Class / Patent application number | Description | Number of patent applications / Date published |
415175000 | INCLUDING ADDITIONAL MEANS CAUSING OR CONTROLLING FLUID FLOW FOR HEAT EXCHANGING, LUBRICATING OR SEALING | 79 |
20080240910 | TURBO-MOLECULAR PUMP, SUBSTRATE PROCESSING APPARATUS, AND METHOD FOR SUPPRESSING ATTACHMENT OF DEPOSITIONS TO TURBO-MOLECULAR PUMP - A turbo-molecular pump that enables reliable suppression of attachment of depositions onto component parts thereof. The turbo-molecular pump discharges a deposition-causing gas from a processing chamber. A rotor has a rotor shaft aligned with an exhaust stream. A cylindrical casing houses the rotor therein. A plurality of blade-form rotor blades projects from the rotor orthogonally with respect to the rotor shaft and are divided into a plurality of rotor blade groups. A plurality of blade-form stator blades projects orthogonally with respect to the rotor shaft from a rotor-facing surface and are divided into a plurality of stator blade groups. Gas supply ports are located on an upstream side of the rotor blade group that is located furthest downstream in the exhaust stream, and supply a deposition-suppressing gas which includes gas molecules having a large molecular weight. | 10-02-2008 |
20090067998 | Component Having a Film Cooling Hole - Conventionally coated components with film cooling holes are known, comprising a diffuser, extending through the layers into the substrate. According to the invention, the component is embodied such that the whole diffuser is largely arranged in the layer. | 03-12-2009 |
20090104027 | INTERMEDIATE CASING OF A TURBOJET AND A TURBOJET - The present invention relates to an intermediate casing of a turbojet comprising, between an inner hub and an outer cylindrical shroud, a plurality of radial arms at least one of which is hollow, a radial transmission shaft for driving the auxiliary machines being mounted rotatably in said radial arm, a first end of the transmission shaft passing through the inner hub and the second end passing through the outer cylindrical shroud. The housing is notable in that the inner volume consists of a single compartment housing the transmission shaft and forming a passageway for a lubrication fluid. | 04-23-2009 |
20090285677 | Systems And Methods For Cooling Heated Components In A Turbine - Systems and methods for cooling heated components in a turbine are provided. According to one embodiment, a system for cooling a turbine is provided that may include at least one liquid source which may include a coolant liquid. The system may also include at least one liquid nozzle in fluid communication with the liquid source or sources and operable to deliver the coolant liquid in an atomized form adjacent to at least one heated turbine component positioned in a hot gas path of the turbine. Upon delivering the atomized coolant liquid adjacent to the heated turbine component or components, at least a portion of the coolant liquid substantially changes phase to a gas. | 11-19-2009 |
20090304499 | Counter-Vortex film cooling hole design - An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall to a first outlet along the exterior surface of the wall for providing film cooling, and first and second rows of vortex-generating structures. The first film cooling passage defines a first interior surface region and a second interior surface region. The first row of vortex-generating structures is located along the first interior surface region, and the second row of vortex-generating structures is located along the second interior surface region. The first and second rows of vortex-generating structures are configured to inducing a pair of vortices in substantially opposite first and second rotational directions in a cooling fluid passing through the first cooling passage prior to reaching the first outlet. | 12-10-2009 |
20090324396 | ACCESSORY GEARBOX SYSTEM WITH COMPRESSOR DRIVEN SEAL AIR SUPPLY - An accessory gearbox system for a gas turbine engine includes a accessory compressor mounted to a gearbox housing. | 12-31-2009 |
20100047062 | STATOR HEAT SHIELD - A stator heat shield ( | 02-25-2010 |
20100189551 | Systems and Methods of Reducing Heat Loss from a Gas Turbine During Shutdown - A method operates a gas turbine that includes a compressor section, a turbine section and an extraction cooling system. The method includes monitoring an operation of the gas turbine, directing a cooling air flow through the extraction cooling system from the compressor section to the turbine section in response to normal operation of the gas turbine, and directing a warming air flow through the extraction cooling system to the compressor section and the turbine section in response to shutdown of the gas turbine. | 07-29-2010 |
