Abstract: A hydraulic bearing is provided for a stationary gas turbine that has an oil sump with an outflow for hydraulic oil, wherein the outflow has an outflow opening which is arranged in the oil sump and an outflow line which is connected to the outflow opening. The hydraulic bearing is adapted to bring about an annular flow with a central air column when hydraulic oil flows out in the outflow line.

Abstract: A fan assembly includes a motor-driven impeller for creating an air flow, at least one heater for heating a first portion of the air flow, a surface diverting a second portion of the air flow away from said at least one heater, and a casing comprising at least one first air outlet for emitting the first portion of the air flow and at least one second air outlet from emitting the second portion of the air flow. To cool an external surface of the casing, at least one second air outlet is arranged to direct at least part of the second portion of the air flow over the external surface.

Abstract: A gas turbine engine with a geared architecture includes a multiple of bearing compartments and at least one carbon seal that seals at least one side of each of the multiple of bearing compartments.

Abstract: A high pressure compressor includes an inner case wall, a plurality of flanges extending outwardly from the inner case wall, a shield that surrounds at least a portion of at least one of the plurality of flanges to define a chamber that at least partially encases at least one of the plurality of flanges, and a passage at least partially defined by the shield that allows air to circulate into the chamber.

Abstract: The present disclosure is applicable to all gear trains using a journal bearing as a means of supporting gear shaft rotation. It is related in some embodiments to a system and method for supplying lubricant to the journal bearings of a gear-turbofan engine gear train when the fan rotor is subjected to a wind-milling condition in both directions, either clockwise or counter-clockwise.

Abstract: A system includes a radiation detector array directed toward a fluid flow into a compressor. The radiation detector array is configured to output a signal indicative of a two-dimensional temperature profile of the fluid flow. The system also includes a controller communicatively coupled to the radiation detector array. The controller is configured to detect a temperature variation across the fluid flow based on the signal, and to adjust a parameter of a temperature control device to compensate for the detected temperature variation.

Abstract: A switchgear cabinet for a wind turbine has a cabinet housing with a ventilation hole defined therein. A fan is disposed in the cabinet housing and supported on the cabinet housing so as to be disposed in front of or in the ventilation hole. A circumferential coaming is disposed on the outer side of the cabinet housing surrounding the ventilation hole. A pan-shaped cover has a closed front and a rim. The cover is disposed over the coaming with the rim extending around the coaming. The cover is spaced from the coaming so as to define at least one air-permeable connection between the fan and the surroundings of the cabinet.

Abstract: A method of operating a turbine assembly is provided. The method includes receiving a flow of air at a filter house that includes a first heat exchanger. The temperature of the air is controlled with the first heat exchanger by one of selectively cooling the air and by selectively heating the air. The air is then channeled from the first heat exchanger to a second heat exchanger to facilitate cooling the air.

Abstract: A cooling apparatus of an array of fan cradles holding fans where a movable baffle assembly directs airflow and blocks removal of more than one fan at a time. A plurality of fans held in a fan cradle assembly in which the fan cradle for a fan to be replaced mechanically moves and is engaged with the movable baffle assembly to prevent removal of the other fans. A method is provided by which an operator may remove and replace an existing fan in an array of fans.

Abstract: A device and method feeding turbomachines with lubricant, the turbomachine including a first set of bearings and a second set of bearings. Both the first and the second sets of bearings are fed with lubricant, and the second set of bearings operate at a temperature higher than the first set. The second set of bearings is fed with lubricant at a temperature higher than the first set.

Abstract: The present invention relates to a turbine blade of a gas turbine with an airfoil arranged on a blade root and having at least one cooling air duct running in the longitudinal direction of the turbine blade, arranged inside the turbine blade and extending through the blade root, characterized in that at least one swirl-generating element is arranged in the transitional area between blade root and airfoil in the cooling air duct, with the swirl-generating element including an outer ring and several swirl-generating stator vanes arranged thereon, which are connected to a centric area, as well as to a method for its manufacture.

