Abstract: A centrifugal compressor includes an impeller and a casing. The casing includes a scroll part forming a scroll flow passage on a radially outer side of the impeller and a diffuser part forming a diffuser flow passage for supplying the scroll flow passage with compressed air compressed by the impeller. The diffuser part includes: a first diffuser portion belonging to a first angular range including an angular position of a tongue section of the scroll part, of an angular range in a circumferential direction of the impeller; and a second diffuser portion belonging to a second angular range downstream of the first angular range in a flow direction of the scroll flow passage, of the angular range in the circumferential direction of the impeller, the second diffuser portion having an outer radius R2 which is defined along a reference circle centered at a rotational center of the impeller.

Abstract: A turbine vane for a gas turbine engine incorporating a ceramic matrix composite airfoil is disclosed in this paper. The turbine vane includes an attachment unit configured to mount the ceramic matrix composite airfoil to other metallic components of the turbine vane.

Abstract: A sealing system (100) for a turbomachine is provided which includes a support (10) designed as a ring part, and a ring-like sealing plate (20, 30) that protrudes from the support in the axial direction (X). The support includes a fastening section (11) for fastening the sealing system to a stator part (200), and a retaining area (12), situated radially within the fastening section, for retaining a radial gap seal (40). The sealing plate (20, 30) is welded to the support (10) radially outside the retaining area (12). Also provided are a turbomachine that includes a sealing system (100), a support (10) for a sealing system, and a method for manufacturing a sealing system.

Abstract: A seal member assembly structure and assembly method, a seal member, and a gas turbine, wherein, in a state where first flange parts provided on a combustor transition piece are fitted into first fitting parts provided in seal members, protruding parts provided on the first flange parts are inserted into recessed parts provided in the first fitting parts.

Abstract: A labyrinth seal system comprises a knife element and a stator element, the knife element having a plurality of teeth radially extending from a base and the stator element having a radially inner surface configured to interact with the plurality of teeth to create a seal. The knife element is axially constrained by and rotationally coupled to a turbine component, but has a degree of freedom in the radial direction with respect to that component.

Abstract: An assembly includes a monolithic carrier structure and a seal assembly. The monolithic carrier structure includes a carrier base and a support ring. The carrier base extends axially along the centerline. The support ring projects radially inward from the carrier base. The seal assembly is nested radially within the carrier base and axially next to the support ring. The seal assembly includes a seal base, a plurality of spring elements and a plurality of seal shoes arranged about the centerline in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes with the seal base.

Abstract: A method for assembly of a rotor of a gas turbine with a housing and a channel which diverges in a direction of flow includes axially displacing the rotor in the direction of flow. Then, an outer sealing ring whose minimum inside diameter is smaller than the maximum outside diameter of the rotor is axially displaced in the direction of flow.

Abstract: Aspirating face seal between high and low pressure regions of turbomachine between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces, starter tooth mounted on the rotatable member operable to sealingly engage abradable starter seal land on the non-rotatable member, and annular pocket in an abradable coating or other abradable material of starter seal land. Abradable material may be in radially inwardly facing groove extending into non-rotatable member. Pocket may extend radially outwardly from a cylindrical radially outer abradable surface to pocket bottom which includes thin abradable material layer groove surface along the non-rotatable member. Pocket may extend axially aftwardly from annular forward groove side surface into abradable coating. Pocket may be bounded axially by abradable material. Pocket may be tapered having taper decreasing axially aftwardly away from annular forward groove side surface.

Abstract: The present invention discloses a turbine engine with at least a high pressure and a low pressure turbine section comprising a casing and at least one turbine blade rotatably mounted within the casing wherein at least part of the inner surface of the casing is covered with shrouds as abradables to provide clearance control between the inner surface and the tip of the at least one blade and wherein the tip of the blade is coated G with a hard PVD coating, characterized in that the shroud material of at least the high pressure and/or the low pressure section comprises a porous ceramic based material and the hard PVD coating on the tip of the blade essentially consists of a droplet free nitride coating.

