Abstract: Disclosed is a pump having a pump rotor rotatably supported about an axis of rotation in a pump stator. In this respect, the pump rotor is designed and is arranged above a rotor shaft in a shaft bearing such that a lubricating film of a lubricating fluid formed from the pump fluid can be formed in a lubricating ring gap between the rotor shaft and the shaft bearing. In accordance with the invention, a separation device is provided at the rotor shaft by which a predefinable quantity of the ingredient can be separated from the pump fluid by means of a centrifugal force in the operating state for providing the lubricating fluid.

Abstract: An exemplary gas turbine engine includes a radially stacked intershaft bearing assembly. The assembly includes an outer stubshaft having outer and inner diameter surface portions disposed concentrically with respect to one another. The outer diameter surface portion is rotatably connected to a body of the engine, and the inner diameter surface portion is rotatably connected to an inner stubshaft of the engine, so as to provide a stacked configuration of the inner stubshaft, the outer stubshaft, and the body along a radial direction orthogonal to a longitudinal axis of the engine.

Abstract: A wind turbine including a rotatable part, at least one absorber element secured to the rotatable part within an interior of the wind turbine, the at least one absorber element at least partly comprising lubricant absorbing material, wherein the absorber element is configured to absorb emerging lubricant inside the wind turbine is provided. Further, a rotor hub for a wind turbine, an absorber element for a wind turbine and a method for maintaining a clean environment in a wind turbine is also provided.

Abstract: The present invention relates to an improvement of an axial turbine. Thereto, the present invention includes a submerged turbine 100 in which a fluid is filled in an interior thereof. The present invention also includes a colliding turbine 200 for ejecting a fluid with a high pressure to rotate blades. The structure of the turbine according to the present invention includes a submerged turbine, a colliding turbine, or a combination type turbine (in which a submerged turbine and a colliding turbine are combined). Accordingly, quality and reliability of the product are significantly improved to satisfy the operator.

Abstract: The invention relates to a turbine casing of an exhaust-gas turbocharger, having an inlet connection piece adjoined by a spiral, and having an outlet connection piece, characterized by an insulating device for reducing the input of heat into the inlet connection piece, the spiral and/or the outlet connection piece.

Abstract: A vacuum pump, in particular to a turbomolecular pump, has a pump inlet, a pump outlet and a pump space for a gas to be pumped arranged between the pump inlet and the pump outlet, and at least one cooling gas inlet for a cooling gas for cooling the vacuum pump, the pump further having one or more hollow regions for the cooling gas connected in a gas conducting manner to the cooling gas inlet and arranged outside the pump space, wherein the or each hollow region is bounded by at least one component of the vacuum pump to be cooled.

Abstract: A low pressure shaft is provided for interconnecting a fan or low pressure compressor of a gas turbine engine with a low pressure turbine of the engine. The shaft has an aft section whose diameter expands progressively with distance along the rearward direction of the engine. The shaft further has an annular joint portion at the rear end of the aft section for joining the shaft to a drive arm of the low pressure turbine. The rate of expansion of the diameter of the aft section decreases with distance along the rearward direction of the engine.

Abstract: The present invention is directed to a pump and motor assembly assembled in a waterproof enclosure with external threaded connections for pump suction and discharge. The motor can be directly connected to a flexible coupling to a bi-rotational internal gear pump, having self-adjusting mechanical seals and cast iron housing. The pump and motor assembly can be mounted on a sliding base for easy access. Flex hoses can be used to connect pump suction and discharge to couplings attached to the pump enclosure. A discriminating leak detector can be installed at the low point of the pump enclosure to detect and annunciate the presence of oil and/or water.

Abstract: A compressor that includes a rotor assembly, a stator assembly and a heat sink assembly. The rotor assembly includes a shaft to which a bearing assembly and a rotor core are secured. The heat sink assembly is then secured to the bearing assembly and to the stator assembly.

Abstract: A turbine housing (1) of an exhaust-gas turbocharger (15) having a turbine volute (7) which is delimited by a metallic outer shell (8) and which has an inner wall (9); and a heat insulation layer (10) which is arranged on the inner wall (9) and which has a heat insulation core (6A, 6B) which, on its surface (12A, 12B) facing into a volute interior space (11), is covered by a first sheet-metal shell (3A, 3B). The heat insulation core (6A, 6B) is covered, on a surface (13A, 13B, 13?B) facing toward the inner wall (9), by a second sheet-metal shell (4A and 4B respectively).

