| Entries |
| Document | Title | Date |
|---|
| 20080232953 | INTER-TURBINE CASING WITH COOLING CIRCUIT, AND TURBOFAN COMPRISING IT - The invention relates to an inter-turbine casing ( | 09-25-2008 |
| 20080267767 | SEALS, SEALED SYSTEMS, AND METHODS FOR SEALING A SHAFT - In one embodiment, and by way of example only, a seal is provided for sealing a hollow shaft, where the hollow shaft has an inner surface that may be uneven due to shot peening. The seal includes an axially extending ring section having a first end, a second end, an inner surface, and a disk section disposed substantially perpendicular to the ring section inner surface between the ring section first and second ends. The seal conforms to the shaft inner surface to stop oil leakage. | 10-30-2008 |
| 20090047120 | Blade shroud with fluid barrier jet generation - A fluid flow machine has a main flow path, in which at least one row of blades ( | 02-19-2009 |
| 20090123266 | AIR SEALING ELEMENT - A turbine blade outer air seal segment assembly has a first turbine blade outer air seal segment with a first end portion, a middle portion and a second end portion. The first turbine blade outer air seal segment is for connection with a second turbine blade outer air seal segment to form at least a part of a shroud of a turbine rotor. A first cooling passage is disposed within the first turbine blade outer air seal segment. The cooling passage extends from the first end portion to the second end portion and a land is disposed in at least one of the first or second end portions. The land represents a portion for receiving a mold ejection pin for a core forming the cooling passage. | 05-14-2009 |
| 20090191046 | DEOILING DEVICE AND TURBOMACHINE COMPRISING THIS DEVICE - The invention relates to a deoiling device. It comprises a tube ( | 07-30-2009 |
| 20090252594 | High-speed air spindle - A high-speed air spindle including a spindle | 10-08-2009 |
| 20100054914 | GAS TURBINE ENGINE COMPONENT HAVING DUAL FLOW PASSAGE COOLING CHAMBER FORMED BY SINGLE CORE - A blade outer air seal for being positioned radially outwardly of a gas turbine blade has at least one cooling air passage with a dividing wall dividing the at least one cooling air passage into two separate flow paths. The dividing wall does not extend throughout an entire length of the blade outer air seal of the first dimension. | 03-04-2010 |
| 20100183426 | FLUIDIC RIM SEAL SYSTEM FOR TURBINE ENGINES - A fluidic rim seal system can be provided between a neighboring stationary and rotatable components in the turbine section of a turbine engine. For instance, the stationary component can be an inner shroud associated with a vane. The inner shroud can include a groove that extends circumferentially about the shroud. The rotatable component can be a blade cover plate. The blade cover plate can include a protrusion that culminates at a tip. One or more passages can extend through the protrusion. The passages can have an inlet in fluid communication with a coolant source and an outlet at the tip. A tip region of the protrusion is received in the groove. During engine operation, an air barrier is formed in the groove by the air discharging from the outlet. This air also provides cooling to the protrusion as well as a portion of the inner shroud. | 07-22-2010 |
| 20100189545 | Automated Seal Oil By-Pass System For Hydrogen Cooled Generators - Disclosed is a solution to automate a seal oil float trap by-pass for a hydrogen cooled generator. An automated by-pass system is coupled to an existing manual by-pass system for a float trap for a hydrogen cooled generator. The automated by-pass system includes at least one solenoid valve and a controller that controls opening and closing of the solenoid valve. The automated by-pass system can also include manual valves, orifices and limit switches. The controller activates the solenoid valve to allow the seal oil to drain. The controller can also provide a notification alarm that the hydrogen cooled generator is being purged. | 07-29-2010 |
| 20100290891 | Component Cooling Through Seals - The present application thus provides for a turbine component cooling system. The component cooling system may include a turbine component, an airflow passing adjacent to the turbine component, and a seal positioned adjacent to the turbine component. The seal may include a number of apertures so as to allow the airflow to pass therethrough. | 11-18-2010 |
| 20110014029 | SEALS FOR A TURBINE ENGINE, AND METHODS OF ASSEMBLING A TURBINE ENGINE - A side seal for sealing the side edges of adjacent combustors of a turbine engine include extended ends. The extended ends of the side seal abut and seal against inner and outer circumferential seals to prevent leakage of combustion gases. | 01-20-2011 |