Abstract: A clearance control arrangement (26) for a rotor (28), the arrangement comprising a rotor and a casing (32) radially outside the rotor. An annular array of segment assemblies (33) mounted to the casing and radially spaced from the rotor by a clearance (42). Each segment assembly comprising a heat transfer cavity (48) radially adjacent to the casing. A birdmouth cavity (66) towards the rear of the segment assembly. A bypass hole (68) configured to deliver air to the birdmouth cavity to reduce the amount of air which leaks from the heat transfer cavity to the birdmouth cavity.

Abstract: A clearance control arrangement (26) for a rotor (28) comprising a segment assembly (33) spaced radially inwards from a casing (32) and defining a radial clearance (42) between the rotor (28) and the segment assembly (33). A front carrier (35a) and a rear carrier (35b) supporting the segment assembly (33). A heat transfer cavity (48) formed between the carriers (35a, 35b), the segment assembly (33) and the casing (32). A settling chamber (60) formed adjacent to the casing (32) and upstream of the heat transfer cavity (48). The clearance control arrangement (26) is configured to receive air into the settling chamber (60) and thence to deliver it to the heat transfer cavity (48).

Abstract: This disclosure provides assemblies for providing a bumper between an exhaust frame and a bearing housing in a gas turbine. The bumper or bumpers have an attachment surface for attaching to the exhaust frame and a bearing contact surface that engages the bearing housing during a blade out event.

Abstract: A turbine blade maximum vibration response prediction method for predicting a maximum vibration response acting on a plurality of turbine moving blades provided along the circumferential direction of a turbine rotor includes the steps of: gaining, before turbine operation start, prior response data that is distribution data on vibration response of all the turbine moving blades for each turbine operating condition; gaining, by using the prior response data, operation response data that is distribution data on the vibration response of all the turbine moving blades during the operation of the turbine; and predicting, from the operation response data, the turbine moving blade of all the turbine moving blades on which the maximum vibration response is acting, and the magnitude of the maximum vibration response.

Abstract: A cooling system for a turbine engine includes a structure defining a fluid passageway. The fluid passageway includes an impingement surface. A first opening into the fluid passageway is also included. The first opening is disposed opposite the impingement surface of the fluid passageway such that airflow entering the fluid passageway impacts the impingement surface. An agglomerate retention structure is disposed on the impingement surface. The agglomerate retention structure holds particulates impacting the impingement surface entering through the opening. A turbine engine is also disclosed.

Abstract: A turbine may include a blade coupled to a rotor, a vane upstream from the blade and coupled to a vane support that defines a metering hole, and a blade outer air seal disposed radially outward from the blade and downstream from the vane support. An impingement surface may be disposed between the vane support and the blade outer air seal. The impingement surface may be oriented at an angle to the metering hole of between 50 degrees and 5 degrees.

Abstract: A turbine assembly may comprise a platform defining a platform cavity cooled by a platform flow with a vane extending from the platform. A platform-fed through cavity is defined by the vane and cooled by a first portion of the platform flow. A direct-fed through flow cavity is defined in the vane and cooled by a direct-fed through flow. The direct-fed through flow cavity and the platform-fed through cavity meet at an outlet to expel an outgoing through flow from the outlet. A platform-fed serpentine cavity may be defined in the vane and separated from the platform-fed through cavity by a divider. The platform-fed serpentine cavity is cooled by a second portion of the platform flow.

Abstract: A system includes a gas turbine engine, including a compressor, a combustor, and a turbine. The system includes an intercooler configured to receive a discharge air from the compressor and to cool the discharge air. The system includes a first conduit to divert a portion of the cooled discharge air from the intercooler or a location downstream of the intercooler to a bearing located within the turbine to pressurize the bearing to block leakage of fluid from the bearing.

Abstract: A turbine shroud segment forms part of a circumferentially segmented shroud assembly surrounding a circumferential array of turbine blades of a gas turbine engine. The turbine shroud segment has a platform extending axially from an upstream end portion to a downstream end portion relative to a flow of gas through the gas turbine engine. A heat shield extension projects radially inwardly and in an upstream direction from the upstream end portion of the platform.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine component and a lubrication system. The lubrication system directs lubricant through the turbine engine component. The lubrication system includes a wash flow filter.

