Abstract: A power plant comprising: a rotor mounted for rotation; a rotor casing; and a rotor casing liner, comprising a plurality of sections, positioned between the rotor and the rotor casing; wherein at least one section of the plurality of sections of the rotor casing liner is sized to enable removal of the at least one section without adapting the rotor.

Abstract: The invention refers to an arrangement for sealing an open cavity against hot gas entrainment. The open cavity is arranged between two axially adjacent stationary components limiting radially a hot gas path of a rotary flow machine, of which at least the downstream component carries at least one airfoil extending radially into said hot gas path. A multitude of air jets is directed into the open cavity such that hot gas flowing over the open cavity is prevented from penetrating into the open cavity completely. The invention has an arrangement of supply conduits for air jets which are directed into the open cavity with a jet momentum such that hot gas is induced not to enter the open cavity and forming at least one hot gas vortex close to the hot gas path within the open cavity and preventing hot gas from penetrating into the open cavity beyond the extension of the hot gas vortex.

Abstract: A component of a turbine stage of a gas turbine engine is provided, the component forming an endwall for the working gas annulus of the stage. The component has one or more internal plena behind the endwall which, in use, contain a flow of cooling air. The component further has a plurality of exhaust holes in the endwall. The holes connect the plena to a gas-washed surface of the endwall such that the cooling air effuses through the holes to form a cooling film over the gas-washed surface. Each exhaust hole has a flow cross-sectional area which is greater at an intermediate position between the entrance of the hole from the respective plenum and the exit of the hole to the gas-washed surface than it is at said exit.

Abstract: A component of a turbine stage of a gas turbine engine is provided. The component forms an endwall for the working gas annulus of the stage. The component has one or more internal passages behind the endwall which, in use, carry a flow of cooling air providing convective cooling for the component at the endwall. Each passage is formed by a plurality of straight passage sections. The passage sections connect end-to-end such that the connections between nearest-neighbour passage sections form angled bends. A first portion of the passage sections lie in a first plane. A second portion of the passage sections lie in a second plane which is spaced from and parallel to the first plane. A third portion of the passage sections extend between the first and the second planes.

Abstract: A system includes a gas compressor system and a thermal cycle. The gas compressor system includes a compressor housing defining an interior compressor chamber. A gas compressor is in the interior compressor chamber to compress gas received into interior compressor chamber. A heat exchange fluid passage is provided adjacent to a surface that contacts the gas being compressed by the gas compressor. The thermal cycle includes a working fluid heated using the heat exchange fluid passage of the compressor housing. The working fluid is expanded by the thermal cycle to generate electricity.

Abstract: An article for mixing ambient fluid with a motive fluid comprises a conduit, and thermally conductive concentric inner and outer nozzles extending from the conduit. The conduit is configured to supply the motive fluid to the outer nozzle and the ambient fluid to the inner nozzle. The inner nozzle extends further downstream from the conduit than the outer nozzle.

Abstract: An apparatus is provided having a first zone with a fluid flow at a first pressure, and a second zone with a fluid flow at a second pressure. A sump cavity is provided in fluid communication with the first zone and a sump vent. An eductor system may be provided with a fluid flow path therethrough and in fluid communication with the second zone and the sump vent. The eductor system may be provided with an altitude sensing valve and may also be provided with gage pressure sensing valve. The eductor system may further be provided with a second gage pressure sensing valve and may also be provided with an orifice plate. The gage pressure sensing valves may react to the gage pressure of the second zone.

Abstract: The present invention relates to a method for providing a fluid flow to a compressor system of a first turbo machine, wherein the compressor system includes at least one compressor housing in which at least one impeller is arranged and through which a compressor flow flows. The method includes feeding a primary fluid flow to a mixing region of the compressor system. The method further includes feeding a secondary fluid flow from an outside region of the compressor housing to the mixing region so that the secondary fluid flow mixes at least in part with the primary fluid flow to form a resulting fluid flow so that between the primary fluid flow and the secondary fluid flow a momentum exchange takes place, and so that the secondary fluid flow is promoted by the primary fluid flow. The method further includes feeding the resulting fluid flow to the compressor flow upstream of the impeller in the direction of the impeller.