20100266393 | TURBINE CASING COOLING - A turbine assembly having a bladed turbine wheel and a turbine casing ( | 10-21-2010 |
20100329855 | FAN SHROUD WITH MODULAR VANE SETS - A fan shroud with modular vane members for a cooling system. A plurality of modular vane set members are positioned around the inner surface of the fan shroud ring, each of the modular vane set members having a plurality of vane members. The modularity provides flexibility and versatility for the fan shroud and corresponding efficiencies in costs and manufacturing. | 12-30-2010 |
20110085894 | GAS TURBINE WITH A STATOR BLADE - A gas turbine with a stator blade is disclosed. The stator blade is fastened on a blade carrier and includes a blade airfoil which extends inwards in the radial direction from an outer platform into a hot gas passage. A cooling medium can flow through an interior of the blade airfoil, such as cooling air, which flows through an access in the blade carrier into a first plenum which is arranged above the outer platform, and from there, via an inlet which is provided in the outer platform, flows into the interior of the blade airfoil. | 04-14-2011 |
20120027576 | TURBINE STAGE SHROUD SEGMENT - A shroud segment for a turbine stage of a gas turbine engine forms an endwall for the working gas annulus of the stage. The segment also provides a close clearance to the tips of a row of turbine blades which sweep across the segment. In use a leakage flow of the working gas passes through the clearance gap between the blade tips and the segment. The segment has a plurality of cooling holes and respective air feed passages for the cooling holes. The cooling holes are distributed over that part of the gas-washed surface of the segment which is swept by the blade tips. The cooling holes deliver, in use, cooling air which spreads over the gas-washed surface. The feed passages are configured such that the delivered air opposes the leakage flow of the working gas. | 02-02-2012 |
20120034074 | Part of a casing, especially of a turbo machine - A part of a casing of a turbomachine is provided. The part is of one piece of material. The part includes a cavity extending along a circumference of a rotational axis of the turbomachine, the cavity having a radially outer wall and a radially inner wall. The part also includes an inlet opening for supplying a cooling medium into the cavity and an outlet opening for discharging the cooling medium from the cavity. The radially inner wall is configured to support at least vanes or rotor seals facing rotor blades of the turbomachine, or a carrier for these vanes or seals. The proposed design provides enhanced efficiency without increasing production costs. The turbomachine may include, for example, a gas turbine, a steam turbine or a compressor. | 02-09-2012 |
20120183391 | TURBOMACHINERY WITH INTEGRATED PUMP - The disclosed embodiments include self-lubricating oil feed systems that may include an integral bearing. The oil feed systems may include gear pumps suitable to minimize the axial profile of the oil feed systems. Additionally, the oil feed systems may be directly coupled to turbomachinery having a gear, and provide for mechanical support and lubrication of certain components of the turbomachinery. In certain embodiments, the oil feed systems enables the transfer of a lubrication fluid to the bearing during operations of the turbomachinery. | 07-19-2012 |
20120201661 | CONTAMINANT SHIELD SYSTEM FOR A SHAFT - Systems for shielding a shaft from contaminants are disclosed. In one embodiment, a contaminant shield system for a shaft includes: a fluid seal disposed circumferentially about the shaft, the fluid seal substantially fluidly isolating an inner portion of the shaft from atmospheric air; an oil deflector ring disposed circumferentially about the inner portion of the shaft, the oil deflector ring having an inner surface facing a portion of the shaft exposed to a lubricating oil and an outer surface facing the fluid seal; and a fluid conduit interposed between the fluid seal and the outer surface of the oil deflector ring, the fluid conduit for receiving a fluid and releasing the fluid between the fluid seal and the outer surface of the oil deflector ring creating a positive pressure differential. | 08-09-2012 |