Abstract: A compressor includes a rotor platform; a rotor blade; and a casing having an inner surface surrounding the tip and spaced radially outwardly from the tip to define a gap. A secondary air flow system includes a bleed inlet configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit. The bleed inlet and plenum at least partially define a secondary air flow path such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit.

Abstract: The invention relates to a turbine center frame for an aircraft gas turbine, with a plurality of first components and a plurality of second components, which, in the peripheral direction, are arranged alternately next to one another and, in a radial direction, bound a flow duct conveying hot gas, wherein the first components each have two first overlapping segments and the second components each have two second overlapping segments with a respective region of the transitioning from a first component to a second component or vice versa, a first overlapping segment and a second overlapping segment are arranged overlapping, and with at least one centering element, at which the first components and the second components are supported along the peripheral direction and in a radial direction with the first components and the second components essentially centered with respect to a central axis of the turbine center frame.

Abstract: An apparatus and method for a turbine engine comprising an outer casing having a first surface and defining an axial centerline and an inner casing located within the outer casing and having a second surface spaced. The first and second surfaces are spaced from each other and define an annular channel between where a combustion air flows in a fore to aft direction along a profile.

Abstract: A turbine center frame for a gas turbine having a plurality of first components and a plurality of second components alternately mutually adjacently disposed in circumferential direction and bounding a hot gas-conducting flow channel in radial direction, the first components each having two first overlapping portions, and the second components each having two second overlapping portions. In a transition from a first component to a second component, one of the first overlapping portions and one of the second overlapping portions overlap. A centering element, against which, the first components and the second components are braced along the circumferential direction and in the radial direction, centers the first components and the second components relative to a central axis of the turbine center frame.

Abstract: A compliant mounting adapter for mounting an engine to a test stand includes: a body having: a first mounting interface configured for being coupled to the test stand; a second mounting interface configured for being coupled to the engine, the second mounting interface spaced-away from the first mounting interface; and a spanning element interconnecting the first and second mounting interfaces. The body is sufficiently flexible so as to permit movement relative movement of the two mounting interfaces, in response to forces generated by engine operation, in at least two degrees of freedom, and has a predetermined stiffness in each of the at least two degrees of freedom, with the predetermined stiffness of each degree of freedom being substantially independent from the stiffness of the other degrees of freedom.

Abstract: Provided is a consumer to industrial scale renewable energy-based quintuple-generation systems and energy storage facility. The present invention has both mobile and stationary embodiments. The present invention includes energy recovery, energy production, energy processing, pyrolysis, byproduct process utilization systems, separation process systems and handling and storage systems, as well as an open architecture for integration and development of additional processes, systems and applications. The system of the present invention primarily uses adaptive metrics, biometrics and thermal imaging sensory analysis (including additional input sensors for analysis) for monitoring and control with the utilization of an integrated artificial intelligence and automation control system, thus providing a balanced, environmentally-friendly ecosystem.

Abstract: A system and method for active draft control through a combined cycle power plant (CCPP) can initiate a CCPP shutdown, activate the recirculated exhaust gas (REG) system for the turbomachine; measure a HRSG airflow through the HRSG; communicate the HRSG airflow to a controller configured to condition a control signal; and adjust a recirculated exhaust gas volume in accordance with the control signal.

Abstract: In a first embodiment, a system includes a turbine system including turbomachinery, one or more processors, and a memory storing instructions. When executed by the one or more processors, the instructions are configured to cause the one or more processors to receive an operating parameter of the turbomachinery, and calculate a risk of failure for the turbomachinery based at least in part on an asset failure mode model. The instructions are also configured to cause the one or more processors to categorize the risk of failure as a selected failure indicator category of a plurality of failure indicator categories, and output the selected failure indicator category.