Abstract: A gas turbine engine including a stator vane directing hot combustion gases onto rotor blades is provided. The stator vane includes a platform disposed at the side of the vane radially inward/outward with respect to the axis of rotation of the engine, the platform having a trailing edge portion downstream with respect to the flow of gases past the stator vane. A support and cooling arrangement is included for directing a cooling fluid to an upstream end of a radially inwardly/outwardly facing side of the trailing edge portion of the platform, the arrangement also directing the cooling fluid to flow over the side in a generally axial direction to a downstream end of the side, the cooling fluid cooling the trailing edge portion as it flows over the side, wherein turbulators are included to increase heat transfer from the trailing edge portion as the cooling fluid flows over the side.

Abstract: An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing.

Abstract: A steam turbine 10 is provided with a double-structure comprising an inner casing 20 and an outer casing 21. A turbine rotor 22, in which plural stages of moving blades 24 are circumferentially implanted, is operatively disposed in inner casing 20. A diaphragm outer ring 25 and a diaphragm inner ring are disposed along the circumferential direction in inner casing 20. Stationary blades 27 are circumferentially provided between diaphragm outer ring 25 and the diaphragm inner ring, so that diaphragm outer ring 25, the diaphragm inner ring and stationary blades 27 form a stage of stationary blades. The stages of the stationary blades are arranged alternately with the stages of moving blades 24 in the axial direction of turbine rotor 22. A cooling medium passage 40 for passing a cooling medium CM which is supplied through a supply pipe 45 is formed between inner casing 20 and diaphragm outer ring 25.

Abstract: The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced.

Abstract: Invention relates to method of operating turbocharged piston engine including the steps of running the engine during a period, shutting down the engine, and restarting the engine. After a first time interval from shutting down the engine, and while a turbine and compressor parts of the turbocharger are rotating, a cleaning agent is introduced into the stream of gas flowing in a flow channel upstream the turbine part during a second time interval prior to restarting the engine.

Abstract: A gas turbine engine axial compressor vane is disclosed having an aperture capable of flowing a relatively high pressure working fluid to change a direction of a flow vector downstream of the vane. The relatively high pressure working fluid can originate from a compressor discharge. The vane may have any number of apertures.

Abstract: Intakes of gas turbine engines are subject to cross winds and high incidence cross flows which can affect the stability of air to the propulsive fan. An active flow control arrangement for an intake comprises a compressed gas supply pipe, a valve arrangement, a controller, and a compressed gas distribution pipe. The supply pipe is fluidly connects between a compressed gas source and the valve arrangement. The distribution pipe fluidly connects between the valve arrangement and intake surface for supply of compressed gas thereto. The active flow control arrangement is operable to supply compressed gas to the intake surface to prevent separation of a main air flow passing through the intake from the inlet surface thereby maintaining stability of the intake air flow to the fan.

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump that is selectively driven by a motor or a shaft to communicate air to an interior of the nose cone. The pump shaft is driven by a dedicated geared architecture.

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.

Abstract: The invention relates to a device for cooling of electric motor (10), which electric motor comprises a stator (30) with a jacket surface/stator back (35), wherein a housing (40) is arranged to surround the stator (30), the device comprising at least one cooling channel (50) in which a liquid cooling medium is intended to stream for cooling of the electric motor (10), wherein the housing (40) is arranged to run separated from the stator (30) along a main part of the thermoset cased jacket surface (35) of the stator (30) for forming of said cooling channel (50) between the housing (40) and said jacket surface (50), wherein the stator winding (32) of the stator is arranged to run along and axially project from and turn outside of said jacket surface (35), wherein the stator (30) including the projecting stator winding (32) is embedded with said thermoset (E), wherein said cooling channel (50) also is formed between the housing (40) and the thus projecting stator winding (32).

Abstract: A steam supply for a turbomachine with an inner housing and an outer housing is provided. The steam supply includes an inner pipe and an outer pipe, a cooling medium inlet opening disposed in the outer pipe and a cooling medium entering thereby into space between the inner pipe and the outer pipe, and the inner pipe being cooled thereby.

Abstract: An in-pipe turbine with the use of an air bubble in a new and unique configuration with electronic controls can improve the efficiency of in-pipe hydroelectric turbines.

