Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

Abstract: The present disclosure is directed to a rotor blade that includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a cooling core in fluid communication with the cooling passage. The cooling core includes a first cooling channel and a second cooling channel. The first cooling channel is radially spaced apart from the second cooling channel. Coolant flows in a first direction through the first cooling channel and in a second direction through the second cooling channel. The first direction is different than the second direction.

Abstract: An apparatus and method for cooling an engine component such as an airfoil can include an outer wall separating a cooling fluid flow from a hot flow. A cooling circuit can be provided in the engine component including a cooling passage having at least one pin within the cooling passage with a chevron shape and a non-uniform configuration.

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.

Abstract: Disclosed is a gas turbine engine component, and a method for forming the component. The component includes a first portion, a second portion formed separately from the first portion, and an intermediate layer provided between the first portion and the second portion.

Abstract: An assembly for a turbine engine comprises a circumferential band defining an air flow path, a component having a leading edge and extending from the band into the flow path, and a trough located in a surface of the band along the leading edge.

Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately ?0.067 to +0.101 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.

Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an assembly axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. A retention clip has an intermediate portion connecting a first leg portion and a second leg portion. The intermediate portion is compressible to position the first and second leg portions in the pair of airfoil openings such that the retention clip limits movement of the airfoil relative to the first shroud.

Abstract: A nozzle box assembly includes steam inlets, through which working steam is supplied, a torus part connected to the steam inlets so as to form an annular steam path and having an opening portion, in which a part of the front surface of the annular steam path is opened, a bridge ring connected to the front surface of the torus part and having a bridge inside, and a steam path ring connected to the bridge ring so as to provide a path, which is connected to a stage, and provided with a plurality of vanes, wherein the bridge ring and the steam path ring are formed of the coupling of a plurality of divisions, which are divided in the circumferential direction thereof, and the divisions are coupled to the front surface of the torus part.

Abstract: A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.

Abstract: A method for cooling a component of a gas turbine engine includes flowing a cooling airflow through a cooling passage of a turbine rotor blade, wherein the cooling passage includes an inlet and an outlet formed on a blade tip of the turbine rotor blade. The method further includes receiving at least a portion of the cooling airflow exiting the outlet of the cooling passage with an aperture defined in a casing of the gas turbine engine, wherein the casing is spaced from the blade tip along the radial direction. In addition, the method includes providing the cooling airflow received with the aperture defined in the casing to the component of the gas turbine engine through a coolant duct assembly of the gas turbine engine.

Abstract: A turboshaft engine has a principal rotational axis and comprises a power turbine, tail bearing housing, and exhaust collector arranged in axial flow series along the axis. The tail bearing housing has radially central region defining flow chamber for cooling air, and an annular duct defined around the central region and which forms at least part of exhaust flow passage for the flow of exhaust gases from the power turbine to the exhaust collector. The flow chamber is provided in fluid communication with the exhaust collector via at least one exhaust port formed in the tail bearing housing such that the flow of exhaust gases along the exhaust collector during operation of the engine educes flow of cooling air through the central flow chamber by drawing air through the or each exhaust port and into the exhaust collector.

Abstract: A device for influencing the temperatures in inner ring segments of a gas turbine is provided, which includes in the circumferential direction of the gas turbine, at least one outer shell assembly having a plurality of outer ring segments and at least one inner shell assembly having a plurality of inner ring segments. The inner ring segments are equal to or greater in number than the outer ring segments. An outer ring segment gap is between each two adjacent outer ring segments. An inner ring segment gap is between each two adjacent inner ring segments. An outer ring segment gap, or at least a radial cooling air passage, is located opposite each inner ring segment gap in the radial direction of the gas turbine.

Abstract: A variable turbine geometry (VTG) turbocharger is disclosed. The VTG turbocharger may comprise a turbine section having a turbine wheel and plurality of guide vanes configured to regulate a flow of exhaust gases to the turbine wheel. The VTG turbocharger may further comprise an actuation pivot shaft (APS) configured to mediate actuation of opening and closing of the guide vanes, a bushing rotatably supporting the APS with a clearance therebetween, and a radial seal circumscribing the APS and inserted in a cavity of the bushing. The radial seal may form an interference fit with both an outer diameter of the APS and an inner diameter of the bushing to seal a leakage of the exhaust gases between the clearance between the APS and the bushing.

Abstract: The invention concerns a conical hula seal wherein an inner part of the conical hula seal is closer to a conical hula seal longitudinal axis than an outer part of the conical hula seal, and wherein the conical hula seal extends in a circumferential direction relative to the conical hula seal longitudinal axis. A gas turbine which includes the conical hula seal is also disclosed, along with a method of operating a gas turbine which includes a conical hula seal that seals a gap between a first vane and a picture frame, the method including purging the gap with a cooling fluid.