Abstract: The present invention provides an apparatus for maintaining the operation of a geothermal production pump which comprises one or more impellers and a vertical line shaft for driving said one or more impellers, comprising a liquid buffer for isolating a discharge column through which pumped geothermal fluid including non-condensable gases flows from a lubrication column through which oil for lubricating one or more bearings of the line shaft flows, the liquid buffer being interposed between the discharge column and an outlet of the lubrication column to prevent infiltration of the non-condensable gases into the lubrication column.

Abstract: An isothermal turbo-compressor-condenser-expander arrangement includes heat-transferring blades that are mounted on, or surround, individual conduits to promote air exchange and heat transfer. In operation, the open framework rotates in free air to promote heat exchange. The assembly includes a first plurality of spokes extending radially outwardly from a first central hub to an outer perimeter with first radial conduits that transport refrigerant under centrifugal force and compression from the hub to the outer perimeter. The first radial conduits include heat exchanging blades. A second plurality of spokes extend radially outwardly from a second central hub that each includes a second thermally-insulated conduit that transports refrigerant from the outer perimeter to the second central hub. Axial conduits extend axially at the outer perimeter. At least some of the axial conduits include an axial blade in thermal communication with the conduit that promotes heat exchange radially.

Abstract: A turbine assembly having a bladed turbine wheel and a turbine casing (1000), extending axially of the turbine assembly, radially outwardly surrounding the tips of the blades of the turbine wheel, the casing having at least one radially outwardly extending dummy flange (2100, 2200) off which, in axial direction, one or more cooling manifolds (1100, 1200, 1300), wrapping radially outwardly around the casing, are mounted, the or each cooling manifold being adapted to receive cooling air and to discharge the cooling air radially inwardly towards the casing, for cooling the casing.

Abstract: An impingement plate is cooperable with a shroud assembly. The shroud assembly includes an outer shroud and plural inner shrouds with seals between the plural inner shrouds, respectively. The impingement plate includes a trailing edge portion, a leading edge portion and a mid portion between the trailing edge portion and the leading edge portion. A plurality of impingement holes are formed across an area of the impingement plate, and a cooling and damping section includes at least one channel that is shaped to accelerate cooling flow through the impingement plate.

Abstract: Disclosed is a power generation system and method. The system includes a combustor, and a turbine driven by products of the combustor. The turbine includes at least one disk supporting a plurality of airfoils, and the airfoils each have an internal passage formed therein. The system further includes a passage for routing a coolant within the system. A portion of the passage is provided by the internal passages of the airfoils, and another portion of the passage is provided between the airfoils and the combustor. The system also includes a generator driven by the turbine to generate electric power.

Abstract: Cooling channels through the interior of a machine component that include: a first set of cooling channels, the first set of cooling channels including a plurality of parallel channels that reside in a first plane; a second set of cooling channels, the second set of cooling channels including a plurality of parallel channels that reside in a second plane. Along a longitudinal axis, the cooling channels of the first and second set of cooling channels may include an alternating diverging-converging configuration, the alternating diverging-converging configuration creating a series of broader chamber sections connected by a series of narrower throat sections. The first set of cooling channels and the second set of cooling channels may be configured such that, when viewed from the side, a crisscrossing pattern with a plurality of intersections is formed.

Abstract: A heat exchanger apparatus includes: (a) an airfoil having opposed pressure and suction sides, a root, a tip, and spaced-apart leading and trailing edges; and (b) a plenum integrally formed within the airfoil which is configured to receive a flow of circulating working fluid; and (c) inlet and outlet ports communicating with the plenum and an exterior of the airfoil.

Abstract: A gas turbine including exhaust chamber defined by a cylindrical casing wall and a bearing case that supports a bearing part of a rotor in the casing wall, struts provided at equal intervals in circumferential direction of the bearing case and extending in tangential direction of the bearing case to couple the casing wall and the bearing case, a diffuser unit having an outer diffuser at the inner periphery of the casing wall and an inner diffuser at the outer periphery of the bearing case, a cooling chamber in which the outer diffuser and the inner diffuser are coupled by a strut cover, led to a portion between the casing wall and the outer diffuser, a portion between the bearing case and the inner diffuser, and the insides of the strut cover, and a partition wall that covers the outer periphery of the bearing case.