20120243978 | STEAM TURBINE - A steam turbine | 09-27-2012 |
20120257962 | POSITIVE DISPLACEMENT PUMP - A positive displacement pump having a variable flow volume comprises a housing having an outer ring inserted in an internal space of the housing, the outer ring supporting a rotor set comprising a rotor, rotor elements and a cam ring. The rotor is surrounded by the cam ring. Working chambers are formed between the rotor and the cam ring, the volumes of the chambers being adjustable by varying the eccentricity between the rotor and the cam ring. Pressure chambers are formed between an outer peripheral surface of the cam ring and the outer ring. A control piston is connected to the pressure chambers by way of associated control bores which extend at least approximately axially in the cover plate radially inside a peripheral flange of the housing and extend through a face plate which is disposed on the inside axially in front of the rotor set into the pressure chambers. | 10-11-2012 |
20120308368 | FLAP SEAL SPRING AND SEALING APPARATUS - A biasing means is provided for securing a plurality of sealing components which are arranged to seal gaps between adjacent structural components in a turbine, the biasing means having three foot regions joined in a substantially linear fashion by two resilient curved arms, wherein each arm has securing means for securing the biasing means to one of said structural components such that when the biasing means is secured to said one of said structural components, each of said foot regions contacts one of said sealing components and the curved arms urge the sealing components towards one of said structural components so that the sealing components collectively create a seal over the gap between said structural components. An apparatus for sealing gaps between adjacent structural components which includes the biasing means is also provided as is a method of sealing gaps in a turbine. | 12-06-2012 |
20130101400 | RAM AIR FAN INNER HOUSING - 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. | 04-25-2013 |
20130101401 | SEAL AIR SUPPLY SYSTEM AND EXHAUST GAS TURBINE TURBOCHARGER USING SEAL AIR SUPPLY SYSTEM - Provided is a seal air supply system including: a seal air compressor | 04-25-2013 |
20130129489 | TURBOCHARGER OIL FEED SYSTEM - 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. | 05-23-2013 |
20130149119 | VARIABLE CAPACITY CORE TYPE HEAT EXCHANGER UNIT - 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. | 06-13-2013 |
20130251513 | FABRICATED HEAT SHIELD - 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. | 09-26-2013 |
20130287553 | MANIFOLD FOR GEARED TURBOFAN ENGINE - 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. | 10-31-2013 |
20130315719 | Turbine Shroud Cooling Assembly for a Gas Turbine System - 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. | 11-28-2013 |
20130323035 | METHOD AND SYSTEM TO PREVENT EQUIPMENT CORROSION FROM HUMID AMBIENT AIR ENTRY INTO AN OFFSHORE WIND TURBINE - 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. | 12-05-2013 |
20140072416 | APPARATUS FOR MAINTAINING THE OPERATION OF A GEOTHERMAL PRODUCTION PUMP - 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. | 03-13-2014 |
20140079539 | Turbine blade of a gas turbine with swirl-generating element and method for its manufacture - 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. | 03-20-2014 |
20140086732 | AIR BAFFLE SYSTEM IN A COOLING SYSTEM FOR ELECTRONICS - 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. | 03-27-2014 |
20140140828 | BLAST SHIELD FOR HIGH PRESSURE COMPRESSOR - 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. | 05-22-2014 |
20140147258 | HYDRAULIC BEARING FOR A STATIONARY GAS TURBINE - 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. | 05-29-2014 |
20140186164 | NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART - A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening. | 07-03-2014 |
20140193246 | COOLING HOLE WITH CRENELLATION FEATURES - A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region. | 07-10-2014 |
