| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415180000 | Cooling fluid contacts shaft, seal or bearing | 49 |
| 20090175718 | SYSTEM AND METHOD FOR PASSIVE COOLING OF GAS TURBINE ENGINE CONTROL COMPONENTS - A system for cooling a gas turbine engine control component comprises a control component, at least one duct in fluid communication with the component and the atmosphere, and a valve assembly located with the duct for modulating airflow to the component. A method for cooling a gas turbine engine control component comprises the steps of: a) providing a system for cooling the component, the system comprising at least one duct in fluid communication with the component and the atmosphere and a valve assembly located with the duct for modulating airflow to the component; b) exposing the system to a first condition where cooling of the component is required; c) opening the valve assembly in response to the first condition; d) exposing the system to a second condition where cooling of the component is not required; and e) closing the valve assembly in response to the second condition. | 07-09-2009 |
| 20090252604 | THERMAL MANAGEMENT SYSTEM FOR A GAS TURBINE ENGINE - A thermal management system and method for a miniature gas turbine engine includes a forward cover having a filter portion along an axis of rotation of a gas turbine engine, a first lubrication passage and a second lubrication passage. | 10-08-2009 |
| 20100054927 | Steam Turbine Having Bearing Struts - 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. | 03-04-2010 |
| 20100074737 | STEAM TURBINE - A steam turbine with at least one magnetic bearing for the shaft is provided, a metal paneling being attached in the area of a magnetic bearing. The metal paneling consists of metal rings insulated from one another. Further, cooling air ducts are provided in the area of the magnetic bearing. | 03-25-2010 |
| 20100111681 | BEARING DEVICE OF GAS TURBINE POWER GENERATION EQUIPMENT AND GAS TURBINE POWER GENERATION EQUIPMENT - A bearing device of a gas turbine power generation equipment provides damping vibration of a shaft and lubricates and cools the bearing main body. | 05-06-2010 |
| 20100272560 | Centrifugal Pump with Improved Drive Shaft and Heat Exchanger - A high temperature centrifugal pump includes non-linear fluid flow paths between the pump housing and seal housing to reduce fluid flow therebetween. In another aspect, the invention provides a drive shaft of variable diameter to compensate for different amounts of thermal expansion to maintain a more consistent gap profile between the drive shaft and thermal insulators or other components positioned around the drive shaft. In yet another aspect, a tube heat exchanger may be placed in fluid communication with the seal housing to re-circulate and cool the fluid therethrough. | 10-28-2010 |
| 20100278642 | BYPASS LIP SEAL - A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open upstream end and an open downstream end to direct a portion of the bypass air flow to pass therethrough. A sealing assembly for the bypass duct is also provided. | 11-04-2010 |
| 20100296920 | TURBOCHARGER COMPRISING A COOLING DEVICE AND AN OIL SUPPLY PIPE - A turbocharger, especially a turbocharger for a motor vehicle, has a turbine housing and a bearing housing. The turbine housing and the bearing housing are fitted with a common cooling device. The turbine housing includes a flange for attaching to an exhaust gas manifold. The flange is formed with a coolant inlet, a coolant outlet, and an oil supply pipe. | 11-25-2010 |
| 20100322759 | STRUCTURE OF EXHAUST SECTION OF GAS TURBINE AND GAS TURBINE - There is provided an exhaust section of a gas turbine and a gas turbine that can cool a strut and the periphery of a bearing without decreasing the efficiency of the gas turbine. A structure of an exhaust section of a gas turbine has: a casing in which a gas path part is formed; a bearing part that rotatably supports moving blades of a turbine section; a strut that extends inwardly from the casing and supports the bearing part; an opening formed in the casing; and a cooling flow channel that extends from the opening toward the bearing part along the strut to guide air at a lower temperature than an exhaust gas flowing in the gas path part to the gas path part and opens into the gas path part at a position downstream of a last-stage moving blade of the turbine section. | 12-23-2010 |
| 20110020115 | REFRACTORY METAL CORE INTEGRALLY CAST EXIT TRENCH - A refractory metal core for use in casting a turbine engine part has a main portion and a plurality of tabs extending from the main portion. An end portion having a first edge which joins together the plurality of tabs and a second edge, opposed to the first edge, located internally of an exterior boundary of the cast part may be provided. | 01-27-2011 |
| 20110020116 | GAS TURBINE - 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. | 01-27-2011 |