Abstract: A seal assembly for sealing a fluid passageway from contaminants is disclosed. The fluid passageway is formed by a rotating shaft entering an opening in a housing. The fluid passageway connects an interior of the housing, and any exterior of the housing. The seal assembly includes a first sealing member and a second sealing member, which divides the fluid passage into an interior section, an open section, and a sealed section. The interior section is exposed to the interior of the housing. The sealed section is fluidly sealed between the interior section and the open section. A sensor is disposed within the sealed section. The sensor is configured to sense the contaminants within the sealed section and is electronically coupled to a controller configured to send an alarm signal. The sensor is a moisture sensor and extends into an annular recess formed in the stationary member.

Abstract: The present invention relates to a turbine engine comprising a wheel, (2) mounted on a shaft (4), and a disk (18), adjacent to the wheel (2) and mounted on the same shaft while being rotated by the latter. The disk (18) is made of a material having a density greater than that of the material used to manufacture the wheel (2). The invention is of use in a compressor/turbine.

Abstract: A turbocharger includes a turbine housing. The turbine housing includes an interior surface defining a turbine housing interior. The interior surface extends between a turbine housing inlet and a turbine housing outlet. The turbine housing also includes a wastegate duct disposed between the turbine housing inlet and the turbine housing outlet and defining a wastegate channel in fluid communication with the turbine housing inlet and the turbine housing outlet. The turbocharger also includes a valve seat and wastegate assembly including a valve movable between a first position and a second position. The turbocharger further includes a diffuser at least partially surrounding the valve seat for uniformly diffusing the flow of exhaust gas into the turbine housing outlet.

Abstract: A turbine engine compressor includes a stator featuring an annular casing and at least one annular row of variable-pitch vanes, wherein each vane comprises a radially external end having a pivot mounted in an orifice in the casing and connected by a linking member to an control ring capable of pivoting axially in relation to the casing, where the linking member comprises a first end fixed to the pivot of the vane and a second end having a pin inserted in a hole in the control ring, where at least one of the holes in the control ring serves for insertion of the pins of the linking members, is oblong in shape and extends in the circumferential direction in order to allow movement of the pin in the oblong hole, during rotation of the control ring.

Abstract: A vane arm may comprise a first end having a first surface and a second surface opposite the first surface. A vane stem aperture may be formed through the first end of the vane arm. The first surface may define a first perimeter of the vane stem aperture. The second surface may defines a second perimeter of the vane stem aperture. The second perimeter may comprise a circular or elliptical shape. A first wedge face and second wedge face may define a portion of the vane stem aperture.

Abstract: A drive system of a gas turbine engine includes at least one drive shaft operable to rotate within the gas turbine engine, a phonic wheel coupled to the at least one drive shaft, a speed sensor operable to detect rotation of the phonic wheel indicative of rotation of the at least one drive shaft, and a processing system coupled to the speed sensor. The processing system is operable to detect a phonic wheel pulse train indicative of rotation of the at least one drive shaft via the speed sensor, determine a torsional mode of the at least one drive shaft based on the phonic wheel pulse train, and record one or more trends of the torsional mode indicative of a health status of the drive system.

Abstract: A combustion system can include: a liner defining a combustion chamber; a casing covering the combustion chamber; a first tube disposed in the liner; a machined union disposed inside the casing and connected to the first tube; a second tube passing through the casing and connected to the machined union; a sensor housing disposed outside the casing and connected to the second tube; and an infinite tube connected to the sensor housing.

Abstract: A rotor includes a rotor hub, a plurality of blades mounted in a circumferentially-spaced arrangement on the rotor hub and a plurality of platform segments circumferentially arranged, respectively, between neighboring ones of the blades. The platform segments include core gas-path defining surfaces and are mounted with a freedom to circumferentially move relative to the neighboring ones of the blades.

Abstract: A turbomachine of bypass type comprising a nacelle defining a fan duct with an interduct. The turbomachine comprises at least one compartment created in the thickness of the interduct or of the nacelle. The compartment is separated from the fan duct by a cold wall and comprises at least one heat-sensitive element. The compartment further is equipped with a ventilation assembly comprising at least one ventilation opening made in the cold wall in order, in use, to cause air from the fan duct to enter the compartment. Each ventilation opening comprises a passive-opening system arranged in the compartment, the system comprising a flap able to move between an open position in which the flap uncovers the opening and a closing-off position in which the flap closes off the opening, and a passive-actuation device of the flap for moving the flap between the two positions.