20140205446 | REGULATED OIL COOLING SYSTEM FOR A TURBINE ENGINE WITH DEICING OF THE NACELLE - The invention relates to an oil cooling system of a turbine engine installed in an aircraft comprising a circuit suitable for circulating the oil between the engine and at least one external heat exchanger placing the oil in thermal communication with a part of the lip of the nacelle, wherein it also comprises at least one air/oil heat exchanger placing the oil in thermal communication with the air circulating in the cold zone of the turbine engine, equipped with a device suitable for varying its oil cooling capacity, and with a control means for said cooling capacity variation device. | 07-24-2014 |
20140219788 | IMPINGEMENT COOLING OF TURBINE BLADES OR VANES - The present invention relates to a turbine assembly with a basically hollow aerofoil, having at least a cavity with an inner wall and having at least an aperture providing access to the cavity, and at least a first impingement device arrangeable within the cavity. The at least first impingement device is self-locking, resilient and preloadable and has at least one locking element to lock the at least first impingement device in place in the cavity via a force fit between the at least one locking element and the inner wall of the cavity wherein the locking element of the at least first impingement device is embodied as a protrusion extending in an assembled state of the at least first impingement device in the cavity basically perpendicular to a surface of a side wall of the at least first impingement device in a direction towards the inner wall. | 08-07-2014 |
20140255171 | LUBRICATION SYSTEM FOR A TURBOPROPELLER - A lubrication system for a turbopropeller, includes an oil feed device for at least one enclosure and one equipment, the equipment being connected to the feed device via a displacement pump, and a pressure restricting valve mounted downstream of displacement pump and in parallel to the equipment, such that oil flows through the equipment when the same is active, and through the valve when the equipment is inactive. | 09-11-2014 |
20140271151 | OIL TRANSFER SYSTEM ON ROTATING SHAFT - Lubrication system for a device ( | 09-18-2014 |
20140286762 | TURBINE AIRFOIL ASSEMBLY - A turbine airfoil assembly has an airfoil with an inner wall, an outer wall, a leading edge and a trailing edge. The airfoil has one or more chambers extending in a substantially chordwise direction of the airfoil. An insert has a plurality of impingement holes, and the insert is configured to be inserted within one of the chambers. The insert is configured to cool the airfoil via the plurality of impingement holes. A chambering element is attached only to the insert, the chambering element is configured to provide an increased cooling gas pressure inside a boundary area defined by the chambering element relative to an area outside the boundary area. A gap exists between the inner wall of the airfoil and the chambering element, and the gap allows cooling gas to exit the boundary area and enter the area outside the boundary area. | 09-25-2014 |
20140301834 | TURBINE CYLINDER CAVITY HEATED RECIRCULATION SYSTEM - A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system. The air may then be passed to a heating air supply system via an air movement device. The heating air supply system may be in communication with a turbine cylinder cavity of the turbine engine positioned radially outward from at least one turbine assembly. The heated air may be passed into the turbine cylinder cavity to reduce the cooling rate of the turbine vane carriers after shutdown and before a warm restart to limit tip rubbing. | 10-09-2014 |
20140321994 | HOT GAS PATH COMPONENT FOR TURBINE SYSTEM - A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough. | 10-30-2014 |
20140321995 | RAM AIR FAN INLET SHROUD - A ram air fan inlet shroud for a ram air fan assembly is provided. The ram air fan inlet shroud includes a shroud portion extending outwardly from a conical portion. The conical portion provides a transition between a central portion and an inner ram air fan hub interface portion. The conical portion includes a plurality of inner cooling slots having a slot arc length and spaced apart by a slot spacing angle. A ratio of the slot spacing angle to the slot arc length is between about 1.24 and 1.4. The ram air fan inlet shroud also includes a recessed portion located between the inner ram air fan hub interface portion and an outer ram air fan hub interface portion. The recessed portion includes a plurality of outer cooling holes. | 10-30-2014 |