| 20110052377 | GAS-TURBINE INLET-AIR COOLING SYSTEM - A gas-turbine inlet-air cooling system includes: a spray device configured to spray cooling water into inlet air entered into a compressor of a gas turbine facility to thereby cool the inlet air; and a cooling-water feed system configured to supply the cooling water to the spray device. The cooling-water feed system including: at least one tank configured to reserve the cooling water; a plurality of pipes connected to the tank independently of each other and configured to feed the cooling water to the spray device; and pumps installed for the pipes, respectively. | 03-03-2011 |
| 20110070076 | COOLING SYSTEMS AND ASSEMBLIES FOR COOLING AN AFT BEARING ASSEMBLY MOUNTED TO A ROTOR - Assemblies for cooling an aft bearing assembly mounted to a rotor are provided. An assembly includes a static aft bearing structure configured to surround the aft bearing assembly and including a cylindrical section defining a cavity for disposal of the aft bearing assembly, a plurality of hollow struts extending from the static aft bearing structure, each hollow strut including an outer radial end configured to receive a gas from an air source and to provide a pathway for the gas to flow into the cavity, and a center-body cap disposed over an end of the static aft bearing structure, the center-body cap including a rim configured to create a low pressure region at an interface between the static aft bearing structure and the center-body cap, wherein the low pressure region has a pressure that is lower than a pressure within the cavity. | 03-24-2011 |
| 20110091314 | FAN STRUCTURE - A fan structure includes a base having a receiving section; a sleeve defining a receiving space therein, and having a shaft hole communicating with the receiving space and an engaging end for engaging with the receiving section of the base; a bearing having an axial bore and received in the sleeve; and an insulating rack externally fitted around the sleeve and having a holding section for holding at least one silicon steel plate set therein, which is spaced from the sleeve by at least one first space. With these arrangements, heat produced by the silicon steel plate set during fan operation is isolated by the first space from directly damaging the bearing. | 04-21-2011 |
| 20110129336 | ASSEMBLY INCLUDING A TURBINE DISK FOR A GAS TURBINE ENGINE AND A BEARING-SUPPORTING JOURNAL, AND COOLING CIRCUIT FOR THE TURBINE DISK OF SUCH AN ASSEMBLY - The invention relates to an assembly including a turbine disk ( | 06-02-2011 |
| 20110135456 | GAS TURBINE PLANT - Provided is a gas turbine plant that enables active clearance control for ensuring tip clearance of first-stage turbine rotor blades required during start-up and for achieving the minimum tip clearance during load operation. In a gas turbine plant including a cooler in an air system used for cooling second-stage turbine stator blades, a first-stage segmented ring and a second-stage segmented ring that oppose tips of first-stage turbine rotor blades and second-stage turbine rotor blades are supported by the same blade ring member, and a cooling-air for the second-stage turbine stator blades forms a cooling air flow cooling the blade ring, to control thermal expansion of the blade ring and to control the clearance with respect to the tips. | 06-09-2011 |
| 20110171013 | SHROUD SEAL SEGMENTS ARRANGEMENT IN A GAS TURBINE - A gas turbine is provided that includes a rotor which is rotatable around an axis and equipped with rotor blades, and which is concentrically enclosed at a distance by a casing, which is equipped with stator blades, forming an annular hot gas passage. Rings with stator blades and rotor blades are arranged in a manner alternating in the axial direction. Between adjacent stator blades, heat shield segments are arranged, which delimit the hot gas passage on the outside in a region of the rotor blades and are cooled by impingement cooling where a cooling medium from an outer annular cavity flows into the heat shield segment. | 07-14-2011 |
| 20110182724 | COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE - A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region which are disposed adjacent to the end portion on a rear side in a rotation direction, and cooling passages of a second region which are disposed on a farther front side in the rotation direction than the first-region cooling passages and have a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages. The first-region cooling passages are disposed adjacent to the second cooling passages of the neighboring segment body. | 07-28-2011 |
| 20110229313 | THRUST BEARING COOLING PATH - A compressor rotor compresses and delivers compressed air across a turbine rotor. The turbine rotor is connected to the compressor rotor such that rotation of the turbine rotor drives the compressor rotor. A shaft is connected to rotate with the turbine rotor and the compressor rotor. A thrust bearing is provided by a member extending perpendicular and radially outwardly of the shaft. The member rotates with the shaft and faces a first housing wall. A hollow chamber is formed on an opposed side of the first housing wall. A cooling air path supplies air across a thrust bearing surface, and between the member and the first housing wall. The first housing wall has a communication hole for communicating cooling air from the cooling air path into the hollow cavity to drive air within the hollow chamber. Also, a housing incorporating the communication hole is disclosed. | 09-22-2011 |
