Abstract: Apparatuses, systems, and methods are provided for the lubrication of fluid displacement machines, in particular positive displacement machines such as twin screw expanders utilized in organic Rankine cycle systems, comprising a working fluid mixed with a lubricant that is neither soluble nor miscible in the liquid phase of the working fluid.

Abstract: This disclosure provides methods and systems for using coatings to control component dimensions during operations of a mechanical system, such as gas turbine combustion air cooling system. The mechanical system may have a component with a critical dimension defined by at least one surface. Upon detecting a change in the critical dimension, such as from surface erosion, a coating additive is deployed into the mechanical system. The surface is coated with the coating additive to offset at least a portion of the change in the critical dimension.

Abstract: Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

Abstract: Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

Abstract: A rotor stack assembly and method of assembling same. The rotor stack assembly comprises a tie bolt, at least one rotor disk, and a stub shaft. The rotor disk and stub shaft are carried by the tie bolt. The stub shaft is threadably engaged with a threaded end of the tie bolt and comprises a rotatable seal member and an engagement surface for contacting the rotor disk. Engagement of the stub shaft with tie bolt allows for tensioning and pre-loading of the tie bolt to desired levels.

Abstract: Airfoils having a leading edge, a trailing edge, a first end, and a second end with a leading edge hybrid skin core cavity formed within the airfoil extending from the first end to the second end proximate the leading edge, the cavity having a hot wall and a cold wall. The cavity has a variable height-to-width ratio in a direction from the first end to the second end, with a first aspect ratio proximate the first end and a second aspect ratio proximate the second end with the height defined as a maximum distance between the hot wall and the cold wall and the width is defined as an arc length of the cold wall.

Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The turbine rotor blade airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: An airfoil includes a leading edge and a trailing edge. A first exterior wall extends between the leading edge and the trailing edge. A second exterior wall opposite the first exterior wall extends between the leading edge and the trailing edge. A first cavity is adjacent the first exterior wall and includes a central portion and at least one forward extending slot passage and at least one aft extending slot passage.

Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.

Abstract: Turn caps for airfoils of gas turbine engines having a first pressure-side turn passage extending from a respective inlet to a respective outlet within the turn cap, a first suction-side turn passage extending from a respective inlet to a respective outlet within the turn cap, and a merging chamber fluidly connected to the outlets of the first pressure-side turn passage and the first suction-side turn passage, wherein each of the first suction-side turn passage and the first pressure-side turn passage turn a direction of fluid flow from a first direction to a second direction such that a fluid flow exiting the first suction-side turn passage and the first pressure-side turn passage are aligned when entering the merging chamber.

Abstract: A cover plate for maintaining axial alignment between a blade assembly and a rotor disk and transferring centrifugal loading directly to the rotor disk. The cover plate comprises a plate key extending axially from an elongate member, the plate key configured to engage a keyway of the rotor disk assembly and/or a notch of the blade key.

Abstract: Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

Abstract: A method of manufacturing a vane arrangement for a gas turbine engine comprises providing an aerofoil having a hollow cavity with an open end and providing a support member having a stub. The method further comprises welding the aerofoil to the stub. The method yet further comprises removing material from the stub so as to define a hollow region that extends through the support member and stub to the cavity of the aerofoil.

Abstract: The invention relates to a wear-resistant shield for a rotating blade root of a rotating blade of a gas turbine, especially an aircraft gas turbine, having a base and two side walls connected to the base, wherein the side walls lie opposite each other and are shaped so as to be substantially complementary to an outer contour of a particular rotating blade root, and wherein the wear-resistant shield for this purpose is set up in such a way that, in an installed state, it is to be taken up between the respective rotating blade root and a rotating blade root mount of a rotor, especially between the respective rotating blade root and an axial securing element arranged in the rotating blade root mount.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Abstract: An assembly for gas turbine, includes a first part and a second part installed circumferentially around a longitudinal axis of the turbine, where the first part has a first side face adjacent to a second side face of the second part, and where a first aperture made in first side face is facing a second aperture made in second side face, a sealing plate fitted inside the first aperture and the second aperture, at least one longitudinal face of the sealing plate includes at least two projections made either side of a longitudinal central area of the sealing plate, wherein each projection is of a height chosen so as to reduce a clearance between the sealing plate and the first and second apertures.

Abstract: A rotating labyrinth seal especially useful for effecting sealing between two plenums in aircraft gas turbine engines comprising a base and a plurality of radially-directed seal teeth rings extending circumferentially around the outer peripheral surface of the base. The seal separated from a load transmitting component via abutting surfaces which prevent cracks from migrating into the load transmitting component from the seal.