Abstract: A product usable with a turbocharger may include a compressor wheel having an inducer section and an exducer section. Air may be collected by the inducer section and expelled by the exducer section. A cover may define a diffuser and a collection volute. The diffuser may lead away from the exducer section to the collection volute. The cover may define a collection cavity opening to the collection volute through a port and extending in an axial direction. The cover may define an inlet passage around the inducer section and the cover may include a dividing wall separating the inlet passage from the collection cavity.

Abstract: An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.

Abstract: Disclosed is a pump for conveying a pump having a pump rotor rotatably supported about an axis of rotation in a pump stator in the operating state and a rotor shaft is arranged in a shaft leadthrough such that a lubricating film of a lubricating fluid formed from the pump fluid can be formed in a ring gap between the rotor shaft and the shaft leadthrough; and wherein a separation device is provided at the rotor shaft by which a predefinable quantity of an ingredient can be separated from the pump fluid by means of a centrifugal force for providing the lubricating fluid at the ring gap in the operating state, wherein a recirculation device is provided so that a gas can be recirculated with the aid of the separation device.

Abstract: A turbo-molecular pump comprises: a rotor having a plurality of stages of rotor blades and a cylindrical section; a plurality of stages of stationary blades alternately arranged with respect to the rotor blades; a stator arranged with a gap from the cylindrical section, the stator together with the cylindrical section constituting a screw groove pump section; a plurality of spacers stacked on a base, the spacers including at least one cooling spacer having a cooling section; a heater heating the stator; a temperature regulation section controlling the heater to regulate the temperature of the stator so as to be a reaction product accumulation prevention temperature; and an auxiliary ring for reaction product accumulation prevention at least a part of which is located in a space between the spacer facing a bottom step rotor blade, and the bottom step rotor blade.

Abstract: The present invention concerns a Magnus rotor comprising a carrier, and a rotary body mounted rotatably to the carrier, as well as a drive device for driving the rotary body. The carrier has at least one opening which connects an internal space in the carrier with an external space in such a way that air can pass through between those two spaces. The invention further concerns a method of cooling elements of a Magnus rotor, a method of heating a rotary body of a Magnus rotor and a ship.

Abstract: A turbine engine cowl capable of covering a fan cone, the cowl including attachment components configured to engage with connection components of the cone in order to maintain the cowl and the cone secured to one another.

Abstract: A wind turbine includes a generator having a generator cooling system configured for passage of a cooling fluid, and a gear unit including a gear unit cooling system configured for passage of a cooling fluid. The gear unit cooling system includes a recooling unit which is configured to transmit during normal operation of the wind turbine thermal energy from the cooling fluid of the gear unit cooling system to air inside the generator or to the cooling fluid of the generator cooling system.

Abstract: According to the present invention, a wind turbine generator system is provided which can not only remove the influence of salt damage in case the system is established off-shore, but even if the facility becomes larger, which can also cool equipment and the generator provided in the tower and can reduce the possibility of decreasing power generation efficiency.

Abstract: A rotating assembly of turbomachinery is provided. The rotating assembly includes a plurality of components mounted on a rotatable shaft within a housing of the turbomachinery and at least one foil journal bearing assembly for mounting the rotatable shaft to the housing. The foil journal bearing assembly includes an annular bearing carrier mounted to the housing. An annular bearing sleeve is disposed within the annular bearing carrier and attached thereto. The annular bearing sleeve is lined with a plurality of foils. A journal is mounted to the rotatable shaft. The journal has an outer surface engaging the foils. The journal is configured to at least one of the following: resist operational deflection thereof and reduce the effects of misalignment. A method for producing the journal of the foil journal bearing assembly is also provided.

Abstract: In an axial flow gas turbine (30), a substantial reduction of the consumption of cooling air can be achieved by providing, within a turbine stage (TS), structure (39-44) to reuse the cooling air that has already been used to cool, especially the airfoils of, the vanes (33) of the turbine stage (TS), for cooling the stator heat shields (38) of that turbine stage (TS) downstream of the vanes (33).