Abstract: This wet compression invention with a vaporizable fluid mist demonstrates major performance improvements over the relevant art in achieving a high degree of saturation, providing sensible cooling, strongly reducing the temperature increase due to compression work, reducing excess diluent air flow for downstream combustion, reducing compression noise, and increasing the achievable compressor pressure ratio.

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 method and system to prevent the equipment corrosion in an offshore wind turbine by minimizing the humid ambient air entry into the turbine. The method uses the fact that the ambient air entry into or the inside air leakage out of the turbine can be minimized by lowering the air pressure difference across the outside and inside faces of the seals. The proposed system includes a slotted, streamlined plenum over each of these interfaces that helps moderate the air pressure on the outside of the seals. On the inside, the air pressure over the seals is controlled by a variable air flow resistance system that consists of two circular, coaxial perforated plates that can rotate relative to each other.

Abstract: A turbine shroud cooling assembly for a gas turbine system includes an inner shroud component disposed within a turbine section of the gas turbine system and proximate a hot gas path therein, wherein the inner shroud component includes a base portion in direct contact with the hot gas path. Also includes is a rib protruding radially away from the base portion and disposed proximate at least one cavity configured to receive a cooling flow from a cooling source, wherein the cooling flow passes through the main passage of the rib for cooling the inner shroud component.

Abstract: Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces.

Abstract: The present invention combines the principles of a gas turbine engine with an electric transmission system. A method and apparatus are disclosed for utilizing metallic and ceramic elements to store heat energy derived from a regenerative braking system. The subject invention uses this regenerated electrical energy to provide additional energy storage over conventional electrical storage methods suitable for a gas turbine engine. The subject invention provides engine braking for a gas turbine engine as well as reducing fuel consumption.

Abstract: A geared architecture for a gas turbine engine includes a lubricant manifold for directing lubricant flow to the geared architecture. The manifold including annular channel and a bowl member received within the annular channel for defining a passage for directing lubricant.

Abstract: A steam turbine having an exhaust-steam casing for directing an exhaust-steam mass flow, a shaft bearing for mounting a turbine shaft, and at least two bearing struts, by means of which the shaft bearing is fastened to the exhaust-steam casing, is characterized according to the invention in that each of the at least two bearing struts has a cooling cavity arranged in the respective bearing strut for directing a coolant, and the cooling cavities of the at least two bearing struts are connected in a fluidically conductive manner via a closed-off connecting cavity in the region of the shaft bearing.

Abstract: A turbine system is provided wherein during self-sealing operating conditions, excess leakoff steam is restricted from being dumped to a steam seal header and is diverted into the working steam flow path, hence increasing net output and efficiency for the turbine system. A related method is also provided.

Abstract: A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.

Abstract: A multi-pieces gas turbine engine combustor heat shield is fabricated from sheet metal. The fabrication involves: sheet metal forming a base sheet having opposed hot and cold facing sides, providing cold side details separately from the base sheet, and mounting the cold side details to the cold facing side of the base sheet. The cold side details may be brazed to the base sheet.

Abstract: A turbocharger includes a housing, a rotating assembly mounted within the housing, a lubrication passage for admitting lubricating oil into the turbocharger, and a lube oil filter, mounted within a portion of the lubrication passage so that oil entering the turbocharger will pass through the lube oil filter, removing any contaminants arising from the engine's lubrication system.

Abstract: A system and method are provided for controlling the temperature of engine bleed air from a turbofan gas turbine engine. The system includes a fan air valve and a fan air valve controller. The fan air valve is adapted to receive a flow of fan air from a turbofan gas turbine engine intake fan. The fan air valve is coupled to receive valve position commands and is configured, in response to the valve position commands, to move to a valve position to thereby control the engine bleed air temperature. The fan air valve controller is configured to implement a linear quadratic regulator (LQR) control. The fan air valve controller is adapted to receive a plurality of sensor signals, each sensor signal representative of one or more system parameters, and is configured, in response to the sensor signals, to supply the valve position commands to the fan air valve.