Abstract: A control system for a gas turbine engine comprises a case structure, a clearance control ring mounted for movement relative to the case structure, an outer air seal mounted to the clearance control ring and facing a first engine component, and a control and valve assembly that receives flow from a flow input source. The control and valve assembly is configured to direct flow into a first cavity positioned radially between the case structure and the outer air seal, and wherein the control and valve assembly is configured to direct flow into a second cavity positioned downstream of the first cavity to interact with a second engine component. A method of controlling flow between a compressor section and turbine section is also disclosed.

Abstract: A clearance control system for a gas turbine engine comprises at least one case support associated with an engine case defining an engine center axis. A clearance control ring is positioned adjacent the at least one case support to form an internal cavity between the engine case and the clearance control ring. The clearance control ring includes a first mount feature. An outer air seal has a second mount feature cooperating with the first mount feature such that the clearance control ring can move independently of the engine case in response to changes in temperature. An injection source inject flow into the internal cavity to control a temperature of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and an engine component. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.

Abstract: A power transmission system for use with a turbine, a turbocharger, or a compressor has a housing, a first shaft mounted within the housing, a second shaft rotatably mounted within the housing and positioned exterior of the first shaft, a second set of blades affixed to the first shaft, and a second set of blades affixed to the second shaft. The first set of blades is positioned adjacent to the second set of blades. The first set of blades are rotatable in a direction opposite to the second shaft and the second set of blades. A shroud is affixed to an outer periphery of one of the sets of blades so as to have a portion overlying at least a portion of an outer periphery of the other of the first and second sets of blades. A power receiver is driven by the second shaft so as to convert rotational energy of the second shaft into energy or motion.

Abstract: Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

Abstract: A gas turbine engine component includes a conformal surface. An array of resistance temperature detector (RTD) sensors is disposed across at least a portion of the conformal surface and a plurality of printed circuit traces are deposited on the conformal surface. The printed circuit traces connect each of the RTD sensors to a controller via a corresponding four wire circuit. Each circuit trace in the plurality of circuit traces extends to a circumferential edge of the conformal surface.

Abstract: A gas expander includes: a casing where a swirl chamber for a gas to be expanded is formed; a turbine wheel that is housed in the casing and rotationally driven by the expanded gas; a diffuser that is mounted to the casing in a direction of a rotating shaft of the turbine wheel and includes a flow path for the expanded gas to flow in the direction of the rotating shaft; a swirl stopper that is disposed in the diffuser, faces a downstream front end surface of a boss of the turbine wheel that faces the flow path, and includes a closed swirl stopping surface that is disposed to face the downstream front end surface of the boss with a gap between the closed swirl stopping surface and the downstream front end surface; and a swirl preventing plate that circumferentially partition the flow path in the diffuser.

Abstract: A shaft (21) for use as a rotating shaft in a gas turbine engine has an axis (X), an outer surface, an inner surface (28), an upstream end and a downstream end. The shaft (21) is arranged, in use, to rotate in a circumferential direction (R) about the axis (X). The inner surface (28) includes a radially inwardly protruding flange (22), a circumferential array of radially extending apertures (26) provided in the flange (22) and an array of channels (24) extending from an upstream side to a downstream side of the flange (22). The channels arranged circumferentially between adjacent apertures (26) of the circumferential array of apertures (26).

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

Abstract: A turbine engine with a casing including opposing surfaces and a manifold opening passing through the surfaces. A surface cooler is provided adjacent one of the surfaces. A cooler manifold passes through the manifold opening. A seal is provided between the surface cooler and the casing. At least one bolt is used to secure the surface cooler to the casing with the seal in between.

Abstract: A sealed bearing assembly includes an inner race, a bearing element, and an outer race extending radially in axial alignment between a rotatable member having an axis of rotation and a stationary support structure. The sealed bearing assembly also includes a first inlet header coupled to a first axial end of the outer race. The first inlet header includes at least one oil inlet port, at least one oil nozzle, and a first sealing member extending between the first inlet header and a first surface of the inner race.

Abstract: A rotary machine, including: a rotor (2) extending in an axial direction, the rotor including a first thrust collar (35) and a second thrust collar (36) projecting radially outward; a first thrust bearing device (31) configured to receive load acting in the axial direction via the first thrust collar (35); a second thrust bearing device (32) configured to receive load acting in the axial direction via the second thrust collar (36); and a load control device (16) configured to control load acting on at least one of the first thrust bearing device (31) and the second thrust bearing device (32).