| 20110064563 | HERMETIC COMPRESSOR AND METHOD OF MANUFACTURING THE SAME - A hermetic compressor includes a hermetic container arranged to store lubricating oil, a motor element accommodated in the hermetic container, an oil-feeding mechanism arranged to carry the lubricating oil, and a centrifugal pump arranged to carry the lubricating oil to the oil-feeding mechanism. The centrifugal pump includes a cylindrical portion having a hollow opening at the opening, and an aperture plate having a suction aperture formed therein. The aperture plate has an inner edge facing the suction aperture, and an outer edge of the aperture plate contacting an inner surface of the cylindrical portion. A portion of the aperture plate between the inner edge and the outer edge of the aperture plate is positioned more outward from the cylindrical portion than the inner edge and the outer edge are. This hermetic compressor does not produce fine metal powder during manufactured, having high reliability. | 03-17-2011 |
| 20110085888 | SEALING ARRANGEMENT FOR USE WITH GAS TURBINE ENGINE - A sealing member has a first portion. The first portion has a central axis, a first peripheral surface extending in a direction parallel to the central axis, and a central aperture. A first wall portion of a groove has a recess communicated with the first opening of the first channel. The recess has a second peripheral surface complementary to the first peripheral surface of the first portion of the sealing member. The first portion of the sealing member moves radially toward and away from the rotational axis as the first peripheral surface of the sealing member defines and maintains a first sealing contact with the second peripheral surface of the recess. The sealing member moves radially outwardly and thereby makes a second sealing contact surrounding the second opening of the second channel to establish a communication between the first and second openings. | 04-14-2011 |
| 20110135445 | PRESSURE BALANCED LOW-FRICTION SEAL - A pressure balance seal includes a sealing surface facing an inward radial direction, and a stator interface comprising at least one surface interfacing with a stator. The pressure balance seal further includes a friction reducing feature. The friction reducing feature includes a cavity on the sealing surface. The cavity is configured to receive a fluid such that a normal force acting on the pressure balance seal is counterbalanced by a force generated by a pressure of the fluid. | 06-09-2011 |
| 20110243710 | TURBO COMPRESSOR AND TURBO REFRIGERATOR - A turbo compressor is provided including: a pump which sends lubricant stored in an oil tank having an open portion; and a control valve which adjusts the flow rate of the lubricant returning to the oil tank by dividing the stream of the lubricant sent from the pump; and an oil tank cover which blocks the open portion and is provided with an installation portion for the control valve, wherein the oil tank cover includes at least one of a first passage opened from the installation portion and allowing the stream of the lubricant sent from the pump to be divided and flow toward the control valve and a second passage opened from the installation portion and allowing the lubricant to flow from the control valve toward the oil tank. | 10-06-2011 |
| 20110274534 | SEALING ASSEMBLY - A sealing assembly is provided for sealing against a component. The sealing assembly comprises a seal carrier and a continuous seal element that is attached to the seal carrier at at least two discrete positions of attachment. The seal element is provided with a sealing surface that is arranged to seal against the component. The seal element is further provided with a thermal expansion slot that is located between the discrete positions of attachment and which extends from a first edge of the seal element over a portion of the width of the seal element. This allows the seal carrier and seal element to thermally expand in the length direction at different rates. | 11-10-2011 |