| 20110236193 | TURBOCHARGER BEARING LUBRICATION - A turbocharger assembly includes a turbocharger housing, an elongated cylindrical center housing, a turbine in a turbine housing, a compressor in a compressor housing and a bearing assembly on a rotary shaft. The bearing assembly including balls, ball retainers, an inner and outer ring with raceways thereon, a lubrication port and a cooling port. The cooling port is located towards the outside of the bearing and directed away from the bearing, whereas the lubrication port is directed towards the bearing and is located towards an inside surface of the bearing. | 09-29-2011 |
| 20110250057 | RADIAL PRE-SWIRL ASSEMBLY AND COOLING FLUID METERING STRUCTURE FOR A GAS TURBINE ENGINE - A gas turbine engine comprises a pre-swirl structure coupled to a shaft cover structure and located radially between a supply of cooling fluid and a flow path. The pre-swirl structure defines a flow passage and includes a plurality of swirl members in the flow passage. A flow direction of cooling fluid passing through the flow passage is altered by the swirl members such that the cooling fluid has a velocity component in a direction tangential to the circumferential direction. The bypass passages provide cooling fluid into a turbine rim cavity associated with a first row vane assembly to prevent hot gas ingestion into the turbine rim cavity from a hot gas flow path associated with a turbine section of the engine. | 10-13-2011 |
| 20110262269 | VALVES FOR GAS-TURBINES AND MULTIPRESSURE GAS-TURBINES, AND GAS-TURBINES THEREWITH - A multiport valve suitable for use with a gas-turbine allowing switching of a mode of gas-turbine operation between a Brayton cycle and an inverse Brayton cycle, and a gas-turbine configured to switch between a high-pressure operation mode according to a Brayton cycle and a low-pressure operation mode according to an inverse Brayton cycle employing the valve are provided. Also provided are a method and apparatus for operating a gas-turbine according to an inverse Brayton cycle. | 10-27-2011 |
| 20110268564 | Gas Turbine with Securing Plate Between Blade Base and Disk - A turbine rotor is provided. The turbine rotor has a plurality of blades assembled into blade rows and arranged on a turbine disk. Each blade has a blade root arranged in a blade retaining slot of the turbine disk extending in an axial direction. A locking plate is arranged between the respective blade root and a base of the blade retaining slot, for securing blades against a displacement along the blade retaining slot. The locking plate is fixed to the turbine disk by folds. The locking plate comprises a plurality of cooling air holes for the passage of cooling medium from a cooling air feed passage. The respective blade root comprises two grooves extending substantially azimuthally in relation to a turbine axis, and the respective locking plate comprises two tongues which are arranged such that they are connected to the two grooves of the blade root for sealing. | 11-03-2011 |
| 20110305561 | WIRE SEAL FOR METERING OF TURBINE BLADE COOLING FLUIDS - A cooling fluid metering system for a turbine blade of a gas turbine engine is disclosed. The cooling fluid metering system may include a cooling channel positioned between a root of a turbine blade and an offset rotor sealing plate for supplying cooling fluids to turbine blades. At one point, a portion of the cooling channel may include a gap between the root and the offset rotor sealing plate. The gap may be sealed with teardrop shaped seal positioned within a teardrop shaped cavity at the gap. The cavity and seal may be positioned such that during operation, the seal is forced radially outward and into the gap, thereby effectively metering cooling fluid flow through the cooling channel. | 12-15-2011 |
| 20120003081 | Air-cooled turbocharger with optional internal pressure relief valve - A cooling system for a turbocharger that has a cooling jacket in the bearing housing wherein air is bled from the area behind the compressor wheel and introduced into the cooling jacket, through which it circulates and then exits into the atmosphere. In addition, a pressure relief valve located behind the compressor wheel is set to open at a predetermined charge air pressure level to introduce additional cooling air into the cooling jacket and also acts to limit the maximum rotational speed of the turbocharger over the high-speed range of the engine on which the turbocharger is mounted. In an alternate embodiment of the invention, cooling air can be taken from the intake manifold system of a turbocharged engine downstream of an air-to-air aftercooler and ducted to the cooling jacket in the turbocharger bearing housing. | 01-05-2012 |