Abstract: A strut assembly for a bearing compartment of a gas turbine engine includes an inner case, an outer case, and a first plurality of struts. The inner case is disposed within the bearing compartment and includes a first axis. The outer case defines an exterior of the bearing compartment and includes a second axis disposed co-axially with the first axis. The inner and outer cases define a flowpath between the inner and outer cases. Each strut of the first plurality of struts extends between and is connected to the inner and outer cases. The first plurality of struts is configured to maintain concentric positioning between the inner and outer cases and to allow relative changes in size between the inner and outer cases without deforming the inner case.

Abstract: A damper assembly includes a bearing assembly including a bearing outer race. A damper inner race is spaced from the bearing outer race and includes a plurality of circumferentially-spaced first openings. The damper assembly also includes a damper outer race spaced from damper inner race and a plurality of damper segments extending between the damper inner race and the damper outer race. Each damper segment includes a plurality of second openings.

Abstract: A turbocharger, with a turbine for expanding a first medium and a compressor for compressing a second medium. The turbine has a turbine housing and a turbine rotor. The compressor has a compressor housing and a compressor rotor coupled to the turbine rotor via a shaft. The turbine and compressor housings are connected to a bearing housing in which the shaft is mounted. The turbine housing has a turbine inflow housing and an insert piece for a nozzle ring with guide blades, which is connected on a first cover ring with a flange of the bearing housing. On the flange of the bearing housing multiple protrusions extending radially to the outside distributed over the circumference and first fasteners penetrate the protrusions of the flange of the bearing housing and are in engagement with the first cover ring of the nozzle ring.

Abstract: A support unit for a power unit reliably absorbs thermal deformation of the power unit due to thermal deformation of a casing and enables the center of the casing to be effectively maintained at a correct position. The support unit includes a supporting unit and a stress supporting unit. The supporting unit includes a first support configured to support a front part of the casing of the power unit, and a second support configured to support a rear part of the casing and provided with an auxiliary support configured to receive and support a weight of the casing. The stress supporting unit is disposed under the rear part of the casing and receives heat from the casing and primarily absorb stress resulting from thermal expansion of the casing. Stress in the casing resulting from the thermal expansion is secondarily damped by the second support via the stress supporting unit.

Abstract: A support assembly for supporting a gas turbine during a manufacturing configuration, a shipping configuration and an operating configuration. The support assembly includes a stand leg securable to a base, and the stand leg includes a turbine casing interface with a slot sized to receive a turbine casing pin. A support plate is attachable to the turbine casing interface. The support plate includes a closed pin aperture that is sized to fit over the turbine casing pin in the slot. The slot is a U-shaped slot in the turbine casing interface, and the U-shaped slot is open to receive the turbine casing pin from above.

Abstract: A turning device for a turbomachine comprises a plurality of electromagnets connectable to an electric power source; a rotor magnetically coupled with the electromagnets, connectable to a main shaft of the turbomachine and having a rotation axis, the electromagnets are arranged facing the rotor in order to induce eddy currents on a surface of the rotor and apply a torque to the rotor, thus rotating the main shaft.

Abstract: A system for generating electrical energy comprises a circuit containing a working fluid, an evaporator configured for boiling the working fluid, a turbine driven by the vaporized working fluid, and an electric generator coupled to the turbine for creating electric energy. The system further comprises a condenser for condensing the working fluid which flows from the turbine, and a pump for pumping the working fluid through the circuit. A hydrocarbons pipeline transports hydrocarbons having a hydrocarbon temperature from a well, a seawater intake is configured for taking in seawater having a seawater temperature, and a seawater discharge is configured for discharging the seawater.

Abstract: A power recovery system for recovering power from a working fluid, comprising a heat exchanger that is configured to receive a first stream of the working fluid, one or more expansion stages for expanding the working fluid to recover power from the working fluid, wherein one or more of the expansion stages is in fluid communication with the heat exchanger, wherein the heat exchanger is configured to transfer heat between the first stream of the working fluid and another stream of the working fluid that is received from one or more of the expansion stages.

Abstract: The use of a refrigerant in organic Rankine cycle systems including at least one hydrofluoroolefin, having at least four carbon atoms represented by the formula (I) R1CH?CHR2 in which R1 and R2 independently represent alkyl groups having from 1 to 6 carbon atoms, substituted with at least one fluorine atom, optionally with at least one chlorine atom.