Abstract: A combustor (14) is placed next to a turbine (16), on the side opposite a compressor (12). A heat insulation device (20) for reducing the transmission of heat from the high-temperature side to the low-temperature side is provided between the combustor/turbine and the compressor. A connection shaft (18) has an axial hole (18a) open on the inlet side of the compressor and axially extending to near a turbine impeller, and also has a radial hole (18b) open near the turbine impeller to the outside of the connection shaft and radially extending to be in communication with the axial hole.

Abstract: A stator for installation in a rear section of a jet engine includes a plurality of guide vanes which extend in the radial direction of the stator and between them define ducts for leading a gas. A first side of the stator in its axial direction defines an inlet for the gas and a second side, opposite the first side, defines an outlet for the gas. The guide vanes have such a shape that together they at least substantially cover the gas inlet viewed in the axial direction of the stator from the outlet side thereof.

Abstract: To provide a can manufacturing pump impeller in which a stress of a base portion of a blade is prevented from increasing while improving the strength of a joint portion of a hub and a boss. In order to reinforce a joint portion of a hub and a boss, a plate is jointed to the inside of an impeller. In order not to overlap a base portion of a blade and the plate with each other on the hub, an opening portion is provided in the plate around the base portion of the blade on the hub. As a shape of the opening portion, a semicircular shape, a semielliptical shape, a rectangular shape, or a trapezoidal shape can be selected. Further, as a plate shape, a flat plate structure, a shell structure, or a curved structure can be selected.

Abstract: A turbine system for the utilization of the energy of oceanic waves includes: a chamber that is provided with an opening at its lower end and at its upper end respectively; a duct that is open at both ends for guiding a stream of air, the lower end of the chamber being designated to be submerged in ocean water, and the opening of the upper end being connected with one of the ends of the duct; an energy unit that is mounted coaxial to such and surrounded by the duct; and a device for cleaning the rotor blades of deposits or for preventing the formation of deposits on the rotor blades.

Abstract: An apparatus for cooling air for an intake to a gas turbine, is provided and includes a pressurized water piping and nozzle apparatus for producing a water spray in an airflow to the intake; and evaporative media for receiving the spray and causing a pressurizing of the air in the airflow.

Abstract: A rotor wheel is provided and includes a body having first and second opposing faces and portions recessed from a plane of the first face to define therein an annular groove and a plurality of tributary grooves, the annular groove being receptive of fluid from an external source and formed to direct the fluid to flow along an annular flow path, and the plurality of tributary grooves being receptive of the fluid from the annular groove and respectively formed to direct the fluid to flow sequentially along radial and axial tributary flow paths while preventing inter-tributary groove fluid communication.

Abstract: A method for machining a gas turbine rotor which is provided with a cooling air slot which concentrically extends around the axis of the gas turbine rotor and is supplied with compressed cooling air via axial cooling air holes which at the side lead into the slot base of the cooling air slot, and the opening of which is covered by bridges which are arranged in a distributed manner over the circumference and spaced apart from each other by gaps. A crack-resistant slot shape is achieved without intervention into the configuration of the bridges by a material-removing tool, particularly a milling tool, being lowered in the gaps between the bridges one after the other into the cooling air slot and in this way the slot base of the cooling air slot being machined and widened over the entire circumference.

Abstract: A turbine rotor 300 includes: a high-temperature turbine rotor constituent part 301 where high-temperature steam passes; low-temperature turbine rotor constituent parts 302 sandwiching and weld-connected to the high-temperature turbine rotor constituent part 301 and made of a material different from a material of the high-temperature turbine rotor constituent part 301; and a cooling part cooling the high-temperature turbine rotor constituent part 301 by ejecting cooling steam 240 to a position, of the high-temperature turbine rotor constituent part 301, near a welded portion 120 between the high-temperature turbine rotor constituent part 301 and the low-temperature turbine rotor constituent part 302. A value equal to a distance divided by a diameter is equal to or more than 0.

Abstract: Apparatus and methods are presented for mixing a high temperature steam, perhaps leaked from an upstream turbine, with the cooler steam from a lower temperature, downstream turbine and introducing the mixture into the downstream turbine.

Abstract: A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air, and a second air passage for directing a portion of a bypass air flow, the portion of the compressor air flow being thereby cooled by the portion of the bypass air flow through the common wall.