| 20120027570 | SHAFT ASSEMBLY FOR A GAS TURBINE ENGINE - A shaft assembly for a gas turbine engine includes a shaft, an annular fluid collection cavity, and a bearing. The shaft is rotatable around an axially extending shaft centerline. The annular fluid collection cavity is formed by an axial panel extending between a forward radial panel and an aft radial panel. The aft radial panel includes a plurality of fluid apertures, each fluid aperture having a center disposed at a first radius from the shaft centerline. The bearing includes an inner race having a shaft mounting surface and a plurality of axially extending race fluid passages. The shaft mounting surface is engaged with an exterior surface of the shaft, and is disposed at a second radius from the shaft centerline, wherein the second radius is less than the first radius. At least some of the axially extending race fluid passages are fluidly connected with at least some of the fluid apertures in the aft radial panel. | 02-02-2012 |
| 20120057959 | FAN - A fan includes a casing having an air inlet and an air outlet, an impeller housing located within the casing, an impeller located within the impeller housing for generating an air flow along a path extending from the air inlet to the air outlet through the impeller housing, a motor housing connected to the impeller housing, and a motor located within the motor housing for driving the impeller. A bellows support is provided for mounting the impeller housing within the casing. The bellows support is disposed on a seat connected to the casing. The bellows support extends about the impeller housing and forms a seal between the impeller housing and the casing. | 03-08-2012 |
| 20120070269 | STEAM TURBINE - A steam turbine of an embodiment includes: a nozzle box having a circular ring-shaped steam passage into which steam is led from a steam inlet pipe and having, on a downstream portion of the steam passage, a plurality of first-stage nozzles in a circumferential direction; and a second-stage nozzle side structure combined with the nozzle box and having a plurality of at least second-stage nozzles in a circumferential direction. Further, in the respective nozzle box and second-stage nozzle side structure, there are provided at least a pair of abutment surfaces for sealing which are not parallel to a turbine rotor axis and abutting each other. Furthermore, a seal member is provided in a part of a gap between the nozzle box and the second-stage nozzle side structure, the gap being formed by combining the nozzle box and the second-stage nozzle side structure. | 03-22-2012 |
| 20120207584 | SEAL LAND WITH AIR INJECTION FOR CAVITY PURGING - An exhaust liner assembly including an interface between moveable parts includes a seal liner having a plurality of slots. The size of each slot varies with the circumferential position of the liner assembly to provide a stable cavity pressure within the interface to create a stable barrier about the entire circumference of the exhaust liner assembly. | 08-16-2012 |
| 20120263574 | Pressure Compensating Wet Seal Chamber - Some embodiments of the invention provide a pump including a pump chamber, a shaft at least partially positioned in the pump chamber, an impeller coupled to the shaft, and a seal coupled to the shaft. The pump also includes a wet seal chamber with a first fluid. The wet seal chamber can include a bladder that compresses to compensate for volumetric expansion of the first fluid. The wet seal chamber substantially prevents fluid from contacting the seal in order to prolong a life of the seal. | 10-18-2012 |
| 20130028708 | Systems, Methods, and Apparatus for Sealing a Bucket Dovetail in a Turbine - Certain embodiments of the invention may include systems methods, and apparatus for sealing a bucket dovetail in a turbine. According to an example embodiment of the invention, a method is provided for sealing a gap between a bucket dovetail and a rotor wheel slot. The method can include providing a bucket tab associated with a bucket dovetail, wherein the bucket tab is configured to accept a seal tab; configuring the bucket tab and the seal tab to engage at least one dimension upon insertion of the seal tab into the bucket tab; and sealing a gap between the bucket dovetail and a rotor wheel slot with the seal tab; wherein at least a portion of the seal tab changes as a function of temperature for further sealing gap between the bucket dovetail and the rotor wheel slot. | 01-31-2013 |
| 20130071229 | PLUG DEVICE FOR GAS TURBINE ENGINE SHAFT - A device for plugging an axially-aligned bore in a shaft of a gas turbine engine comprises a plug. A sealing body of the plug is sealingly received in a bore of the shaft. Legs project from the sealing body and are displaceable between a normally contracted position in which the legs are radially inward relative to a periphery of the bore, and a deployed position in which the legs project radially outward and engage with shaft projections within the bore of the shaft. A wedge is operatively engaged to the plug for movement of the wedge relative to the plug. The wedge comprises a portion in operative contact with the legs of the plug unit to displace the legs between positions as a response to movement of the wedge. A gas turbine engine and a method for plugging a shaft are provided. | 03-21-2013 |
