Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a platform lip extending axially from the platform portion; and a plurality of voids disposed along a surface of the platform lip.

Abstract: A component includes a component body that is configured for use in a gas turbine engine. The component body includes first and second structural segments that are bonded to each other in at least one diffusion joint. The first and second structural segments are formed of, respectively, first and second materials. The first and second materials are different base-metal alloys, a metallic alloy and a ceramic-based material, or ceramic-based materials that differ by at least one of composition and microstructure.

Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.

Abstract: A rotating blade for use in a turbomachine is disclosed. In an embodiment, the rotating blade includes an airfoil portion, a root section affixed to a first end of the airfoil portion, and a tip section affixed to a second end of the airfoil portion, the second end being opposite the first end. A part span shroud is affixed to the airfoil portion between the tip section and the root section, wherein the part span shroud further comprises a hollow portion, wherein the hollow portion is devoid of any coupling structure therein.

Abstract: A coating, a coated turbine component, and a coating process are disclosed. The coating includes an epoxy-polyamide structure formed from a coating composition comprising a phenolic resin and a curing agent, the phenolic resin comprising a bisphenol F constituent and an epichlorohydrin constituent. The coating composition is solvent-free or substantially solvent-free. The cured coating is cross-linked from curing below 120° C., from curing using infrared-microwave radiation, or a combination thereof. The coated turbine component includes a surface and the coating. The coating process includes applying the coating and curing the coating.

Abstract: An article includes a substrate, a substantially hermetic sealing layer disposed on the substrate, and a porous transition layer disposed on the substrate between the sealing layer and the substrate. The article also includes one or more openings extending through the substrate to the porous transition layer.

Abstract: A system, in particular a turbocharger with a barrier layer for protecting against high temperature corrosion of parts and/or components of the system or turbocharger that are subjected to high temperatures, where the barrier layer includes at least one Cr—Al—O layer.

Abstract: A gas turbine engine includes an engine static structure that has a fluid port. A turbine vane is supported relative to the engine static structure and includes a cooling passage. A flow splitter is provided between the engine static structure and the turbine vane. The flow splitter is configured to divide a flow upstream from the flow splitter into a first fluid flow provided to the fluid port and a second fluid flow provided to the cooling passage.

Abstract: A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform.

Abstract: A method of retrofiting a multi-stage partial arc or admission steam turbine and a steam turbine obtainable by the method. The method comprises forming at least one inlet belt in the inner housing downstream of at least one the first blade rows of the steam turbine and forming a duct, connecting the first inlet line and the or each inlet belt. The duct and the inlet belt are adapted to enable a steam to pass through the first inlet line and bypass the first blade row of the steam turbine and the connection of the duct to the first inlet line is such that all steam flowing through the first inlet line passes through the duct.

Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge flow in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a shank portion extending radially inward from the platform portion; at least one angel wing extending axially from a face of the shank portion; a platform lip extending axially from the platform portion, the platform lip disposed radially outward from the at least one angel wing; and a plurality of turbulators disposed along and extending outward from the face of the shank portion between the platform lip and the at least one angel wing.

Abstract: A vane seal system includes a non-rotatable vane segment that has an airfoil with a pocket at one end thereof. The pocket spans in an axial direction between forward and trailing sides, with respect to the airfoil, and in a lateral direction between open lateral sides. A seal member extends in the pocket. The seal member includes a seal element and at least one spring portion that is configured to positively locate the seal member in the axial direction in the pocket. A method for positioning the seal member in a vane seal system includes positively locating the seal member in the axial direction in the pocket using the spring portion.

Abstract: A sealing arrangement has a turbine static structure with contact surfaces, a bearing compartment with contact surfaces, and a cavity between the turbine static structure and the bearing compartment. There are also two seals, wherein each seal is configured to contact the turbine static structure and the bearing compartment.

Abstract: According to one embodiment of the present invention, a sealing arrangement includes a turbine static structure with an inner case and a seal ring each having contact surfaces. The sealing arrangement also has a bearing compartment with a contact surface. A piston seal is positioned between the inner case, the seal ring, and the bearing compartment and is configured to contact the contact surfaces.