| 20120003082 | COOLING DEVICE OF TURBOCHARGER OF ENGINE FOR VEHICLE - There are provided first and second water supply passages to supply cooling water from an engine to first and second center housings of first and second turbochargers, and first and second return passages to return the cooling water from the first and second turbochargers to the engine. A cooling-water connection portion of the first water supply is located above the level of a cooling-water connection portion of the second water supply passage. A vapor releasing passage is provided between the second turbocharger and an upper tank provided on the outside of an engine body at a position located above the connection portion of the second return passage of the second turbocharger. Accordingly, the function of vapor releasing from the first and second turbochargers can be improved, thereby increasing the layout flexibility around the engine. | 01-05-2012 |
| 20120057969 | RING SEGMENT WITH IMPINGEMENT AND CONVECTIVE COOLING - A ring segment for a gas turbine engine includes an outer panel defining a structural body for the ring segment. An outer side of an inner panel is attached to an inner side of the outer panel at an interface, and an inner side of the inner panel defines a portion of a hot gas path through the gas turbine engine. An outer side of the outer panel, opposite from the interface, is in communication with a source of cooling air. A plurality of impingement holes extend through the outer panel from the outer side to the inner side of the outer panel for directing impingement air to the outer side of the inner panel. The outer and inner panels define a plurality of flow channels at the interface for effecting convective cooling of the outer panel along the flow channels between the outer and inner panels. | 03-08-2012 |
| 20120076645 | ENDWALL COMPONENT FOR A TURBINE STAGE OF A GAS TURBINE ENGINE - 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. | 03-29-2012 |
| 20120087783 | SYSTEM AND METHOD FOR TURBINE COMPARTMENT VENTILATION - According to an aspect of the invention, a method for ventilating a turbine compartment is provided, the method comprising directing an air flow from an air intake to a first air conduit, transferring a first heat between the air flow and a first fluid within a heat exchange apparatus and pumping the first fluid through a fluid circuit in fluid communication with the heat exchange apparatus, wherein a portion of the fluid circuit is located underground. The method further includes transferring a second heat between the first fluid and a surrounding ground and directing a conditioned air flow from the heat exchange apparatus to a turbine compartment via a second air conduit. | 04-12-2012 |
| 20120087784 | INDUCER FOR GAS TURBINE SYSTEM - An inducer for a casing of a gas turbine system is disclosed. The inducer includes a plurality of orifices defined in the casing, the plurality of orifices disposed in an annular array about the casing, and a plurality of cartridges, each of the plurality of cartridges configured to mate with one of the plurality of orifices. Each of the plurality of cartridges includes an inlet and an outlet for flowing a cooling medium therethrough. The inducer further includes at least one flow modifier disposed in each of the plurality of cartridges for modifying the flow of the cooling medium through each of the plurality of cartridges. Each of the plurality of cartridges is independently removable from each of the plurality of orifices. | 04-12-2012 |
| 20120107105 | TURBOCOMPRESSOR ASSEMBLY WITH A COOLING SYSTEM - A turbocompressor assembly is provided, which is divided along a rotor axis into at least three sections. The three sections include a bearing section having an active magnetic bearing, a motor section including a motor having a stator arranged along the rotor axis, the stator enclosing a circumferential motor gap formed between the stator and the rotor, and a compressor section having a compressor for compressing a cooling fluid. A gas-tight housing encloses the rotor, the bearing section, the motor section and the compressor section. A cooling system is provided having an inlet for supplying the pressurized cooling fluid to the bearing section and the motor section through a fluid channel positioned between the bearing section and the motor section. The cooling system includes a throttling device positioned adjacent to the motor gap for limiting the flow of cooling fluid from the fluid channel to the motor gap. | 05-03-2012 |
| 20120128473 | ROTATING MACHINE - A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner. | 05-24-2012 |
| 20120156014 | AIR CYCLE MACHINE BEARING COOLING INLET PLATE - An air cycle machine includes a housing, and a shaft rotationally supported within the housing includes a thrust runner. Air bearings are provided on either side of the thrust runner. An inlet plate is arranged radially outward of the air bearings. The inlet plate has inner and outer peripheries provided between lateral sides. One side includes four circumferentially arranged slots extending from the outer periphery to the inner periphery and having a width and a depth providing a first ratio of 4:1. | 06-21-2012 |