Abstract: An axial flow turbine stage structure has: an annular diaphragm inner ring; an annular diaphragm outer ring arranged radially outside and coaxially with the diaphragm inner ring and separated from the diaphragm inner ring by an annular flow path interposed between them; stationary blades arranged peripherally at intervals in the annular flow path and rigidly secured to the diaphragm inner ring and the diaphragm outer ring; and moving blades rigidly secured to the outer periphery of a rotatable rotor and arranged peripherally at intervals respectively at axially downstream sides of the stationary blades. Through holes are formed in the diaphragm outer ring so as to allow axial upstream side and axially downstream side of the stationary blades to communicate with each other.

Abstract: An apparatus and a method for cooling and/or sealing a gas turbine by selectively boosting the pressure of air extracted at a lower extraction stage is provided. The pressure of the extracted air is boosted by an external compressor before it becomes available for cooling and/or sealing the turbine components. A bypass line includes a higher extraction stage providing air for cooling the turbine.

Abstract: A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow using available dynamic pressure in the bypass duct. Scooped air may be provided, for example, to an active tip clearance control apparatus in a long duct turbofan engine.

Abstract: A system for providing air from a multi-stage to a turbine includes a turbine having a high pressure input port and a low pressure input port. The system also includes a compressor having at least one high pressure extraction air output and at least one low pressure extraction air output. A valve is fluidly connected to the at least one high pressure extraction air output, at least one low pressure extraction air output and low pressure input port of the turbine. The valve is selectively operated to fluidly connect the at least one low pressure extraction air output with the low pressure input port during normal operating conditions and fluidly connect the at least one high pressure extraction air output and the low pressure input port during a turn down condition or below design temperature operation to enhance turbine engine performance.

Abstract: A turbo-molecular pump that enables reliable suppression of attachment of depositions onto component parts thereof. The turbo-molecular pump discharges a deposition-causing gas from a processing chamber. A rotor has a rotor shaft aligned with an exhaust stream. A cylindrical casing houses the rotor therein. A plurality of blade-form rotor blades projects from the rotor orthogonally with respect to the rotor shaft and are divided into a plurality of rotor blade groups. A plurality of blade-form stator blades projects orthogonally with respect to the rotor shaft from a rotor-facing surface and are divided into a plurality of stator blade groups. Gas supply ports are located on an upstream side of the rotor blade group that is located furthest downstream in the exhaust stream, and supply a deposition-suppressing gas which includes gas molecules having a large molecular weight.

Abstract: A turbine wheel hole plug that includes: 1) an approximate cylindrical body, the cylindrical body sized such that the cylindrical body fits snugly into a turbine wheel hole; 2) a first flange at a first end of the cylindrical body, the first flange being approximately cylindrical in shape and having a diameter that is larger than the diameter of the turbine wheel hole; and 3) a second flange at a second end of the cylindrical body, the second flange comprising a flared flange. The first flange and the second flange may lock the cylindrical body into a preferred position in the turbine wheel hole.

Abstract: A rotary pressure transfer device utilizes a multi-channel, generally cylindrical rotor (15) that revolves with its flat end faces juxtaposed with flat end surfaces of a pair of flanking end covers (19, 21) in which inlet and outlet passageways are provided. The design is such that there are only oblique ramps (65) in the passageways on the high pressure side which create directional flow of liquid to cause rotor revolution in the desired direction. Passageways (27a, 27b) on the low pressure side may be shaped so that there is essentially axial or longitudinal flow entry and discharge of liquid between the channels and the passageways, or passageways (71) may be constructed to create directional flow that slightly retards rotor revolution in such desired direction.

Abstract: The invention relates to a rotor of a flotation machine, particularly to a rotor, that is used for dispersing air to a slurry, and which rotor comprises alternating air ducts and slurry grooves and a collar fitted to the rotor for guiding the slurry flow into the interior of the rotor for avoiding undesired cross flow effect of the slurry flow. The rotor of the present invention efficiently prevents sanding effect and provides excellent dispersion of air into the slurry.

Abstract: Invention relates to method of operating turbocharged piston engine including the steps of running the engine during a period, shutting down the engine, and restarting the engine. After a first time interval from shutting down the engine, and while a turbine and compressor parts of the turbocharger are rotating, a cleaning agent is introduced into the stream of gas flowing in a flow channel upstream the turbine part during a second time interval prior to restarting the engine.