Abstract: The present disclosure includes feather seals for use in gas turbine engines. The feather seals may be used in stationary components such as vanes or blade outer air seals. The feather seals may include stiffening elements, such as round or ovoid dimples, to improve the stiffness of the feather seals.

Abstract: An airfoil module may have an outer diameter ring assembly, a vane assembly having a stator vane and an inner diameter ring assembly. The outer diameter ring assembly and the inner diameter ring assembly may be arranged concentrically with the stator vane of the vane assembly extending between them. The inner diameter ring assembly may have a first inner diameter ring section sealing end and a second inner diameter ring section sealing end. A feather seal may be disposed along the first inner diameter ring section sealing end. A stator ring assembly may comprise multiple airfoil modules arranged in an annulus. The outer diameter ring assemblies may be joined together by brazing or welding, or may share a unified outer diameter ring assembly. The inner diameter ring assemblies may abut feather seals so that the airfoil modules may expand and contract independently along the inner diameter ring assemblies.

Abstract: An example seal includes, among other things, a plug body to limit flow through an axially extending interface between a first component and a second component, the plug body to flow when positioned within both a cavity of the first component and a cavity of the second component.

Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes a shim seal including multiple seal plates forming a box shaped shim seal. The box shaped seal includes a plurality of cuts at two opposing sides or corners for allowing high pressure fluid to occupy the cavity of the box-shaped shim seal. The seal may be inserted within one or more slots between adjacent stator components of the rotary machine.

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal between the mate face of the first engine component and the mate face of the second engine component. The seal establishes three points of contact with each mate face in at least one condition.

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including an engine case, a retention block attached to the engine case, and a blade outer air seal (BOAS). The BOAS includes a plurality of layers formed of a ceramic matrix composite (CMC) material. At least one of the plurality of layers provides a slot receiving a portion of the retention block.

Abstract: A laminate seal assembly, disposed on a stator seal portion and opposite a rotor seal portion of a gas turbine engine comprises a first honeycomb layer having a first edge which engages the rotor portion and a second edge distal from said rotor seal portion, a plurality of honeycomb cells extending between the first edge and the second edge, an intermediate seal plate having a first material surface and a second material surface, the first material surface disposed against the second edge of the first honeycomb layer, a low conductivity structure disposed on the second surface, and a backing plate disposed on against said low conductivity structure, wherein the stator portion may be tuned for thermal growth to match the thermal growth of the rotor portion.

Abstract: A first actuator moves a compressor rotor and compressor blades along a rotational axis of the compressor rotor. A turbine rotor includes a plurality of turbine blades each extending radially outwardly from the turbine rotor to an outer tip. A turbine housing surrounds each of the turbine blade tips. The turbine housing has an inner surface, and a turbine tip clearance is defined between each of the turbine blade tips and the inner surface of the turbine housing. A second actuator moves the turbine rotor and the turbine blades along a rotational axis of the turbine rotor. A control controls the first actuator of the compressor rotor, and the second actuator of the turbine rotor to control the compressor tip clearance and the turbine tip clearance.

Abstract: The present disclosure includes active clearance control systems including improved cooling manifolds. Such improved manifolds may utilize multiple cooling zones to provide varied levels of cooling to an engine case.

Abstract: Apparatus to enable rotation of a compressor, the apparatus comprising: a guide for insertion through a fan of a gas turbine engine to the compressor, the guide including: a surface arranged to guide a drive assembly through an interior portion of the gas turbine engine to the compressor; and a first fastener arranged to fasten the guide to the gas turbine engine.

Abstract: A system and device to prevent damage during over-speed condition in a turbo-machine. In one embodiment, the system includes a fluid circuit with a header, which couples to the turbo-machine, and a hydraulic circuit through which fluid evacuates the header to a drain during the over-speed condition. The hydraulic circuit includes a trip header manifold with a pilot element in flow connection with a drain valve element having an actuator to regulate flow of fluid from the header. For example, the pilot element uses a pair of solenoid valves to change pressure of a fluid in the drain valve element and maintains the actuator in a first position to prevent fluid evacuation during normal operating conditions. When over-speed condition is detected, the solenoid valves change state, reducing the pressure of the fluid, permitting the actuator to move to a second position placing the header in flow connection with the drain.

