the exhaust duct which divides the exhaust duct at least partially into a first passage and a second passage where the first and second passages have a respective inlet opening and are fluidically arranged in parallel. The feed point is disposed in the first passage and is shielded from the second passage by the baffle where the inlet opening of the second passage is disposed upstream of the feed point.

Abstract: A method for reducing reductant deposits in an exhaust conduit fluidly coupled to an engine comprises operating the engine to produce an exhaust gas. The exhaust gas is communicated into the exhaust conduit which has an initial cross-sectional area. An initial flow rate corresponding to an initial flow velocity of the exhaust gas entering the exhaust conduit is determined. The initial flow rate and, thereby the initial flow velocity of the exhaust gas, increases or decreases based on an operating condition of the engine. The initial flow rate of the exhaust gas is compared with a predetermined threshold. If the initial flow rate of the exhaust gas is lower than the predetermined threshold, a cross-sectional area of the exhaust conduit is reduced. The reducing of the cross-sectional area causes the exhaust gas to have an adjusted flow velocity greater than the initial flow velocity.

Abstract: The present invention relates to a mounting mat for mounting a pollution control device in a catalytic converter, the mounting mat comprising a non-woven mat of inorganic fibers having distributed therein inorganic particles having an average diameter of 1 nm to 100 nm and wherein the mounting mat is free of organic binder or contains organic binder in an amount of not more than 5% by weight, based on the total weight of the mounting mat. The invention further relates to a pollution control device including the mounting mat and to a method of making the mounting mat.

Abstract: An exhaust gas purifying device includes a honeycomb catalyst body, a plugged honeycomb structure and a can member to receive therein the honeycomb catalyst body and the plugged honeycomb structure, and the plugged honeycomb structure disposed at a position on a downstream side of the honeycomb catalyst body is designed so that a pressure loss in an end face central region of at least one of a second inflow side end face and a second outflow side end face of a second honeycomb substrate is larger than a pressure loss of an end face circumferential region positioned around the end face central region.

Abstract: The present techniques are directed to a system and methods for operating a gas turbine system. An exemplary gas turbine system includes an oxidant system, a fuel system, and a control system. A combustor is adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas. A catalyst unit including an oxidation catalyst that includes an oxygen storage component is configured to reduce the concentration of oxygen in the exhaust gas to form a low oxygen content product gas.

Abstract: Systems are provided for a mixer configured to be used in either an intake or exhaust passage. In one example, a mixer in the intake passage may be adapted to mix EGR with intake air and a mixer in the exhaust passage may be adapted to mix urea with exhaust gas.

Abstract: Methods and systems are provided for controlling a vehicle engine to adjust exhaust warm-up strategy based on a vehicle network information. In one example, in response to an expected decrease in temperature of a catalyst of a vehicle below a threshold and an estimated duration thereof based on communications external from the vehicle, a method may include delaying catalyst heating actions, when the catalyst heating actions are determined to be unable to heat up the catalyst to threshold temperatures. However, the catalyst heating actions may be enabled when the catalyst heating actions are determined to be able to achieve the threshold temperature within the duration.

Abstract: A method is provided for monitoring an emission device coupled to an engine. In one example approach, the method comprises: following a deceleration fuel shut-off duration, indicating degradation of the emission device based on an amount of rich products required to cause a sensor to become richer than a threshold. The amount of rich products required may be correlated to an amount of oxygen stored in the emission device.

Abstract: Methods and systems are provided for sensing particulate matter in an exhaust system of a vehicle. An example system comprises a particulate matter sensor inside a tube configured to receive a portion of exhaust gas in an exhaust passage.

Abstract: An automatically stoppable internal combustion engine comprises an exhaust purification catalyst, an upstream side air-fuel ratio sensor, a downstream side air-fuel ratio sensor, and sensor heaters heating air-fuel ratio sensors. A controller comprises an air-fuel ratio control part and a heating control part. The heating control part controls the temperature of the upstream side air-fuel ratio sensor to the activation temperature or more and the temperature of the downstream side air-fuel ratio sensor to less than the activation temperature during automatic stop of the internal combustion engine. The air-fuel ratio control part controls the air-fuel ratio of the exhaust gas based on the outputs of the two air-fuel ratio sensors during engine operation and controls the air-fuel ratio of the exhaust gas temporarily based on the output of the upstream side air-fuel ratio sensor without using the output of the downstream side air-fuel ratio sensor.

Abstract: A vehicle comprising an engine having a cylinder block, a cylinder head and a gasket disposed between the cylinder block and the cylinder head. The cylinder block and the cylinder head each comprising at least one bore opening leading to a casting bore within the cylinder block and cylinder head respectively. The gasket comprising a gasket opening having a control gap, said gasket opening being sized and arranged to provide a fluid pathway between the bore opening in the cylinder block and the bore opening in the cylinder head. The control gap being configured and arranged to selectively restrict that fluid pathway such that gas may freely pass through the cylinder block bore opening and into the bore opening in the cylinder head whereas coolant can only restrictively pass through the cylinder block bore opening and into the bore opening in the cylinder head.

Abstract: A control method for a vehicle provided with a water-cooling intercooler apparatus, includes: detecting a coolant temperature of the water-cooling intercooler apparatus; detecting a rotation speed and a power consumption amount of an electric water pump (EWP) included in the water-cooling intercooler apparatus; calculating an efficiency value of the water-cooling intercooler apparatus based on the detected coolant temperature and air temperatures at an inlet and an outlet of an intercooler, respectively, included in the water-cooling intercooler apparatus; and determining whether the water-cooling intercooler apparatus is in a failure state based on the detected coolant temperature, the detected rotation speed and power consumption amount, and the calculated efficiency value.

Abstract: A first valve portion and a second valve portion are formed in a rotary valve, wherein the first and the second valve portions are arranged in an axial direction thereof. The first valve portion includes a first and a second valve windows formed in a valve member, and a first and a second valve port openings formed in a valve housing. The second valve portion includes a third valve window formed in the valve member and a third valve port opening formed in the valve housing. The valve member is rotatable in both directions of a clockwise direction and an anti-clockwise direction, so that each of the first to the third valve port openings is respectively opened or closed by the first to third valve windows. Each of the valve windows and the valve port openings of the first valve portion is formed in a rectangular shape in its developed figure in a rotational direction of the valve member.