Abstract: A valve train device, in particular for an internal combustion engine, includes a support element and a cam element which can be moved axially relative to the support element. The valve train device further includes a switch unit for axially moving the cam element, which switch unit includes a displacer that is intended to be at least operatively inserted between the support element and the cam element in order to axially move the cam element.

Abstract: A cam carrier includes a pair of longitudinal frames provided parallel to an axial direction of a camshaft and a plurality of transversal frames connected to the pair of longitudinal frames to be spaced from each other and supporting the camshaft via cam bearings. A flexible structure suppressing amounts of change in a relative position and an inclined angle of the cam bearings relative to the camshaft due to a thermal expansion is provided on at least one of wall surfaces of the longitudinal frames, the wall surfaces being located between adjacent transversal frames.

Abstract: A valve train lever for actuating a valve of a reciprocating piston engine, in particular an internal combustion engine. The valve train lever comprises a lever arm, which is pivotally movable about a pin; a tapping element, which lies against or can be made to lie against a cam of a camshaft of the reciprocating piston engine; a coupling mechanism, by way of which the tapping element is coupled to the lever arm spring-elastically in a first state and rigidly in a second state; and an actuating element, which is connected to the lever arm and lies against or can be made to lie against a valve tappet of the valve.

Abstract: An engine variable camshaft timing phaser (10) includes a sprocket (12), three ring gears (26, 28, 30), multiple planet gears (24), and a sun gear (22). The sprocket (12) receives rotational drive input from an engine crankshaft. One or more of the three ring gear(s) (26, 28, 30) receives rotational drive input from the sprocket (12) and rotates with the sprocket (12), and the remaining ring gear(s) (26, 28, 30) transmit rotational drive output to an engine camshaft (62). All three of the ring gears (26, 28, 30) engage with the planet gears (24). And the sun gear (22) also engages with the planet gears (24). In operation, relative rotational speeds between the sprocket (12) and the sun gear (22) causes the engine camshaft (62) to advance or retard engine valve opening and closing.

Abstract: A method of noise filtering a sliding camshaft actuator pin position output signal includes determining an actual pin position output signal period of a sliding camshaft actuator that occurs within a predetermined output signal period measurement window and establishing a pin position output signal filter window based on the actual pin position output signal period. Thereafter, the actual pin position output signal period from the sliding camshaft actuator is monitored by a control module and signals that occur outside of the pin position output signal filter window are rejected accordingly to prevent responding to false triggers.

Abstract: A valve operating system that includes a plurality of cam assemblies that are coupled for rotation about a rotary axis. Each of the cam assemblies has a control link and a first cam member. Each of the control links has a link body, which forms a majority of the control link, and that extends parallel to the rotary axis. Each of the first cam members is coupled to one of the control links for axial movement therewith along the rotary axis between first and second positions to alternate between first and second cam profiles, respectively.

Abstract: Provided is a grounding structure for an internal combustion engine, including a resinous body 2 configured to be attached to an engine body 7 and having a recessed portion 6 formed on a side thereof facing the engine body 7; a nut portion 13 integrally provided in the body 2, wherein the nut portion 13 includes a first end portion 13a opened into the recessed portion 6 and is made of a conductive material; and an oil pressure switch 5 configured to be attached to a second end portion 13b of the nut portion 13; and a conductive spring 16 arranged inside the recessed portion 6, wherein the conductive spring 16 is attached to the first end portion 13a of the nut portion 13 and is pressed against the engine body 7.

Abstract: The invention relates to a lubricating system for an internal combustion engine (1). The system includes a first conduit means (7) connecting a lubricant supply source (5) to the internal combustion engine (1) for supplying lubricant to the internal combustion engine (1). According to the invention, the system further includes a second conduit means (8) connecting a gas supply source to the first conduit means (7) for supplying gas to the first conduit means such that gas bubbles are formed in the first conduit means (7). A sensor (3) detects whether lubricant or whether gas is present in a certain part of the first conduit (7). The certain part being located downstream the connection of the second conduit means (8) to the first conduit means (7). A control unit (6) is connected to the sensor (3), which control unit (6) is arranged to determine whether lubricant is flowing through the first conduit means (7) or not, in response to the detections of the sensor (3).

Abstract: An oil filling assembly is configured to couple to an intake port of an engine to fill an oil tank connected to the intake port. The intake port is located behind an access door of the engine. The oil filling assembly includes a hopper defining an oil retention chamber that is configured to receive oil, and a coupler extending from the hopper. The coupler includes a neck defining an oil outlet fluidly connected to the oil retention chamber. The coupler is configured to removably mount to the intake port of the engine.