| 20130078079 | SEAL PLATE WITH COOLING PASSAGE - A seal assembly for a gas turbine engine includes a carbon seal and a seal plate. The seal plate has a contact face configured to slidably engage the carbon seal. The seal plate has a surface disposed on an opposing side of the seal plate from the contact face. The surface forms a portion of a single passage that extends an entire length of the seal plate. The continuous cooling provided by single passage along the seal plate allows for a more uniform temperature profile along the contact face of seal plate. | 03-28-2013 |
| 20130078080 | AIR SYSTEM ARCHITECTURE FOR A MID-TURBINE FRAME MODULE - A mid-turbine frame is disposed between high and low pressure turbine assemblies. A secondary air system is defined in the mid-turbine frame (MTF) to provide cooling to the turbine section of the engine. The secondary air system may be used to cool and pressurize seals to assist with oil retention in bearing cavities. The temperature gain of the secondary air may be reduced by flowing the secondary air through one or more external lines and then generally radially inwardly through air passages defined in the MTF. | 03-28-2013 |
| 20130084161 | Turbocharger Variable-Nozzle Assembly With Vane Sealing Arrangement - A variable-nozzle turbocharger includes a turbine housing and a center housing, and a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. The vanes extend between the nozzle ring and an opposite wall formed by an insert in the turbine housing. A vane sealing member is supported on the insert, and has a portion disposed between distal ends of the vanes and the insert. This portion of the vane sealing member is configured to be contacted by the distal ends of the vanes when the vanes are in the closed position, while a clearance exists between the portion of the vane sealing member and the distal ends of the vanes when the vanes are in the open position. | 04-04-2013 |
| 20130115048 | CONVOLUTION SEAL FOR TRANSITION DUCT IN TURBINE SYSTEM - A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a convolution seal contacting the interface member to provide a seal between the interface member and the turbine section. | 05-09-2013 |
| 20130129479 | MULTI PIECE TURPOCHARGER HOUSING - A turbocharger casing including a first casing part, wherein an oil line starts at a first opening on an outer side of the first casing part, runs through the first casing part and opens out at a second opening of a substantially hollow-cylindrical bearing receptacle of the first casing part. Such turbocharger casings of the prior art are produced in a complicated manner by a sand casting process and therefore give rise to high production costs. The teaching is to arrive, without functional losses, at a simple-to-produce and cost-effective turbocharger casing by the turbocharger casing having a second casing part attached to the first casing part and by both casing parts together forming a cooling water line provided for cooling the bearing receptacle. It is thus possible to arrive at a lightweight turbocharger casing by conventional machining production methods and joining technique, and this turbocharger casing can be produced cost-effectively. | 05-23-2013 |
| 20130170953 | VEHICULAR POWER TRANSMITTING SYSTEM - A vehicular power transmitting system including an oil pump constructed to sufficiently reduce a required drive torque. A high-pressure-port discharge amount of first and second high-pressure passages of the oil pump is determined such that an amount of consumption of working oil of relatively high pressure can be afforded only by the high-pressure-port discharge amount, during steady-state running of a vehicle in which engine speed is not lower than a predetermined threshold value corresponding to a predetermined lowest target input shaft speed of a continuously variable transmission for its shifting control. The pressure of the working oil discharged from first and second low-pressure discharge passages is kept at a predetermined low level, and the required drive torque of the oil pump is sufficiently reduced. | 07-04-2013 |