| 20120321451 | Bearing Housing Cooling System - A cooling system for the rear bearing capsule of a turbine in a gas turbine engine supported by an exhaust cone attached to multiple exit guide vanes that extend radially from the exhaust cone to an exhaust housing, comprises: an inlet air flow path through each guide vane between a source of cool ambient air and the rear bearing capsule; and at least one discharge air flow path that receives air from the inlet air flow path through each guide vane and passes the air through the exhaust cone from the rear bearing capsule to a high velocity gas flow path in the exhaust housing. | 12-20-2012 |
| 20120321452 | PRESSURE AND TEMPERATURE ACTUATION SYSTEM - A pressure and temperature actuation system is provided having a high-temperature low-pressure zone, a low-temperature high-pressure zone, a boundary, a pressure actuated mechanism, and a temperature mechanism. A gas located in the high-temperature low-pressure zone has a greater gas temperature than the gas located in the low-temperature high-pressure zone. The gas located in the low-temperature high-pressure zone has a greater gas pressure than the gas located in the high-temperature low-pressure zone. The boundary separates the high-temperature low-pressure zone from the low-temperature high pressure zone. The pressure actuated mechanism is located within the boundary and is configured for opening at a specified gas pressure in either the high-temperature low-pressure zone or the low-temperature high-pressure zone. The temperature actuated mechanism is located within the boundary and is configured for opening at a specified gas temperature in either the high-temperature low-pressure zone or the low-temperature high-pressure zone. | 12-20-2012 |
| 20120321453 | NON-MECHANICALLY FASTENED TOBI HEAT SHIELD - A high pressure turbine includes a stator, a rotor, a tangential on-board injector, and a heat shield. The rotor is located downstream of the stator and the tangential on-board injector directs cooling air to the rotor. The heat shield is retained by abutment with the stator and the tangential on-board injector. | 12-20-2012 |
| 20130058769 | COMPRESSOR END HEAD HEATING ARRANGEMENT - A compressor end head for providing a thermal barrier near a mechanical seal includes an inner end head and an outer end head. The outer end head includes an opening in the center for enclosing the inner end head, an outlet and grooves alongside surfaces radially adjacent the opening. The inner end head has an opening in the center, an inlet, grooves in the opening for enclosing an end portion of a compressor shaft and a flow path along an outer surface. | 03-07-2013 |
| 20130071236 | COOLING AND CLIMATE CONTROL SYSTEM AND METHOD FOR A WIND TURBINE - A system to cool the air inside a nacelle of a wind turbine including the heat generating components such as the drivetrain, the electrical generator, the converter, and the transformer. The system has an upper cooling circuit, with a reservoir disposed below the nacelle. The reservoir has at least one pair of annular chambers and a lid that freely rotates about its axis and about the nacelle yaw axis. Coolant flows from a first annular chamber to a second annular chamber through a heat exchanger in the nacelle, thereby carrying heat from the nacelle to the second annular chamber. The system also has a lower cooling circuit, having a coil that connects the first annular chamber to the second annular chamber and being exposed to the outside of the wind turbine. Coolant flows from the second annular chamber to the first annular chamber through the coil, thereby dissipating the heat to ambient air. | 03-21-2013 |
| 20130101402 | FAN HOUSING WITH COOLING SLOTS - A fan housing for a ram air fan includes an outer portion to connect the fan housing to ram air fan components; a tubular portion; a plurality of struts connecting the outer portion and the tubular portion; and a central disc portion inside of the tubular portion. The central disc portion comprises six cooling slots around an outer circumference. | 04-25-2013 |
| 20130170966 | TURBINE COOLING SYSTEM - A turbine cooling system is provided, having a compressor for supplying cooling air, a forward turbine rotor wheel space, a high-pressure packing seal (HPPS) bypass cavity, and a metering device. The forward turbine rotor wheel space is cooled by the cooling air supplied by the compressor. The HPPS bypass cavity is in fluid communication with and receives a portion of the cooling air from the compressor, and is in fluid communication with and supplies the cooling air to the forward turbine rotor wheel space. The metering device is in operable communication with the forward turbine rotor wheel space and the HPPS bypass cavity to modulate the cooling air supplied to the forward turbine rotor wheel space from the HPPS bypass cavity. The metering device modulates the cooling air based on at least one operating condition of the turbine. | 07-04-2013 |
| 20140072417 | TURBO-MOLECULAR PUMP - A turbo-molecular pump includes a case member, a rotor accommodated in the case member, the rotor having rotor blades arranged in multiple steps, a rotor shaft provided coaxially with the rotor, a plurality of stator blades provided on an inner surface of the case member and arranged between the rotor blades, and a plurality of spacers for supporting the stator blades. One of the plurality of spacers has a cooling thick portion for covering an outer peripheral side surface of at least one adjacent upper or lower spacer, and a cooling pipe through which a cooling medium is circulated is provided in the cooling thick portion. | 03-13-2014 |