Abstract: The present invention relates to an adjustable guide vane for a turbomachine, having a vane element (1) and a turning disk (2, 3), which has a first impact chamber (4), in which an impulse element (5) is arranged with play of movement.

Abstract: A disclosed lubrication system for turbofan engine includes a primary lubricant circuit, a primary pump driving lubricant through the primary circuit, an auxiliary lubricant circuit in communication with the primary lubricant circuit and an auxiliary lubricant pump driving lubricant through the auxiliary lubricant circuit. A first valve downstream of an outlet of auxiliary lubricant pump separates the auxiliary lubricant circuit from the primary lubricant circuit. A sensor is disposed within the auxiliary lubricant circuit for sensing pressure within the auxiliary lubricant circuit separate from a pressure within the primary lubricant circuit.

Abstract: A method for assembling a section of a gas turbine engine is disclosed. The method involves aligning a vane ring with a first rotor hub such that a row of vanes on the vane ring is adjacent a first row of blades of the first rotor hub, and aligning a second rotor hub with the vane ring such that a second row of blades of the second rotor hub is adjacent the row of vanes and the row of vanes is axially between the first row of blades and the second row of blades. The first hub and the second hub are then non-mechanically bonded together.

Abstract: Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterised in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.

Abstract: A centering arrangement includes a ring-like inner part and a ring-like outer part, whereby the outer part surrounds the inner part in a concentric arrangement and with an interspace established between the outer part and the inner part, and whereby the outer part and the inner part are subject to a differential radial expansion. A centering contact element, procures a centering mechanical contact between the outer part and the inner part at a plurality of circumferentially distributed contact points, and is able to deform in order to compensate for differential radial expansion.

Abstract: The quatro generation system of the present invention includes: a power generation engine driven by fuel gas; an exhaust-heat boiler configured to utilize energy of exhaust gas discharged from the power generation engine to produce steam from boiler water; a boiler-water circulation device configured to supply the steam produced by the exhaust-heat boiler to a steam-energy recovery unit, and to return condensed water of the steam to the exhaust-heat boiler after the steam-energy recovery unit recovers energy of the steam; a condensation economizer configured to utilize condensation latent heat of exhaust gas discharged from the exhaust-heat boiler to heat a heat medium; and a heat-medium circulation device configured to supply the heat medium heated by the condensation economizer to a thermal-energy recovery unit, and to return the heat medium to the condensation economizer after the thermal-energy recovery unit recovers energy of the heat medium.

Abstract: A pushrod assembly for an engine is disclosed. The pushrod assembly may include a first piece configured to house a hydraulic lash adjuster and a second piece coupled to the first piece. The first piece may include a mating portion with a tapered end section. The second piece may include a first bore adapted to receive the mating portion of the first piece.

Abstract: A switching rocker arm according to one example of the present disclosure includes an outer arm, an inner arm, a latch and a sleeve. The inner arm can be pivotally secured to the outer arm and have a latch bore. The latch can have a distal end portion and a proximal end portion. The distal end portion can include a latch flat. The sleeve can be one-piece and have a sleeve body that defines a sleeve bore having a sleeve flat. The latch can be received by the sleeve body. The latch flat can be keyed to the sleeve flat.

Abstract: A hydraulic camshaft adjuster (1) with a stator (2) in which a rotor (3) is rotatably arranged. A vane (4) which protrudes radially outwards is provided on the rotor (3), the vane being provided with a pressure chamber delimiting side (7). A pressure chamber supply groove (10) is arranged so as to extend on a separation plane which separates the rotor (3) into two halves in order to supply a hydraulic medium to a pressure chamber formed by the rotor (3) and the stator (2), the pressure chamber supply groove (10) having an outlet (11) in the pressure chamber delimiting side (7) of the vane (4).