| 20130183138 | DUAL TEMPERATURE OIL CONTROL SYSTEM AND METHOD FOR A WIND TURBINE GEARBOX - A system and method are provided for supplying oil at different temperatures to different locations within a wind turbine gearbox, wherein oil is pumped from a common oil sump to the different locations via a common header. The different gear box locations are divided into at least two groups, wherein each of said groups receives inlet oil at a respective inlet oil temperature. A first temperature control device is disposed between the common header and the first group, and a second temperature control device is disposed between the common header and the second group of gearbox locations. | 07-18-2013 |
| 20130195618 | Underwater Compressor Arrangement And Underwater Process Fluid Conveying Arrangement Equipped Therewith - Underwater compressor arrangement and underwater process fluid conveying arrangement outfitted therewith. The underwater compressor arrangement has a housing, a turbocompressor with a compressor rotor, and a rotary drive unit with a drive rotor. The turbocompressor and rotary drive unit are arranged in the housing, and the compressor rotor is in rotationally driving connection with the drive rotor. The housing is hermetically sealed with the exception of operating connections for the turbocompressor and rotary drive unit, The compressor rotor is rotatably supported in the housing by a rolling element bearing arrangement. | 08-01-2013 |
| 20130209226 | PUMP AS WELL AS A RECIRULATION DEVICE FOR A PUMP - 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. | 08-15-2013 |
| 20130251507 | EPDM COMPOSITION - Disclosed is an EPDM composition for molding sealing materials, containing a plasticizer; the plasticizer being a paraffinic oil or naphthenic oil in which the absolute value of the difference between its SP value (solubility parameter; determined by Small's formula) and the SP value of EPDM is 0.3 (cal/cm | 09-26-2013 |
| 20130280038 | Pressure Exchange Noise Reduction - Various aspects of the technology provide for reducing noise and vibration in a pressure exchanger for high pressure fluid handling equipment such as a desalination system, by disposing grooves between a seal surface and a port. The groove reduces a hammer effect in moving high pressure fluid to a low pressure port and moving low pressure fluid to a high pressure port. Reduction in the hammer effect, in addition to reducing noise, reduces vibration that can cause deterioration of high pressure fluid handling equipment. | 10-24-2013 |
| 20130315708 | Nozzle with Extended Tab - A nozzle feature for sealing leakage in a gas turbine engine having a plurality of nozzle segments within the turbine engine which includes a radially inner band, a radially outer band, at least one vane disposed between the radially inner and outer bands, the radially inner band having a first tab formed in said inner band extending radially downwardly from at least one of first and second circumferential ends. | 11-28-2013 |
| 20130336764 | DEVICE FOR LUBRICATING A TRANSMISSION AND A BEARING - The invention relates to a device for lubricating a transmission ( | 12-19-2013 |
| 20130336765 | CRANKSHAFT FOR AN ALTERNATIVE COOLING COMPRESSOR - The present invention refers to a crankshaft ( | 12-19-2013 |
| 20130336766 | ROTATING SYSTEM FOR A WIND TURBINE - A rotating system ( | 12-19-2013 |
| 20140010631 | COMPRESSOR INTAKE MIXER SYSTEM - A compressor intake mixer system for internal combustion gas engines having a compressed charge bypass system comprises a bypass charge and fuel pre-mixer connected in line with the charge bypass system to reduce pressure gradient between the high pressure bypass charge and the low pressure fuel. A single volume main mixer is connected to the compressor inlet downstream of the pre-mixer to mix the flow of premixed charge and air and provide a mixed gas to the compressor inlet. Thus a need for a separate volume for a fuel mixer and a bypass mixer is eliminated and a single volume is provided at the compressor inlet. The locational constraint of necessarily locating the volumes at the compressor inlet is also obviated by providing a pre-mixer. | 01-09-2014 |
| 20140023482 | TURBINE, MANUFACTURING METHOD THEREOF, AND POWER GENERATING SYSTEM - A turbine according to an embodiment includes: a formation object member; a facing member; and a seal part. A formation object member is one of a static part and a rotation part. A facing member is the other of the static part and the rotation part. A seal part at the formation object member is configured to reduce combustion gas leaking between the formation object member and the facing member. The seal part including a ceramics layer. The ceramics layer has a heat conductivity lower than that of the formation object member, and has a concave and convex shape at a surface thereof. The ceramics layer is not in contact with the facing member, or has hardness higher than that of the facing member so that the facing member is preferentially abraded when the facing member and the ceramics layer are in contact with each other. | 01-23-2014 |