Abstract: A method for selective aluminide diffusion coating removal. The method includes diffusing aluminum into a substrate surface of a component to form a diffusion coating. The diffusion coating includes an aluminum-infused additive layer and an interdiffusion zone. The diffusion coating is solution heat treated at a temperature and for a time sufficient to dissolve at least a portion of the interdiffusion zone. Thereafter the aluminum-infused additive layer is selectively removed. An aluminide diffusion coated turbine component is also disclosed.

Abstract: Described is a shaft support system for a gas turbine engine comprising: a rotatable fan shaft; first and second support structures extending in parallel from the shaft to a load bearing structure to provide radial location of the shaft within an engine casing, wherein the first support and second support structures include first and second respective mechanical fusible joints; wherein the first fusible joint is a two-stage fuse which partially fails within a first predetermined load range, the second fusible joint fails within a second predetermined load range which is different to the first load range, and the first fusible joint fully fails only when the second fusible joint has failed.

Abstract: A gas turbine engine includes a fan shaft that drives a fan that has fan blades. A fan shaft support that supports the fan shaft defines a fan shaft support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh that defines a gear mesh transverse stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 11% of the fan shaft support transverse stiffness and less than 8% of the gear mesh transverse stiffness.

Abstract: A turbine ring assembly includes ring sectors made as a single piece of ceramic matrix composite material and being for mounting on a metal ring support structure, the ring support structure having two tabs extending radially towards a gas flow passage, each ring sector having a first portion forming an annular base with a radially inside face defining the inside face of the turbine ring and an outside face from which there extend two tab-forming portions, the ring sectors having a section that is substantially ? shaped. The tabs of each ring sector fit axially over the tabs of the ring support structure with contact between the tabs of the ring support structure and the tabs of each ring sector when cold. The tabs of each ring sector are held to the ring support structure by pegs passing through holes formed in the tabs of each ring sector.

Abstract: A system includes an alignment system. The alignment system includes a first bladder configured to be positioned under a first component of a first gas turbine system. The alignment system further includes a first valve configured to adjust a first flow of fluid from a fluid source to the first bladder to expand the first bladder to adjust a position of the first component of the first gas turbine system.

Abstract: A gas turbine engine unit (110) for use in a modular power generation system includes an engine package (112) and a mechanical handling system adapted to convey components (114) out of and into the engine package (112). The engine package (112) includes a floor (132), a plurality of side walls (136), and a ceiling (134) that cooperate to define a sheltered space (140) sized to receive a gas turbine engine. The mechanical handling system includes rails (121) adapted to support components (114) conveyed out of and into the sheltered space (140) defined by the engine package (112).

Abstract: An exhaust system and a gas turbine, in which the exhaust system includes an exhaust casing; an outer diffuser supported inside the exhaust casing; an inner diffuser disposed inside the outer diffuser to form an exhaust gas flow passage between the inner diffuser and the outer diffuser; a strut cover coupled at a first end to the outer diffuser and coupled at a second end to the inner diffuser; and a second cooling air introduction port provided in the exhaust casing, further on the downstream side of the exhaust gas flow passage than the strut cover. Furthermore, a non-perforated partition member having an annular shape is arranged so as to cover the outer side of the outer diffuser and is supported by the exhaust casing to form a cooling air flow passage.

Abstract: The invention relates a combined cycle power plant with a gas turbine, a shaft connecting a compressor to a turbine, and a first generator, a heat recovery steam generator fluidly connected to the exhaust of the gas turbine.

Abstract: Disclosed are compositions of novel working fluids uniquely designed for higher cycle efficiencies leading to higher overall system efficiencies. In particular, these working fluids are useful in Organic Rankine Cycle systems for efficiently converting heat from any heat source into mechanical energy. The present invention also relates to novel processes for recovering heat from a heat source using ORC systems with a novel working fluid comprising at least about 20 weight percent cis-1,1,1,4,4,4-hexafluoro-2-butene (HFO-1336mzz-Z), trans-1,1,1,4,4,4-hexafluoro-2-butene (HFO-1336mzz-E), or mixtures thereof.

Abstract: A valve train assembly having a valve train carrier including a body having a cartridge cavity formed in the body, a hydraulic lash adjuster adjustment (HLA) assembly, and a cartridge removably disposed in the cartridge cavity. The cartridge includes a main body defining an inner bore, wherein the HLA assembly is disposed in the inner bore, and the cartridge is sized and shaped for insertion into the cartridge cavity formed in an underside of the valve train carrier. The cartridge is configured to have a valve train lash set prior to insertion into the cartridge cavity. A rocker arm assembly includes a body configured to engage the hydraulic lash adjustment (HLA) assembly, an end having a socket formed therein, and an e-foot extending through the socket and coupled to the end, the e-foot configured to maintain substantially flat contact with a top surface of an engine valve.