Abstract: A bearing chamber apparatus (2) comprising a bearing chamber (4) having one or more seals (7) which seal an interior (5) of the chamber from an exterior (24) of the chamber; and further comprising: a pump in fluid communication with the interior of the chamber; and a controllable valve (20) in fluid communication with the interior of the chamber and the outside atmosphere. The arrangement allows oil leakage from the bearing chamber to be prevented and also allows a minimum pressure to be maintained within the bearing chamber.

Abstract: An active tip clearance control (ATCC) system of a gas turbine engine includes an ejector to selectively drive an air flow passing through the ATCC system. A high pressure air flow as a motive flow of the ejector is controlled by a valve according to engine operation requirements.

Abstract: An aircraft nacelle includes a first conduit for an air inlet and a second conduit for an engine, arranged end to end and connected by an annular flange, attached to the air inlet, and an annular flange, attached to the engine. The annular flanges are connected by a plurality of passage holes in the annular flanges and arranged in line with each other. Rods are housed in the passage holes. For at least one rod, the passage hole of one of the annular flanges has a diameter greater than the diameter of the rod allowing the rod to move in case of deformation of one of the two conduits. An angle profile is inserted between the rod and a cylindrical portion adjacent to the annular flange and is connected to the adjacent cylindrical portion through the intermediary of at least one mechanism for absorbing eventual deformations in radial direction.

Abstract: A particle deflector for a gas turbine engine deters accumulation of particles in cooling passages of nozzle vanes of the engine. The particle deflector is arranged to be disposed around a turbine housing over cooling passages that supply cooling air to nozzle vanes within the housing. The particle deflector includes circumferentially distributed mounting holes for mounting the particle deflector to the turbine housing. The particle deflector also includes circumferentially distributed spacers to space the particle deflector from the housing.

Abstract: A dovetail attachment seal for a turbomachine includes an outer seal member having a first end that extends to a second end through an intermediate portion, and at least one articulating element encapsulated, at least in part, by the outer seal member at one of the first and second ends. The at least one articulating element is slidingly disposed within the outer seal member.

Abstract: A thrust bearing device is constituted by a turbine-side thrust collar and a compressor-side thrust collar that are fixed to a rotary shaft; and a thrust bearing that is arranged between the thrust collars. The thrust bearing is provided with an oil passage that supplies lubricating oil r to sliding-contact surfaces formed between the thrust bearing and the thrust collars. The outsides of the thrust collars in a radial direction incline toward the thrust bearing side. A gap c between the sliding-contact surfaces is narrowed as the gap goes outward in the radial direction, and establishes a basic region gap (c1)>an outer peripheral end gap (c2). The lubricating oil outflow resistance of a radial outer region of the gap c becomes larger than that of a radial inner region. Therefore, the lubricating oil r can be kept from flowing out from a radial outer outlet.

Abstract: An electronic device includes a casing and a fan received in the casing. The fan includes a cover plate, a bottom plate and a side wall. An air outlet is defined in the side wall. The bottom plate defines an air inlet. The casing includes a bottom cover and a top cover. The bottom cover includes a base plate, and a side plate extending upwardly from a periphery of the base plate. The bottom plate includes a horizontal first area and a second area inclining relative to the first area. A height of the base plate relative to a horizontal plane gradually increases from one side of the casing to another side of the casing. A height of the second area relative to the horizontal plane also gradually increases from the one side of the casing to another side of the casing.

Abstract: A system for preventing objects from entering the intake of a jet engine including a deflector mounted to the turbine shaft and including a de-icing device to minimize collection of ice on the deflector. The deflector includes a sensor in one embodiment for measuring object strikes so that comprehensive impact data may be obtained to generate an impact report so that measures can be taken to minimize object impacts.

Abstract: A cooling structure of a turbine airfoil cools a turbine airfoil (10) exposed to hot gas (1), using cooling air (2) of a temperature lower than that of the hot gas. The turbine airfoil (10) includes an external surface (11), an internal surface (12) opposite to the external surface, a plurality of film-cooling holes (13) blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections (14) integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert (20) which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes (21) for impingement-cooling the internal surface (12).