20140321996 | FIXED OUTSIDE RING OF A BEARING WITH AT LEAST ONE DRAINAGE ORIFICE PASSING THROUGH A GUIDING EDGE OF AT LEAST ONE ROLLING ELEMENT - The invention relates to an outside ring of a rotary shaft bearing of a turbomachine, comprising a first guiding edge of at least one rolling element, the first guiding edge comprising an inside surface of the first guiding edge, an outside surface of the first guiding edge opposite the inside surface and at least one through-hole passing through the inside surface and the outside surface. | 10-30-2014 |
20140334921 | PUMP FOR WATER COOLER - A pump for a water cooler is positioned inside or outside an electronic device having heating parts in order to cool heat generated by the heating parts via a circulating refrigerant. | 11-13-2014 |
20140341723 | GAS TURBINE VANE INSERT TO CONTROL PARTICULATE DEPOSITION - A guide tube assembly in one embodiment includes a guide tube and a collection impingement feature. The guide tube includes an inlet and at least one first impingement opening. The inlet is configured to direct a cooling air flow along the length of the tube in an inlet direction. The at least one impingement feature is configured to direct at least a portion of the cooling air received via the inlet along a first impingement direction. The collection impingement feature receives the at least a portion of the cooling airflow directed in the first impingement direction, collects particulate matter from the cooling airflow upon impingement of the cooling airflow with the collection impingement feature, and directs the at least a portion of the cooling air flow in a second impingement direction toward a surface of the turbine component to be cooled by the cooling air flow. | 11-20-2014 |
20140341724 | STATIC CORE TIE RODS - A core tie having a varying cross sectional diameter, a component including such a core tie, and a method of casting a hot gas path component for a turbomachine are provided herein. In an embodiment, the core tie includes a tie member having an axial length; and a cross sectional diameter which varies along the axial length of the tie member. A variation in the cross sectional diameter of the tie member positively secures a position of the core tie relative to the core. | 11-20-2014 |
20140356146 | VACUUM PUMP - A vacuum pump includes a rotor and a rotary bearing, which is to be supplied with an operating medium, for the rotatable support of the rotor, wherein the rotor has a conveying section, in particular a conical conveying section, for supplying the operating medium to the rotary agent. A conveying pump is provided for conveying the operating medium and/or an operating medium store is provided having an absorbent storage means for the operating medium. Further, at least one wick is provided which is in contact with the conveying section to transfer the operating medium provided from the conveying pump and/or from the absorbent storage means to the conveying section in a desired quantity. | 12-04-2014 |
20140377058 | TURBINE GUIDE VANE WITH A THROTTLE ELEMENT - A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant. | 12-25-2014 |
20150016971 | COMPARTMENTALIZATION OF COOLING AIR FLOW IN A STRUCTURE COMPRISING A CMC COMPONENT - A structure in a gas turbine engine comprises a spar and a CMC component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air. | 01-15-2015 |
20150016972 | BI-CAST TURBINE VANE - One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together. | 01-15-2015 |
20150016973 | IMPINGEMENT COOLING OF TURBINE BLADES OR VANES - A turbine assembly having a hollow aerofoil and impingement device, the aerofoil having a first side wall from leading to trailing edge and a cavity arranged a distance to an inner surface of the cavity for impingement cooling and a flow channel for cooling medium from the leading to trailing edge, the impingement device has first and second pieces arranged side by side, the second piece downstream of the first forming a first flow passage providing passage from one side of the aerofoil towards an opposite side. A blocking element is arranged in the flow channel between the second piece and first side wall at a suction side for blocking flow of cooling medium from leading to trailing edge denying access to a section of the flow channel downstream of the blocking element while directing cooling medium in the first flow passage away from the suction side towards pressure side. | 01-15-2015 |