Abstract: Systems for valve actuation in internal combustion engines provide configurations for hydraulic lash adjusters and valve actuation valvetrain components that are particularly suitable for prevention of HLA jacking in lost motion cam environments and in valve bridge environments. In one implementation, a rocker arm may transmit motion from a lost motion cam having main event and auxiliary event lobes. Main event motion is transmitted to two engine valves through the rocker arm, a lash adjuster, lash adjuster loading component and valve bridge, which define part of a first load path. Braking motion is transmitted to one of the engine valves through an inboard valve actuator and bridge pin, which define part of a second load path. The HLA is thus disposed in a separate load path from the braking valve load and the lash adjuster loading component keeps the lash adjuster under a constant compressive force to prevent jacking.

Abstract: A camshaft phaser arrangement configured for a concentric camshaft having inner and outer camshafts is provided. The camshaft phaser arrangement includes a first camshaft phaser and a second camshaft phaser. Each of the camshaft phasers is configured to be connected to either the inner or the outer camshaft. One or more couplers are arranged to torsionally couple the first camshaft phaser to the second camshaft phaser. A first end of the coupler is received by a radial slot configured within either the first or second phaser.

Abstract: A sliding mechanism 1 includes a first sliding member 10 and a partner second sliding member 20 configured to slide relative to the first sliding member 10. The first sliding member 10 includes a matrix phase 11 and a hard phase 13 that is harder than the matrix phase 11, in which the hard phase 13 is embedded in the matrix phase 11 in a dispersed state. The second sliding member 20 includes a base 21 and a surface-treatment layer 23 that is formed on the sliding surface 20 of the base 21 and is harder than the matrix phase 11.

Abstract: Internal combustion engines having multi-stage telescoping poppet valves in lieu of conventional poppet valves are disclosed. The engines may have pistons with a skirt with a field of pockets that provide a ringless, non-lubricated, seal equivalent. The piston heads may include one or more depressions and may be domed to facilitate the movement of air/charge in the cylinder. The engines may also have non-circular, preferably rectangular, cross-section pistons and cylinders. The engines also may include a split crankshaft. The engines may use the pumping motion of the engine piston to supercharge the cylinder with air/charge. The engines also may operate in an inverted orientation in which the piston is closer to the local gravitationally dominant terrestrial body's center of gravity at top dead center position than at bottom dead center position.

Abstract: A switching rocker arm assembly constructed in accordance to one example of the present disclosure can include an outer arm, an inner arm, a pivot axle, a bearing axle, a first torsional bearing axle spring and a second torsional bearing axle spring. The outer arm can have a first outer side arm and a second outer side arm. The outer arm can further include first and second torsional spring mounts. The inner arm can be disposed between the first and second outer side arms. The pivot axle can support the inner and outer arm for relative pivotal movement therearound. The bearing axle can support a bearing. The first torsional bearing axle spring can be mounted around the first torsional spring mount and have a first end engaged to the bearing axle and a second end engaged to the outer arm. The first end extends inboard relative to the second end.

Abstract: The first opening part penetrates the first partition wall that separates the crank chamber and the oil sump chamber. The lubricating device of the engine includes an oil mist generation control part. The oil mist generation control part disperses gas injected from the crank chamber into the oil sump chamber through the first opening part when the crank chamber has a positive pressure or restricts the flow of oil with which the injected gas collides, thereby controlling an amount of oil mist generated in the oil sump chamber.

Abstract: A coiling heat exchanger, characterized by a heat exchanger spiral consisting of a liquid shield with fins, whereby neighboring coils of the spiral of the liquid shield are spaced apart from one another by the fins and connected to one another in a heat exchanging manner and that the liquid shield is perfused by liquid, whereby gas flows between the neighboring coils of the spiral of the liquid shield along the coiling axis.

Abstract: A liquid cooled exhaust manifold preferably includes an exhaust open-ended manifold, at least two exhaust tubes, an input port and an outlet tube plate. The exhaust open-ended manifold includes an inner cavity. The input port is formed as an inlet of the exhaust open-ended manifold housing and an exhaust opening is formed as an outlet of the exhaust open-ended hollow housing. The at least two exhaust tubes are inserted through the exhaust opening into input port. An opposing end of the at least two exhaust tubes are retained by the outlet tube plate, which is attached to the outlet. A second embodiment includes a dual open-ended manifold, at least two exhaust tubes, an inlet tube plate and an outlet tube plate. A third embodiment includes an inlet open-ended manifold, at least two exhaust tubes, an inlet tube plate and an outlet port. The liquid cooled exhaust manifold includes additional embodiments.