Abstract: A micro-circuit cooling module for providing endwall cooling for a vane assembly in a gas turbine engine. The micro-circuit cooling module includes an outer perimeter rail, an upper plate and a lower plate defining a mixing chamber therein. A first plurality of spaced apart strip elements extend along a first direction in an upper channel of the mixing chamber, and a second plurality of strip elements extend along a second direction opposite to the first direction in a lower channel of the mixing chamber so that the first plurality of strip elements and the second plurality of strip elements form a criss-cross configuration. Air enters the module through metering holes in the lower plate and flows through the mixing chamber across the criss-cross elements in a turbulent manner and exits the module through slots in the upper plate.

Abstract: A system adapted for clearance control for a gas turbine including an outer turbine casing, an inner turbine casing and a plenum defined between the inner and outer turbine casings is disclosed. The clearance control system may include an impingement box disposed within the plenum. The impingement box may define a plurality of impingement holes. In addition, the clearance control system may include a first conduit in flow communication with the interior of the impingement box and a second conduit in flow communication with the plenum at a location exterior to the impingement box.

Abstract: A gas turbine includes a blade ring which faces blades from the outer side in a radial direction perpendicular to a turbine shaft, and a channel provided in the blade ring 1 and through which a cooling medium is flowed. The channel includes an inner channel formed in the blade ring 1, and a tubular outer channel which is connected to the inner channel, is disposed in an outer portion of the blade ring 1, and extends in a circumferential direction of the blade ring 1. The outer channel includes a plurality of fixing portions fixed to the blade ring 1 and a thermal stress absorbing portion disposed between the fixing portions adjacent in the circumferential direction and expandable and contractible in the circumferential direction.

Abstract: A method to modify the shape of a channel in a metallic substrate is described. The method includes the step of applying at least one metallic coating on selected portions of an interior surface of the channel, so as to alter the heat transfer characteristics of the channel during passage of a coolant fluid therethrough. Related articles that contain the modified channels are also described, such as gas turbine engine components.

Abstract: Modified turbine components include an original turbine component comprising an outer wail enclosing an internal cavity, wherein the outer wall has an original portion removed therefrom to expose the internal cavity, and, an internally cooled supplemental element joined to the outer wall that replaces the original portion removed from the outer wall and re-encloses the internal cavity. The internally cooled supplemental element comprises one or more cooling channels that circulate air from the internal cavity through at least a portion of the internally cooled supplemental element.

Abstract: A thermally actuated assembly for a gas turbine assembly for a gas turbine system includes a heat transfer component having a first portion and a second portion, wherein the first portion is disposed within a first cavity having a first temperature and the second portion is disposed in a second cavity having a second temperature, wherein the heat transfer component extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element disposed within the second cavity and in operable communication with the heat transfer component. Further included is a flow manipulating device disposed within the second cavity and configured to displace in response to a temperature change in the first cavity.

Abstract: A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Abstract: The present application provides a hot gas path component for use in a hot gas path of a gas turbine engine. The hot gas path component may include an internal wall, an external wall facing the hot gas path, an impingement wall, a number of internal wall pedestals positioned between the internal wall and the impingement wall, and a number of external wall pedestals positioned between the external wall and the impingement wall.

Abstract: A gas turbine stator component includes a composite, segmented ring made up of an annular array of arcuate segments, each having end faces formed with respective seal slots, with radial gaps formed between opposed end faces of adjacent arcuate segments. A seal is located between each pair of opposed seal slots to thereby seal the gaps, and a channel is provided in each of said arcuate segments adapted to be supplied with cooling air, the channel connecting to a passage extending between the channel and a respective one of the seal slots or radial gaps, on a lower-pressure side of the seal.

Abstract: A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.

Abstract: Provided is a seal air supply system including: a seal air compressor 73 provided separately from an exhaust gas turbine turbocharger 27 to generate compressed air; a seal air supply passage 77 through which the compressed air is supplied to a seal air supply part 79 as seal air of the exhaust gas turbine turbocharger 27; and a surplus air inlet passage 81 bifurcating from the seal air supply passage 77 and guiding surplus air of the seal air to an outlet side of an intake gas compressor 27a of the exhaust gas turbine turbocharger.