| 20140030062 | Method for Making a Temporary Turbocharger Compressor Seal and Temporary Turbocharger Compressor Seal Made by Same - A method for temporarily sealing a turbocharger compressor outlet and the seal for doing same are disclosed. The seal may include a layer of lubricant, a cover, and a layer of heat-shrink material. The seal creates a temporary water-tight seal around a turbocharger compressor outlet preventing damage to the inside of the turbocharger while the turbocharger is not in use. | 01-30-2014 |
| 20140030063 | SHAFT SEAL INSERT - A shaft seal insert for the shaft seal of a turbomachine extending along a rotational axis includes:—a rotor part attachable on a shaft of a rotor,—a stator part insertable into a stator receiving area, and—a dry gas seal having a rotating seal element attached to the rotor part and a fixed seal element attached to the stator part to seal an intermediate space between the two seal elements, which lie opposite each other on a sealing surface extending radially and in the circumferential direction. A labyrinth seal is provided on a high-pressure side in a serial arrangement with the dry gas seal to seal the intermediate space, having a fixed and rotating labyrinth seal parts. The fixed labyrinth seal part is part of the stator part or is fixed thereto. The rotating labyrinth seal part is part of the rotor part or is fixed thereto. | 01-30-2014 |
| 20140099187 | OIL BAFFLE FOR GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM - An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine, a compressor hub driven by the second shaft, the compressor hub within a compressor section of the gas turbine engine, an epicyclic gear train that is driven by the first shaft, and a common attachment point that secures the first shaft and the compressor hub to the second shaft. | 04-10-2014 |
| 20140112757 | CLEARANCE CONTROL - A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energise the first and second plasma generators at an energising frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component. | 04-24-2014 |
| 20140119887 | FLUID-COOLED SEAL ARRANGEMENT FOR A GAS TURBINE ENGINE - A rotational component for a gas turbine engine includes at least one passage with a semi-spherical end. | 05-01-2014 |
| 20140248125 | CHAMBER FLUID REMOVAL SYSTEM - A chamber fluid removal system including a pump and an ejector is disclosed. The system is arranged in use to pump fluid from a chamber using the pump and deliver it to the ejector as a motive fluid and the system being further arranged to draw fluid from the chamber or from a second chamber as an entrained fluid by entraining it using the ejector and the motive fluid. | 09-04-2014 |
| 20140334913 | SYSTEM FOR SEALING AN OIL CHAMBER FROM AN ADJOINING EXTERIOR VOLUME AND TURBO-MACHINE PROVIDED WITH SUCH A SEALING SYSTEM - A system for sealing an oil chamber from an adjoining exterior volume, and a turbo-machine including a sealing system. The system for sealing the oil chamber from the adjoining exterior volume, both of which are delimited by a mobile rotor in rotation about an axis and a part, fixed or mobile, includes: a first seal arranged between the rotor and the part; a second seal that is mounted between the rotor and the part and which is offset longitudinally relative to the first seal, to form with the first seal a sealing chamber delimited by the rotor, the part, and the two seals; and a mechanism for supplying gas to the sealing chamber, such that the gas can be compressed when the rotor begins to rotate, the chamber communicating with the oil chamber and/or the adjoining exterior volume via the first and second seals alone, respectively. | 11-13-2014 |
| 20150050125 | FLUID SEAL ARRANGEMENT AND METHOD FOR CONSTRICTING A LEAKAGE FLOWTHROUGH A LEAKAGE GAP - The invention refers to a fluid seal arrangement for constricting a leakage flow directed through a leakage gap bordered by a rotational and a stationary component including at least one nozzle opening in the rotating and/or stationary component facing towards the rotating or stationary component of an opposite side of the leakage gap respectively in order for injecting a liquid or gaseous fluid flow through the nozzle opening into the leakage gap. The at least one nozzle opening is fluidly connected to a cooling channel inside said rotating and/or stationary component, so that said fluid flow emanating at the nozzle opening consists of a cooling fluid of the rotating and/or stationary component exclusively. | 02-19-2015 |