Abstract: The present invention relates to an exhaust valve of a diesel engine for a large ship, containing a shall part and an umbrella part that are integrated with each other and made of an Ni—Cr—Al system Ni-base age-precipitated alloy, in which the exhaust valve has a layered structure and hardness of 600 HV or less as a whole, and the layered structure contains a layer formed of an ?-Cr phase having a thickness of 150 nm or more that is aged beyond peak mechanical strength.

Abstract: The present disclosure provides an engine valve actuation system comprising: a camshaft, with a plurality of cams: a control shaft one; a control shaft two; and a plurality of valve actuation units, each unit further comprising: (i) at least one set of an engine valve and an engine-valve return spring; (ii) an lost-motion module, further comprising a collapsible high-pressure chamber, and operably converting the profile of the one of the cams and the collapsing motion from the high-pressure chamber to corresponding movement of the at least one engine valve; and (iii) a hydraulic circuit, further comprising: a trigger valve one and a trigger valve two, being controlled respectively by the control shaft one and the control shaft two.

Abstract: A motor control apparatus for adjusting a cam phase includes a motor control part, which controls a current supplied to a stator coil by controlling plural switching elements forming an inverter to turn on and off. The motor control part stops the current supplied to the stator coil each time a motor rotates a predetermined rotation angle interval in a power generation control mode, in which a rotation torque is generated in a direction to impede the motor rotation. The motor control part maintains the power generation control mode when a rotation signal is determined as varying in a predetermined time period. The motor control part switches over an operation mode to a normal control mode to generate a rotation torque in a direction to promote the motor rotation when the rotation signal is determined as not varying in the predetermined time period.

Abstract: A supply pump includes a housing that has a tappet receiving chamber, which receives a plunger drive mechanism, and oil for lubricating respective lubricating portions of the plunger drive mechanism is temporarily retained in the tappet receiving chamber. In the housing, a communication hole opens in an inner peripheral wall surface of a tappet guide and guides the oil from a tappet upper side chamber into a tappet lower side chamber at the time of upwardly moving a tappet.

Abstract: A thermal management unit for a vehicle powertrain includes an integrated oil heater, a control valve, and a pressure relief valve. A remote oil cooler is connected to fluid ports of the thermal management unit. Transmission oil is received into the thermal management unit and is directed to one or both of the transmission oil heater and the transmission oil cooler. A portion of the flow of oil can be internally bypassed through the pressure relief valve to maintain the pressure of the oil below a threshold. The flow of oil is directed through the control valve after having been heated and/or cooled, and the proportions of oil being directed through the oil heater and the oil cooler are determined by the temperature of the oil in the control valve.

Abstract: An oil filter for an engine is in the form of a reservoir mounted in an oil pan having a closed interior volume and an open top edge spaced from an adjoining oil pan sidewall and positioned to receive oil with entrained debris as the oil flows by gravity after being centrifugally flung radially outward from the moving engine components. The debris separates from the oil in the reservoir, with clean oil overflowing the top edge of the wall for recirculation in the engine.

Abstract: A power system may include a first generator configured to be connected to at least one other generator. Each generator may be configured to be connected to a bus. The bus may be connected to at least one load. The first generator includes a controller that operates the first generator and determines a need to regenerate a diesel particulate filter in the first generator. The controller communicates the need to regenerate the diesel particulate filter to the at least one other generator.

Abstract: There is disclosed a honeycomb structure including a honeycomb structure body, and a pair of electrode members disposed on a side surface of the honeycomb structure body, an electric resistivity of the honeycomb structure body is from 1 to 200 ?cm, each of the pair of electrode members is formed into a band shape extending in a cell extending direction of the honeycomb structure body, and in a cross section orthogonal to the cell extending direction, one electrode member is disposed on a side opposite to the other electrode member via a center of the honeycomb structure body, and in the honeycomb structure body, one or more specific slits each having an open end in the side surface are formed.

Abstract: A device for providing a liquid additive for exhaust-gas purification, having at least one duct for conducting the liquid additive, the duct having a duct wall which has a first stiffness. There is inserted into the duct an insert component (5) that extends at least in sections along the duct, wherein the insert component is composed of a solid material.