Abstract: A supercritical fluid power system comprises: a power cycle loop (10) filled with a supercritical fluid working substance and comprising a first pressure container (11), a second pressure container (12), and a driven portion (13) disposed between the two pressure containers; and a hot source (20) and a cold source (30), wherein the hot source (20) is used to provide thermal energy to a working substance in one pressure container, and the cold source (30) is used to cool the working substance in another pressure container, so as to form a pressure difference between the two pressure containers. The working substance flows between the two pressure containers under the effect of the pressure difference and flows to the driven portion (13) to provide power to the driven portion (13). For this power system, a pressure difference is cyclically produced between the two pressure containers, thereby implementing recycling of power.

Abstract: The invention relates to a system for recovering thermal energy produced in pyrometallurgical process plants and converting said thermal energy into electrical energy. The system is characterised in that it comprises at least one heat transfer chamber (1) comprising a gas interface section (1A), for separating the subsystem from the corrosive power of, and incrustation generated by, the gases from the heat source or duct (5). The system also comprises a section (1B) for connecting to a Stirling engine (2), which is a thermal engine and which, by means of the cyclical compression and expansion of a gaseous working fluid, at different temperature levels, produces a net conversion of thermal energy into mechanical energy.

Abstract: This exhaust cam shaft (2) is provided with a shaft part (5) and cam parts (6 to 13) provided on the outer circumference of the shaft part (5). The shaft part (5) has holes (16, 17, 19) opened at predetermined positions on the outer circumferential surface of the shaft part (5). The holes (16, 17, 19) are formed so as to be gradually tapered from an outside of the shaft part (5) toward a center of the shaft part (5) in a radial direction.

Abstract: An improved cam follower for a vehicle engine includes a body, a spring seat, a tower, a spring and an anti-rotation member. The body defines a body diameter, a first open end, and a second end. The spring seat includes a spring seat opening and an interlock portion. The spring seat may be affixed to the first open end of the body. The spring seat further includes a spring seat diameter wherein the spring seat diameter is greater than the body diameter. The tower may be disposed in a pin housing through the spring seat opening at the first open end of the body. The tower further includes an upper flange and a spring which abuts the upper flange at a first spring end. The second spring end abuts the spring seat. The anti-rotation member accordingly may be coupled to the body via the spring seat.

Abstract: A variable valve train module selectively controls the opening and closing of a valve of an engine. The variable valve train module includes a drive element configured to be driven by a cam which rotates on a camshaft, a pump which is driven by the drive element, and a hydraulic control unit. The hydraulic control unit is configured to control the engine valve. The hydraulic control unit has a high pressure chamber containing hydraulic fluid which is selectively pressurized by the pump. The hydraulic control unit also has a control valve which is configured to depressurize the high pressure chamber, and a damper which is configured to increase an effective volume of the high pressure chamber when a pressure in the high pressure chamber exceeds a threshold value.

Abstract: The invention relates to a cooled inlet or outlet valve (4) for internal combustion engines, comprising a valve disc (6), a valve stem (8), and a hollow space (10) inside the valve stem (8) and the valve disc (6). A coolant (12) is arranged in the hollow space (10). The valve is designed comprising at least two parts and has on a valve disc surface (22) an opening (18) which is closed by a cover (20), wherein the cover (20) is additionally provided with at least one relief groove (34) which relieves a joint (32) between the opening (18) in the valve disc surface (22) and the cover (20).

Abstract: A two-cycle internal combustion engine with rear compression chamber, other than that of a crank case. This present engine has valves that can be screwed on the engine block near top dead center, and is actuated by air pressure. This present two-cycle engine yet uses an oil sump similar to that of a four-cycle engine, which eliminating the need to premix oil with the fuel. This present engine has a stationary piston which operates within a movable piston to form a rear-compression chamber. The movable piston has ports near its crown to transfer charge to the combustion chamber. The movable piston also has ports near bottom of its skirt to allow the fuel and air mixture to enter the rear compression chamber. This engine has a piston seat which is adapted to connect the movable piston to the connecting rod.