| 20150056064 | TURBOCHARGER BEARING HOUSING - There is provided a turbocharger bearing housing having no necessity to use a core and capable of achieving cost reduction. A bearing housing of a turbocharger contains a shaft connecting a turbine and a compressor and turnably supports the shaft. The bearing housing of the turbocharger is divided into a turbine-side housing disposed at a turbine side and a compressor-side housing disposed at a compressor side. The turbine-side housing and the compressor-side housing is subjected to machining to thereby form a cooling water passage for supplying cooling water and a lubricating oil passage for supplying lubricating oil. | 02-26-2015 |
| 20150071761 | SEALING ARRANGEMENT FOR A NOZZLE GUIDE VANE AND GAS TURBINE - A nozzle guide vane support arrangement including a platform portion of a nozzle guide vane at a trailing edge is provided, the platform portion having a platform wall including a first platform wall portion and a second platform wall portion. A working fluid interaction surface and a cooling surface at least partly limit an inner cavity of the platform portion in which a cooling fluid is leadable. The second platform wall is connected to the first platform wall at an axial downsealing arrangement and gas turbinesealing arrangement for a nozzle guide vane and gas turbinestream end of the platform portion. A first surface of the second platform wall limits the inner cavity, and a support structure including a seal arranged in a recess between the support structure and a second surface of the second wall to reduce cooling liquid leakage from the inner cavity to a space downstream. | 03-12-2015 |
| 20150078885 | FAN - A fan includes a casing having an air inlet and an air outlet, an impeller housing located within the casing, an impeller located within the impeller housing for generating an air flow along a path extending from the air inlet to the air outlet through the impeller housing, a motor housing connected to the impeller housing, and a motor located within the motor housing for driving the impeller. A bellows support is provided for mounting the impeller housing within the casing. The bellows support is disposed on a seat connected to the casing. The bellows support extends about the impeller housing and forms a seal between the impeller housing and the casing. | 03-19-2015 |
| 20150147157 | PIVOT PIN FOR A TURBINE ENGINE COMPRISING A RING FOR RECOVERING A FLOW OF LUBRICATING OIL WITH A PLURALITY OF LUBRICATING OIL DISCHARGE PORTS - A journal configured to be driven in rotation in a housing of a turbine engine, or for an aircraft, the journal including: a circumferential main body including plural ventilation openings configured to allow plural axial airflows to circulate from upstream to downstream in the turbine engine, two consecutive ventilation openings being connected by a connecting segment, and a circumferential ring for recovering a flow of lubrication oil, which ring is rigidly connected to the main body and is radially inside the ventilation openings, the recovery ring including plural radial discharge openings for allowing plural radial flows of oil to be discharged towards the outside, each discharge opening being radially aligned with a connecting segment of the main body to allow each flow of oil to be discharged between the airflows. | 05-28-2015 |
| 20150292358 | GAS TURBINE ENGINE INNER CASE INCLUDING NON-SYMMETRICAL BLEED SLOTS - A compressor of a gas turbine engine includes a plurality of rotors rotatable about a central longitudinal axis, a plurality of stators, and a circumferential inner case wall located outwardly of the plurality of rotors and the plurality of stators. The inner case wall includes a plurality of first slots located in a first section of the circumferential inner case wall and a plurality of second slots located in at least one second section of the circumferential inner case wall. A first area of each of the first slots is greater than a second area of each of the second slots. A circumferential manifold is located outwardly of the inner case wall including a port. At least one of the plurality of second slots is located proximate to the port. | 10-15-2015 |
| 20150308445 | GAS TURBINE ENGINE AND BUFFER SYSTEM THEREFOR - The present disclosure relates generally to a buffer vent system for a gas turbine engine. A supply of auxiliary pressurized gas is supplied to the buffer vent system during engine start during a period of time when the compressor section of the gas turbine engine is not able to supply adequate pressurized air to the buffer vent system. | 10-29-2015 |