Abstract: An incorrect or wrong diagnosis in abnormality diagnosis of a sensor is suppressed. Provided at the downstream side of an NOx selective reduction catalyst is a sensor which detects NOx and ammonia in an exhaust gas flowing out of the NOx selective reduction catalyst, and in which the NOx and the ammonia react with each other. An amount of decrease in an output of the sensor due to a reaction of the NOx and the ammonia in the sensor is calculated based on the NOx and the ammonia flowing out of the NOx catalyst, and an abnormality diagnosis of the sensor is carried out based on this amount of decrease in the output of the sensor.

Abstract: An object of the present invention is to provide an exhaust system component having excellent properties to be located in an exhaust flow path from an internal combustion engine, particularly, an exhaust system component having an extended use-life. The exhaust system component of the present invention for an internal combustion engine has a self-healing ceramic material and an electric heater for heating the self-healing ceramic material. In particular, the exhaust system component of the present invention is an oxygen sensor having a detection element and an electric heater, wherein the detection element has a solid electrolyte layer, a reference-side electrode layer, an exhaust-side electrode layer, and a diffusion layer and/or a trap layer each composed of a self-healing ceramic material.

Abstract: An exhaust gas purification device having such a structure that exhaust gas can uniformly flow into without depending on a shape of an exhaust gas inlet pipe. A gas purification body which purifies the exhaust gas, a purification casing which accommodates the gas purification body, an exhaust gas inlet pipe which communicates with an exhaust gas inflow port of the purification casing, and an exhaust gas outlet pipe which communicates with an exhaust gas outflow port of the purification casing. The exhaust gas inlet pipe is attached to the purification casing in such a manner as to cover the exhaust gas inflow port and extend in a longitudinal direction of the purification casing. An introduction passage of the exhaust gas is formed by an outside surface of the purification casing and an inside surface of a pipe wall of the exhaust gas inlet pipe.

Abstract: A fluid delivery system includes a flow agitator connected to a gas conduit and disposed within an internal cavity of the conduit at an upstream location with respect to a fluid injector. The flow agitator operates to separate the gas flow passing through the conduit during operation into a bypass flow, a control flow, and a main flow, such that a recombination of the bypass flow, the control flow, and the main flow downstream of the flow agitator creates an oscillation in the gas flow that also encompasses the fluid delivered into the internal cavity by the injector.

Abstract: An exhaust aftertreatment system may include an exhaust gas passageway and a mixer assembly. The exhaust gas passageway may receive exhaust gas output from a combustion engine. The mixer assembly may be disposed along the exhaust gas passageway and may receive the exhaust gas. The mixer assembly may include a mixer housing, a mixing bowl and an injector housing. The mixing bowl may be disposed within the mixer housing and may include an outer diametrical surface that engages an inner diametrical surface of a wall of the mixer housing. The injector housing may extend through the wall and into an aperture in the mixing bowl. The aperture may define a flow path through which at least a majority of the exhaust gas entering the mixer assembly flows. The mixing bowl may include an upstream end portion having contours directing the exhaust gas toward the injector housing.

Abstract: In one embodiment, an exhaust waste heat recovery system includes a first exhaust waste heat recovery assembly including a central exhaust channel configured to allow passage of exhaust along an exhaust axis, and a first plurality of thermoelectric (TE) legs, each of the first plurality of TE legs including a hot end in thermal communication with the exhaust channel, and a cold end opposite to the hot end, and an electrical coupler in electrical communication with each of the first plurality of TE legs, the electrical coupler configured to receive electricity from the first plurality of TE legs.

Abstract: An apparatus includes an exhaust aftertreatment component. According to various embodiments, the exhaust aftertreatment component is any of a diesel oxidation catalyst, a diesel particulate filter, a decomposition reactor tube, a selective catalytic reduction device, and a reductant injector assembly. The apparatus also includes a ceramic thermal barrier coating applied to a surface of the exhaust aftertreatment component. The surface may, for example, be an outer wall of a housing of the exhaust aftertreatment component.