Abstract: A cooling system provided for a motor powering a compressor in a vapor compression system. The cooling system includes a housing enclosing the motor and a cavity located within the housing. A fluid circuit has a first connection with the housing configured to provide a liquid or two phase cooling fluid to the motor. The two phase cooling fluid is separable into a vapor phase portion and a liquid phase portion. The fluid circuit further has a second connection with the housing to remove cooling fluid in fluid communication with the fluid circuit. The cooling fluid conveyed through the second connection is two phase cooling fluid. The fluid circuit further has a third connection with the housing for receiving and circulating in the cavity the vapor phase portion conveyed through the second connection.

Abstract: A turbocharger for an internal combustion engine includes a bearing housing with a bearing bore and a semi-floating bearing disposed within the bore. The turbocharger also includes a shaft having a first end and a second end, wherein the shaft is supported by the bearing for rotation about an axis within the bore. The turbocharger also includes a turbine wheel fixed to the shaft proximate to the first end and configured to be rotated about the axis by post-combustion gasses emitted by the engine. Additionally, the turbocharger includes a compressor wheel fixed to the shaft proximate to the second end and configured to pressurize an airflow being received from the ambient for delivery to the engine. Furthermore, the turbocharger includes a plate secured within the bearing housing and configured to prevent rotation of the bearing about the axis. An internal combustion engine employing such a turbocharger is also disclosed.

Abstract: A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portion. A labyrinth seal device serves to suppress the amount of steam leaking from a clearance present between each stator blade (fixed portion) of the steam turbine and a rotor (rotating portion). The seal structure for the steam turbine is formed to ensure that permeable spacers made of a permeable metal are provided on the rotor and a seal stationary body and face respective seal fins provided in the labyrinth seal device.

Abstract: A ring segment for a turbine in an industrial gas turbine engine, the ring segment having an inner side with a number of pedestals extending radially inward, each pedestal having an inlet metering hole connected to a diffusion chamber having an opening flush with a TBC covering the pedestals. The pedestals form a larger surface area to secure the TBC to the ring segment so that the TBC can be formed thicker than the prior art without spalling.

Abstract: Combined bleed air and hot section component cooling air systems for gas turbine engines and methods of operating combined bleed air and hot section component cooling air systems are disclosed. An example system may include a high-pressure bleed air line receiving high-pressure bleed air; a precooler receiving at least some of the high-pressure bleed air and discharging cooled high-pressure bleed air; a pressure regulator receiving at least some of the cooled high-pressure bleed air and discharging pressure-regulated cooled bleed air to a pneumatic systems supply line; and/or a hot section component cooling air line connected upstream of the first pressure regulator and configured to convey at least some of the cooled high-pressure bleed air to a hot section component for use as hot section component cooling air.

Abstract: A variable capacity core type heat exchanger unit, may include a heat exchanger heat-exchanging high-temperature cooling water, a reservoir tank in which the high-temperature cooling water is inputted and thereafter, transmitted to the heat exchanger and the low-temperature cooling water is inputted and thereafter, discharged to the engine and the electric system, wherein the reservoir tank includes an introduction space and a discharge space, and an actuator module installed to the reservoir tank and controlled by a controller, varying the introduction space through which the high-temperature cooling water is inputted into the heat exchanger and the discharge space through which the low-temperature cooling water is discharged from the heat exchanger, wherein the variation in the introduction space is associated with the variation in the discharge space.

Abstract: A blower housing of a hydrogen recirculation device for a fuel cell vehicle includes a plurality of cooling pins installed on a perimeter of a housing body installed in a fuel processing system of the recirculation device. The cooling pins are arranged in parallel with air flow, thereby reducing a temperature deviation and the highest temperature point.

Abstract: An anti-vortex device for use in a compressor rotor assembly of a gas turbine engine is described. Spaced-apart radial passageways extend from an axially extending passage provided in a central area of the device to an outer peripheral rim surface thereof. The radial passageways channel air from the primary gaspath about the rotor assembly to the axially extending passage where the air is directed into a central axial passage of the rotor assembly.