Abstract: Aspects of the subject disclosure may include, for example, an emission control system that includes an emission control device having a plurality of passages to facilitate emission control of an exhaust gas from a vehicle engine. A controller generates a control signal to initiate induction heating of the emission control device. An electromagnetic field generator responds to the control signal by generating a power signal applied to a coil to cause the induction heating of the emission control device, wherein a frequency of the power signal is adjusted to control a power transferred to the coil.

Abstract: Aspects of the subject disclosure may include, for example, an emission control system that includes an emission control device having a plurality of passages to facilitate emission control of an exhaust gas from a vehicle engine. A controller generates a control signal to control induction heating of the emission control device and determines a resonant frequency of a coil. An alternating current (AC) source responds to the control signal by generating a power signal applied to the coil to cause the induction heating of the emission control device, wherein a frequency of the power signal is selected based on the resonant frequency of the coil.

Abstract: A support for an electric heating type catalyst includes: a honeycomb structure; and a pair of metal electrode portions. One metal electrode portion of the pair of metal electrode portions is disposed on a side opposite to the other metal electrode portion across a center of the honeycomb structure. One or both of the pair of metal electrode portions includes: a plate-shaped body portion; and a plurality of tongue pieces each protruding from the body portion. A part of each tongue piece is in contact with the honeycomb structure.

Abstract: The invention relates to a method for checking the function of at least one PTC heating element which is used in a device for providing a liquid additive. The at least one PTC heating element is connected to a voltage source via electric conductors. According to the method, a starting current with a first value is provided at a specified operating voltage in a step a). Then, in a step b), a monitoring process is carried out in order to determine whether the starting current with the first value is provided for a minimum duration, said minimum duration having a value of at least seconds. The method is used in particular for on-board diagnoses of a device for providing a liquid additive.

Abstract: A method for operating a system having an internal combustion engine and an exhaust aftertreatment system having an SCR catalyst, wherein the internal combustion engine is controlled on the basis of at least one process parameter that influences a nitrogen oxide raw emission, wherein aging detection is performed for the SCR catalyst, wherein in a first operating mode of the internal combustion engine, if aging of the SCR catalyst is detected, the at least one process parameter is changed in the direction of a reduced nitrogen oxide raw emission, wherein the internal combustion engine is controlled on the basis of the changed at least one process parameter.

Abstract: An exhaust aftertreatment system includes a pump configured to circulate a reagent, an injector configured to deliver the reagent into an exhaust stream, a sensor configured to (i) measure an operating parameter of the aftertreatment system and (ii) output a signal that indicates a value of the measured operating parameter, and a control module configured to control the injector based on the signal outputted by the sensor. The control module includes a correction coefficient determination module configured to generate a correction coefficient based on the signal outputted by the sensor. The control module further includes an injector control module configured to receive an injector flow control signal, determine a pulse width modulation (PWM) signal based on at least the injector flow control signal, and generate an injector control signal that controls actuation of the injector based on at least the correction coefficient and the PWM signal.

Abstract: An aftertreatment system comprises an aftertreatment component structured to decompose constituents of an exhaust gas produced by an engine. A reductant insertion assembly is fluidly coupled to the aftertreatment component and configured to insert a reductant therein. A controller is operatively coupled to the reductant insertion assembly and configured to instruct the reductant insertion assembly to insert the reductant into the aftertreatment component for a first insertion time between first time intervals. The controller determines an operating condition of the engine, and determines if the operating condition satisfies a predetermined condition. In response to the predetermined condition being satisfied, the controller instructs the reductant insertion assembly to insert the reductant into the aftertreatment component for a second insertion time between second time intervals. The second insertion time is longer than the first insertion time.

Abstract: A line connector for a fluid and a ready-made medial line including the line connector. The line connector includes a connecting piece with a flow-through channel in the interior thereof and extending in a longitudinal direction of the connecting piece. The connecting piece has at each of its two ends a coupling section that is designed such that a flexible media line or a tubing or an aggregate can be connected to an aggregate connector. The flow-through channel is provided with an electrical heating unit. In the region of the flow-through channel, between the connecting sections, a circumferential enclosed receiving housing is formed on the coupling piece and in which an optical sensor unit is disposed for measuring characteristics of the fluid flowing in the flow-through channel. The ready-made media line includes the line connector and a tubular media line connected on one or both ends thereof.