Abstract: A vertical axis wind turbine comprising: a rotatable vertical shaft; a first horizontal shaft attached to the vertical shaft, and extending on either side of the vertical shaft; a first wind turbine blade fixedly attached to the first horizontal shaft, the first wind turbine extending in a generally perpendicular direction from the first horizontal shaft; a second wind turbine blade fixedly attached to the first horizontal shaft, the second wind turbine blade extending in a generally perpendicular direction from the first horizontal shaft, the second wind turbine blade fixed at an operational angle with respect to the first wind turbine blade; a first and second motion limiting means attached to the vertical shaft, where each motion limiting means extends into the rotational travel of a turbine blade.

Abstract: The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced.

Abstract: A damped spring assembly includes a helical spring. The helical spring is movable along an axis and has a winding direction. A damper is movable along the axis and includes a helical shape. The damper is wound in a direction opposite the winding direction. The damper applies a radial load to the spring for damping movement of the spring along the axis as the spring vibrates. The damper has a very low axial spring rate and it contributes very little to the axial load provided by the spring.

Abstract: A heat exchanger comprising a main heat exchange housing, a cooling air inlet line and a hot air inlet line to bring a cooling airflow and a hot airflow in the main housing. A heat pre-exchanger is disposed upstream from the main housing, the heat pre-exchanger being able to be crossed by the cooling airflow and the hot airflow prior to the main housing. The invention also relates to a propulsion unit and an aircraft comprising such a heat exchanger.

Abstract: A device is provided. The device is configured to introduce a pressurized flow along a Coanda profile and to entrain additional fluid flow to create a high velocity fluid flow; wherein the high velocity fluid flow is directed to an end use system through a flow path in flow communication with the device.

Abstract: In the method for interspersing a gas flow with liquid droplets, the liquid droplets are injected in a liquid injection plane into the gas flow, characterized in that an auxiliary gas is simultaneously injected with the liquid droplets into the gas flow. The injection speed of the auxiliary gas is larger than the injection speed of the liquid droplets so that the injected auxiliary gas stabilizes the injected liquid droplets with respect to trajectory and size, partly shields them from the gas flow and/or entrains them into the gas flow. By way of this one achieves an improved control of the spatial distribution of the liquid droplets and their size distribution. The liquid droplets penetrate the gas flow more efficiently than without an auxiliary gas. A preferred use is the online wet-cleaning of a gas turbine compressor.

Abstract: A turbocharger having a cleaning port communicating between an external surface of the turbocharger housing and an internal cavity which communicates with a component of a gas flow control mechanism.

Abstract: A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the at least two injection openings is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation. Methods for optimizing the flow through the turbine engine are also disclosed.

Abstract: A method to operate and electronic controlled internal combustion engine, and particularly a heavy duty diesel engine, to effect vane cleaning of a variable geometry turbocharger.

Abstract: An air-guiding system between a compressor and a turbine of a gas turbine engine includes an air chamber (5) being delimited by the inner casing of the combustion chamber (4) and first and second seals (7, 8) towards the rotating compressor shaft cone (12). An axial thrust compensation chamber (6) is adjoined to said second seal (8) and respectively loaded with the turbine cooling air (B?, C) branched-off from the compressor air. Due to the higher pressure in said axial thrust compensation chamber with respect to said air chamber, the high axial forces are compensated. The air flowing back into said air chamber through said second seal (8) is guided and separated from components (10) and flowing-off air masses by a flow-guiding means (16) in said air chamber. This results in a high rinsing effect, a reduced vortex formation and finally, a reduced thermal stress.

Abstract: A securing arrangement 32 for securing an actuating lever 20 to a spindle 14, for example a spindle 14 of a variable inlet guide vane 10 in a gas turbine engine, comprises a fastening formation 38 rotatably co-operable, in use, with a corresponding fastening formation 30 on the spindle 14. The securing arrangement 32 is rotatable relative to the spindle 14 to a securing position in which the respective fastening formations 30, 38 co-operate so that the securing arrangement 32 secures the actuating lever 20 to the spindle 14. The securing arrangement 32 includes anti-rotation means 42, preferably in the form of anti-rotation tabs 44, for preventing rotation of the securing arrangement 32 from the securing position.