Abstract: A system and method to cool the air inside the nacelle and the heat generating components, particularly of an offshore wind turbine is presented. The ambient air first enters an air handling unit near the tower bottom where the airborne water droplets and salt particles are removed. The clean air is then compressed adiabatically, thus increasing the dew point temperature of the water vapor in the air. The high pressure, high temperature air from the compressor is then cooled and dehumidified in a sea water-to-air heater exchanger or an air-to-air heat exchanger. The high pressure air from the heat exchanger then enters the turbine at the tower bottom and flows up to the nacelle where it is allowed to expand adiabatically in a duct. The duct helps direct the resulting cold air over the heat generating components. The cold air can also used to cool these components internally. The warm air ultimately exits the nacelle at the rear top.

Abstract: A heat exchanger assembly in one embodiment includes an inlet, an outlet, and a core. The inlet is configured to accept a fluid to be cooled and the outlet is configured to provide an exit for a flow of the fluid that has been cooled. The core includes at least one passageway formed therein configured for passage of the fluid to be cooled from the inlet to the outlet. The core also includes a receiving surface configured to receive a cooling flow therethrough. The core is configured to direct the cooling flow to pass by at least a portion of the at least one passageway to cool the fluid. The core is comprised of a high temperature geopolymer composite material. The composite material may be configured for use at temperatures above about 300 degrees Celsius, and may have a thermal conductivity below about 20 Watts/(meter*degree Kelvin).

Abstract: A lube oil supply system of a turbine system and method of regulating lube oil temperatures. In one embodiment, the system includes a first valve positioned on a lube oil bypass conduit in fluid communication with a lube oil supply line to a heat exchanger. The first valve may be positioned in parallel with the heat exchanger. The system may also include a second valve positioned on a cooling fluid supply line in fluid communication with the heat exchanger, and a lube oil control system operably connected to the first valve and the second valve. The lube oil control system may be configured to modify a position of at least one of the first valve, or the second valve in response to determining a temperature of a lube oil of the lube oil supply line differs from a predetermined lube oil temperature threshold.

Abstract: A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.

Abstract: A structure in a gas turbine engine comprises a spar and a CMC component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air.

Abstract: A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn.

Abstract: An apparatus and method for cooling a dual, walled component is disclosed herein. An augmented cooling system according to the present disclosure includes transporting a cooling fluid through one wall of a cooling pathway formed between two opposing spaced apart walls of the dual walled component. The cooling fluid can be deflected away from one wall of the cooling pathway with a first trip strip as the cooling fluid traverses along the cooling pathway. The cooling fluid can be deflected away from the opposing wall of the cooling pathway with a second trip strip as the cooling fluid continues traversing along the cooling pathway. The cooling fluid can then be discharged from the cooling pathway through the opposing wall of the dual walled component.

Abstract: One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

Abstract: A turbine airfoil for a turbomachine is provided. The airfoil includes a suction side wall and a pressure side wall bordering an airfoil cavity, which receives a cooling fluid for cooling the airfoil. The suction side wall includes one or more protrusions extending inside the cavity. The number of protrusions on the suction side may be higher than the number of protrusions on the pressure side. The density of protrusions on the suction side may be higher than the density of protrusions on the pressure side and/or the surface of protrusions on the suction side may be larger than the surface of protrusions on the pressure side, so that heat transfer from the suction side to the cooling fluid is higher compared to heat transfer from the pressure side to the cooling fluid during operation of the turbomachine.

Abstract: A turbine assembly having a hollow aerofoil and impingement device, the aerofoil having a first side wall from leading to trailing edge and a cavity arranged a distance to an inner surface of the cavity for impingement cooling and a flow channel for cooling medium from the leading to trailing edge, the impingement device has first and second pieces arranged side by side, the second piece downstream of the first forming a first flow passage providing passage from one side of the aerofoil towards an opposite side. A blocking element is arranged in the flow channel between the second piece and first side wall at a suction side for blocking flow of cooling medium from leading to trailing edge denying access to a section of the flow channel downstream of the blocking element while directing cooling medium in the first flow passage away from the suction side towards pressure side.