Abstract: A pump assembly to move water past a reverse osmosis membrane, the pump assembly having a first pump and a second pump each including a bore having a longitudinal axis and surrounding a chamber. First and second partition members extend longitudinally of the chamber. The second partition is moveable relative to the first partition member, and divides the chamber into a first sub chamber and a second sub chamber. A shaft is attached to the second member to cause angular movement thereof about the axis to change the volumes of the sub chambers. End caps are fitted to ends of each chamber to contain pressure, and ducting is provided to provide for the flow of water. The shaft of the first pump is coupled to the shaft of the second pump so that the first pump second partition angularly oscillates in phase with the second pump second partition.

Abstract: A feed line for connecting an oil pump to a turbocharger supplies oil to the turbocharger when the oil pump is active. The feed line includes a turbo end and a pump end, which is lower than the turbo end relative to gravity. Oil drains from at least the pump end of the feed line when the oil pump is not active. The feed line has a center axis running therethrough, and a pool zone is disposed between the pump end and the turbo end of the feed line. The center axis of the feed line drops from a main line level on either side of the pool zone to a trap level in the pool zone. The pool zone therefore retains oil when the oil pump is not active.

Abstract: A turbomachine includes a housing having an outer surface and an inner surface that defines an interior portion. The housing includes a fluid plenum. A rotating member is arranged within the housing. The rotating member includes at least one bucket having a base portion and a tip portion. A stationary member is mounted to the inner surface of the housing adjacent the tip portion of the at least one bucket. At least one fluid passage passes through at least a portion of the stationary member. The at least one fluid passage includes a fluid inlet fluidly coupled to the fluid plenum and a fluid outlet exposed to the interior portion. The fluid outlet being configured and disposed to direct a flow of fluid toward the tip portion of the at least one bucket.

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 ram air fan inner housing for a ram air fan assembly comprises a center body housing, an end cup attached to the center body housing, and a perforated cone. The perforated cone is attached to the center body housing and the end cup such that the perforated cone extends away from the center body housing and radially inward toward an axis of the inner housing.

Abstract: A compressor assembly having an air ducting shroud that can direct a cooling air stream from a fan to components of the compressor assembly, such as a pump assembly. The pump assembly can have at least a pump, a motor and a fan. The compressor can be cooled by providing cooling air to a cylinder head of the pump without the cooling air experiencing choking or substantial cooling flow interference from a cooling of the motor.

Abstract: A rim seal assembly includes an annular seal element circumscribing an engine centerline or axis and mounted on an annular platform including a radially inwardly extending annular platform flange disposed between and connected to forward and aft flanges at distal ends of forward and aft annular elements respectively. Annular forward and aft outer rim cavities radially disposed between the forward and aft annular elements and the platform are axially separated by the platform flange. Cooling slots extend radially across axially facing forward and aft surfaces of the forward and aft flanges. The platform flange and the forward and aft flanges are bolted together. The annular seal element may include seal teeth in sealing relationship with an annular seal land such as in a labyrinth seal. The rim seal assembly may be incorporated in a low pressure turbine use a compressor as a source of cooling air.

Abstract: In one embodiment, a system includes a seal having a first sealing end portion, a second sealing end portion, and an intermediate portion between the first and second sealing end portions, wherein the seal has at least one metering hole configured to control a leakage flow across the seal.

Abstract: A system includes a turbine casing including a first hook configured to mate with a second hook to support a turbine shroud about a plurality of turbine blades. The turbine casing includes a coolant circuit configured to adjust clearance between the turbine shroud and the turbine blades based on coolant flow through the coolant circuit. The coolant circuit includes a first plurality of radial coolant passages extending into the first hook.

Abstract: A twin scroll exhaust gas turbocharger for an internal-combustion engine, includes a turbine housing and a first and a second gas inlet port separated from one another by the turbine housing. The inlet ports lead into a first and a second spiral duct, respectively, which extend radially on the outside around an exhaust gas turbine rotatable about an axis. The gas inlet ports are arranged at least in sections parallel to one another in the turbine housing and radially with respect to the axis of rotation in a mutually spaced manner. The first spiral duct, which connects to the first gas inlet port arranged closer to the axis of rotation, extends up to 180° around the exhaust gas turbine. The second spiral duct, which connects to the second gas inlet port farther away from the axis of rotation, extends up to 180° around the remaining circumference of the exhaust gas turbine. As a result, thermal stress to the turbine housing is significantly reduced.