Abstract: A hydraulic pressure supply system includes: a mechanical oil pump; an electric oil pump; an electric motor that drives the electric oil pump; a control device that controls the operation of the electric oil pump by manipulating a power-supply voltage or a power-supply current to the electric motor; a check valve that is installed at an upstream position relative to a junction pipe of an outlet-side pipe of the mechanical oil pump and an outlet-side pipe of the electric oil pump; and a hydraulic pressure measurement circuit that measures a hydraulic pressure of the outlet-side pipe of the electric oil pump.

Abstract: The hydraulic piston (1) constitutes a hydraulic chamber (5) with a cylinder (4) and has a cylindrical body (6) connected—from the side of the chamber (5)—by a link-stop valve (3) to a cooling and lubricating gasket valve (2) which is passed right through by a flow calibration opening (27), the valve (2) being able to move in longitudinal translation over a short stroke with respect to the body (6) or to be held at a distance from the body (6) by the valve link-stop (3), a valve return spring (30) tending to move the valve (2) away from the cylindrical body (6).

Abstract: The oil circulation system of an internal combustion engine comprises: a high temperature side oil circulation path provided with a high temperature side oil pan, a high temperature side part supplied with oil, and a heating part, and circulating oil among these; a low temperature side oil circulation path provided with a low temperature side oil pan and a low temperature side part supplied with oil, and circulating oil between the low temperature side oil pan and the low temperature side part supplied with oil; an oil transport mechanism transporting oil between the low temperature side oil circulation path and the high temperature side oil circulation path; and a control device configured to control transport of oil by the oil transport mechanism while the internal combustion engine is operating.

Abstract: An oil circulation system of an internal combustion engine comprises a first oil pan and second oil pan, first oil supplied parts supplied with oil stored in the first oil pan, second oil supplied parts supplied with oil stored in the second oil pan, and a heating part. The heating part has oil paths through which oil flows and heats the oil flowing through the oil paths. The oil circulation system comprises a first circulation path circulating oil through the first oil pan, heating part, and first oil supplied parts, and a second circulation path circulating oil between the second oil pan and the second oil supplied parts.

Abstract: A device for reciprocatingly removing and replenishing fluid in circulating system of an hydraulic mechanism that includes at least two processing tanks, at least one air pressure regulator and connector releasably engageable with a pressurized air source, at least one vacuum generator, at least one pressure regulator; and means for removing the fluid from the circulating system at vacuum.

Abstract: Systems and methods for an exhaust system for a gas turbine engine are provided. The method includes: receiving a primary exhaust fluid in a primary manifold; receiving a secondary cooling fluid in a secondary plenum; directing the primary exhaust fluid through a plurality of eductor primary flow paths associated with a respective plurality of ducts spaced circumferentially about a primary manifold, the plurality of eductor primary flow paths extending through the secondary plenum; and mixing the primary exhaust fluid and the secondary cooling fluid in a mixing chamber associated with a respective one of the plurality of ducts to create a mixed fluid flow.

Abstract: A fine particle detector includes an antenna, an electromagnetic wave generator configured to supply electromagnetic waves to the antenna, an electromagnetic wave detector configured to detect reflected waves of the electromagnetic waves emitted from the antenna, and a controller configured to estimate, based on intensities of the reflected waves detected by the electromagnetic wave detector, an accumulated amount of fine particles.

Abstract: An exhaust gas after-treatment unit for an internal combustion engine, particularly for a motor vehicle, includes a first selective catalytic reduction (SCR) catalytic converter through which the exhaust gas from the internal combustion engine can flow and at least one particle filter for retaining the soot particles from the exhaust gas, The particle filter, which is located downstream from the first SCR catalytic converter, is equipped with a heavy metal and precious metal free catalyzing coating which oxidizes the soot particles retained by the particle filter, where downstream from the particle filter there is a second SCR catalytic converter through which the exhaust gas can flow.