| 20160032781 | MOVEABLE SEALING ARRANGEMENT FOR A GAS TURBINE DIFFUSER GAP - A sealing arrangement for a gas turbine including exhaust and manifold diffusers separated by a circumferential diffuser gap. The sealing arrangement includes a forward clamp arrangement attached to the exhaust diffuser wherein the forward clamp arrangement includes a forward groove. The sealing arrangement also includes an aft clamp arrangement attached to manifold diffuser wherein the aft clamp arrangement includes an aft groove. Further, the sealing arrangement includes a flexible circumferential seal including forward and aft loop portions. The forward loop portion is located in the forward groove and the aft loop portion is located in the aft groove wherein the circumferential seal extends across the circumferential diffuser gap to seal the circumferential diffuser gap. The forward and aft loop portions are moveable in the forward and aft grooves to enable movement of the circumferential seal in a circumferential direction to accommodate thermal expansion of the exhaust and manifold diffusers. | 02-04-2016 |
| 20160047263 | GAS TURBINE SEALING BAND ARRANGEMENT HAVING AN UNDERLAP SEAL - A sealing band arrangement for a gas turbine including first and second adjoining rotor disks each including a disk arm having a slot. The sealing band arrangement includes at least one first seal strip segment located within the slots, wherein the seal strip segment includes first and second ends. The sealing band arrangement also includes a tab section that extends from the first end in order to form an underlap seal with an adjacent second seal strip segment. The underlap seal enables a thickness of the first and second ends to be substantially equivalent to a thickness of the first seal strip segment in order to improve wear life of the seal strip segment. The sealing band arrangement further includes at least one wide portion formed in the first seal strip segment wherein the wide portion is wider than a remaining portion of the first seal strip segment. | 02-18-2016 |
| 20160061211 | Mechanical Seal Lubrication System - Disclosed is a pump which comprises a mechanical seal lubricated by supplying lubricant from an external oiler. When there is no fluid flowing through the pump and the pump is in operation, the temperature of the mechanical seal rises. The lubricant from the oiler is supplied to the center of the mechanical seal through entry lines, and serves to maintain temperature within the pump and seal, while also avoiding failure of the seal. The lubricant keeps the mechanical seal cool and lubricated at all times. | 03-03-2016 |
| 20160069215 | OFFTAKES FOR GAS TURBINE ENGINE SECONDARY GAS FLOWS - A turbo machinery case includes a shell body extending circumferentially about a longitudinal axis and defining therein a main gas path. The shell body defines a first offtake opening and a second offtake opening that extend in a circumferential direction about the longitudinal axis. The first and second offtake openings are defined at a common axial location with respect to the longitudinal axis of the turbo machinery case. | 03-10-2016 |
| 20160076449 | AERO ENGINE WITH A BEARING CHAMBER AND AN APPLIANCE FOR INTRODUCING OIL - What is proposed is an aero engine ( | 03-17-2016 |
| 20160097398 | VACUUM PUMP - The present disclosure relates to a vacuum pump including a bearing and a lubricant supply system for lubricating the bearing. The lubricant supply system includes: a lubricant reservoir comprising a reservoir matrix for receiving a lubricant; a lubricant transfer arrangement in contact with the reservoir matrix for transferring lubricant from the reservoir matrix to the bearing, the lubricant reservoir including a reservoir enclosure for locating the reservoir matrix in position relative to the lubricant transfer arrangement; wherein the lubricant reservoir includes a plurality of contact regions at which the reservoir matrix is in contact with the reservoir enclosure for locating the reservoir matrix in position relative to the lubricant transfer arrangement and a plurality of spacing regions between respective contact regions at which the reservoir matrix is spaced apart from the reservoir enclosure for receiving gas and lubricant foam caused by outgassing in the lubricant in the reservoir matrix. | 04-07-2016 |
| 20160177825 | AIRCRAFT ENGINE HAVING A DEVICE FOR SEPARATING OIL | 06-23-2016 |
| 20170234213 | TURBOMACHINE | 08-17-2017 |