| 20140241865 | COOLING JACKET INCLUDING A GROOVE UNIT THROUGH WHICH COOLING MEDIUM PASSES, STATOR INCLUDING A COOLING JACKET, AND ROTARY ELECTRIC MACHINE INCLUDING A COOLING JACKET - A cooling jacket capable of improving production efficiency. The cooling jacket includes a tubular main body having a first end face and a second end face, and a groove unit defining a flow channel of a cooling medium successively disposed axially on an outer periphery of the main body. The cooling jacket includes no portion located radially outward from a bottom of the groove unit between a first end portion of the groove unit located on the axial rear side of the main body and the first end face of the main body. | 08-28-2014 |
| 20150093238 | METHOD FOR MANUFACTURING TURBOCHARGER BEARING HOUSING, AND TURBOCHARGER BEARING HOUSING - There is provided a method for manufacturing a turbocharger bearing housing which can prevent a collapsible core from being damaged when molten metal is cast in the mold. The method for manufacturing a bearing housing of a turbocharger is that the bearing housing of the turbocharger is formed with a cooling passage for circulating cooling liquid by casting using a collapsible core. The collapsible core includes the end part forming portions (a one end forming portion and an other end forming portion) corresponding to the end portions of the cooling passage and having a substantially elliptical cross-section, and a fixing portion holding the end part forming portions and being embedded in a mold and fixed to the mold. | 04-02-2015 |
| 20150300202 | TURBOCHARGER - A turbocharger includes a turbine housing, a compressor housing, and a bearing housing. Each of the housings includes a passage for cooling inside. The turbocharger further includes a switching valve and a controller that switches a valve position of the switching valve. The switching valve is adapted to switch the circulation state of coolant in each passage such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing or such that the coolant is supplied from another passage to the passage of the bearing housing. The controller switches the valve position of the switching valve such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing until a predetermined amount of time passes after starting of the engine. | 10-22-2015 |
| 20150322796 | TURBINE ROTOR FOR A TURBOMACHINE - A turbine rotor for a turbomachine, including a disk containing slots for mounting vane roots, each slot being defined by two adjacent teeth of the disk, the vane roots including contact surfaces bearing on contact surfaces of the teeth of the disk. Foils are mounted on the teeth of the disk, each foil having a general U-shape including lateral bearing parts inserted between the corresponding contact surfaces of the vane roots and teeth of the disk, and a central part facing the peak of the corresponding tooth of the disk and defining a cavity between said peak and the foil. The turbine rotor also includes a device for supplying cooling air into said cavity. | 11-12-2015 |
| 20150330401 | CENTRIFUGAL STEAM COMPRESSOR AND SHAFT SEAL SYSTEM USED WITH SAME - In a centrifugal steam compressor having sealing water discharge at pressure higher than atmospheric pressure, a simple structure in which a high-pressure piping system is omitted as much as possible from a sealing water circulation system is realized. A shaft seal system | 11-19-2015 |
| 20150345510 | ROTARY MACHINE HEAT SINK - A heat sink that can be positioned around a rotating shaft includes a cylindrical body with a first end and a second end, a bore running through the body with a first opening at the first end of the body and a second opening at the second end of the body, fins extending radially outward from the body and running from the first end to the second end of the body, and channels defined between the fins and running from the first end to the second end of the body. | 12-03-2015 |
| 20160003262 | PUMP INCLUDING A SHIELD FOR PROTECTING A PUMP WHEEL AGAINST A COOLANT LEAK ALONG THE HUB OF THE WHEEL - A pump is provided. The pump includes a flow chamber for the heat-transport fluid, a pump wheel which is placed entirely in the flow chamber and which comprises a hub, a shaft for rotating the pump wheel, having an axial end section rigidly connected to the pump wheel and fitted in the hub of the pump wheel, a motor for rotating the shaft around its axis, and means for causing a coolant for cooling the driveshaft to flow, at a temperature lower than that of the heat-transport fluid, along the driveshaft. The pump also includes a shield for protecting the pump wheel against a coolant leak along an outer peripheral surface of the hub of the pump wheel, the protective shield being attached to the pump wheel. | 01-07-2016 |
| 20160169019 | SEAL RUNNER | 06-16-2016 |