Abstract: An evaporative emission control canister system comprises an initial adsorbent volume having an effective incremental adsorption capacity at 25° C. of greater than 35 grams n-butane/L between vapor concentration of 5 vol % and 50 vol % n-butane, and at least one subsequent adsorbent volume having an effective incremental adsorption capacity at 25° C. of less than 35 grams n-butane/L between vapor concentration of 5 vol % and 50 vol % n-butane, an effective butane working capacity (BWC) of less than 3 g/dL, and a g-total BWC of between 2 grams and 6 grams. The evaporative emission control canister system has a two-day diurnal breathing loss (DBL) emissions of no more than 20 mg at no more than 210 liters of purge applied after the 40 g/hr butane loading step.

Abstract: An exhaust purification system includes an LAF sensor provided in an exhaust pipe and generates a signal corresponding to an air-fuel ratio of exhaust gas. An upstream catalytic converter is downstream of the LAF sensor and has a catalyst to purify the exhaust gas. An O2 sensor is downstream of the upstream catalytic converter, and generates a signal corresponding to the air-fuel ratio of the exhaust gas. A GPF is downstream of a the O2 sensor and purifies the exhaust gas. An ECU controls an air-fuel mixture in an engine using output signal KACT of the LAF sensor and an output signal VO2 of the O2 sensor such that the air-fuel ratio of exhaust gas flowing into the GPF converges to a target value near the stoichiometric ratio. The GPF has a filter substrate and a downstream TWC supported by a partition of the filter substrate.

Abstract: Exhaust gas systems and method for controlling the same are provided. Systems include a hydrolysis catalyst device (HCD) in fluid communication with an exhaust gas conduit, a turbocharger turbine disposed downstream from the HCD and in fluid communication therewith via the conduit, a selective catalytic reduction device (SCR) disposed downstream from the turbine and in fluid communication therewith via the conduit; and a reductant injector configured to inject reductant into the conduit upstream from the HCD. The HCD can comprise TiO2, V2O5, A12O3, and SiO2. Methods can include injecting reductant upstream from turbine, such as while the SCR is below a NOx light-off temperature and/or a reductant decomposition temperature. The system can further include a second reductant injector configured to inject reductant into the conduit at a second injection location downstream from the turbine and upstream from the SCR, and the method can include injecting reductant via the second injector.

Abstract: Provided is a nanofiber vent device for a urea water tank including a filter unit for discharging gas generated in the tank main body and preventing external dust, foreign matter, and moisture from flowing into the tank main body, as a vent device that is installed in a tank main body storing urea water and discharging gas inside the tank main body to the outside.

Abstract: In an embodiment of the present disclosure, a gas turbine engine includes a fan, a first compressor stage and a second compressor stage, a first turbine stage and a second turbine stage, and wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as part of a low spool, and a gear train driving said fan with said low spool, and such that said fan and said first compressor stage rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool.

Abstract: A catalyst arrangement for use with a selective catalytic reduction system includes a frame and a plurality of catalyst elements coupled to the frame. The plurality of catalyst elements is arranged vertically among a plurality of vertical stations. The plurality of vertical stations is successively defined along a height of the catalyst arrangement. The catalyst elements of at least one of the vertical stations are arranged at a plurality of axial positions with respect to an axial direction of a flow of exhaust gases through the selective catalytic reduction system.

Abstract: A mat material including: inorganic fibers; and an oily fiber-scattering inhibitor attached to a surface of the inorganic fibers, wherein the amount of the fiber-scattering inhibitor attached is 0.05 to 2.0% by weight, and the mat material has an odor index of 80 or less as a relative value determined by an odor sensor from the odor of decomposed gas generated when the mat material is placed on a 500° C. hot plate, when the odor index of a mat material to which 1.0% by weight of an acrylic resin as a fiber-scattering inhibitor is attached is taken as 130.

Abstract: A heat exchanger includes an introduction path and a discharge path. The introduction path introduces the heating medium to upstream portions of heating medium passages. A length of the introduction path along a third direction is reduced gradually from an upstream end portion of the introduction path towards a downstream end portion of the introduction path. The discharge path discharges the heating medium to an outlet portion. A length of the discharge path along the third direction increases gradually from a first portion towards a second portion. The first portion is disposed downstream of the upstream end portion of the introduction path in the flow direction, and the second portion is disposed downstream of the downstream end portion of the introduction path in the flow direction.