20150044036 | LUBE OIL SUPPLY SYSTEM AND METHOD OF REGULATING LUBE OIL TEMPERATURE - A lube oil supply system of a turbine system and method of regulating lube oil temperatures. In one embodiment, the system includes a first valve positioned on a lube oil bypass conduit in fluid communication with a lube oil supply line to a heat exchanger. The first valve may be positioned in parallel with the heat exchanger. The system may also include a second valve positioned on a cooling fluid supply line in fluid communication with the heat exchanger, and a lube oil control system operably connected to the first valve and the second valve. The lube oil control system may be configured to modify a position of at least one of the first valve, or the second valve in response to determining a temperature of a lube oil of the lube oil supply line differs from a predetermined lube oil temperature threshold. | 02-12-2015 |
20150118033 | MICROCHANNEL EXHAUST FOR COOLING AND/OR PURGING GAS TURBINE SEGMENT GAPS - A gas turbine stator component includes a composite, segmented ring made up of an annular array of arcuate segments, each having end faces formed with respective seal slots, with radial gaps formed between opposed end faces of adjacent arcuate segments. A seal is located between each pair of opposed seal slots to thereby seal the gaps, and a channel is provided in each of said arcuate segments adapted to be supplied with cooling air, the channel connecting to a passage extending between the channel and a respective one of the seal slots or radial gaps, on a lower-pressure side of the seal. | 04-30-2015 |
20150118034 | TRAILING EDGE COOLING USING ANGLED IMPINGEMENT ON SURFACE ENHANCED WITH CAST CHEVRON ARRANGEMENTS - A gas turbine engine component, including: a pressure side ( | 04-30-2015 |
20150147164 | MODIFIED TURBINE COMPONENTS WITH INTERNALLY COOLED SUPPLEMENTAL ELEMENTS AND METHODS FOR MAKING THE SAME - Modified turbine components include an original turbine component comprising an outer wail enclosing an internal cavity, wherein the outer wall has an original portion removed therefrom to expose the internal cavity, and, an internally cooled supplemental element joined to the outer wall that replaces the original portion removed from the outer wall and re-encloses the internal cavity. The internally cooled supplemental element comprises one or more cooling channels that circulate air from the internal cavity through at least a portion of the internally cooled supplemental element. | 05-28-2015 |
20150147165 | METHODS FOR THE FORMATION AND SHAPING OF COOLING CHANNELS, AND RELATED ARTICLES OF MANUFACTURE - A method to modify the shape of a channel in a metallic substrate is described. The method includes the step of applying at least one metallic coating on selected portions of an interior surface of the channel, so as to alter the heat transfer characteristics of the channel during passage of a coolant fluid therethrough. Related articles that contain the modified channels are also described, such as gas turbine engine components. | 05-28-2015 |
20150315923 | STATOR VANE FORMED BY A SET OF VANE PARTS - A stator vane for a turbine machine includes a set of vane parts arranged relative to each other to define air flow stream paths between vane parts, and a mechanism circulating a fluid to be cooled by the air flow. | 11-05-2015 |
20150330243 | DEVICE FOR SEALING BETWEEN THE COAXIAL SHAFTS OF A TURBOMACHINE - A sealing device for sealing between coaxial shafts of a turbomachine, the sealing device including an elastic ring having a circular central opening allowing a sliding connection with an internal shaft, an external surface configured to engage with an internal surface of a portion of an external shaft, two retaining components situated one on either side of the elastic ring and allowing the elastic ring an axial clearance, wherein the elastic ring is a profile section. | 11-19-2015 |
20150330248 | HEAT SHIELD FOR COOLING A STRUT - An assembly for a gas turbine engine includes a strut and a heat shield. The heat shield is disposed adjacent the strut and the heat shield and is adapted to contain a cooling air flow that passes along first cavity between the heat shield and the strut. | 11-19-2015 |
20150361991 | Water-Cooled Electronic Inverter - A water cooled inverter is disclosed herein. More specifically, disclosed is a water cooled inverter for attachment to a water pump housing that defines a water chamber therewithin, the water cooled inverter comprising a pump seal plate, including a sealing wall that has a pump seal plate aperture therethrough, the pump seal plate aperture configured to receive a motor shaft to allow an impeller coupled to the motor shaft to propel water within the water chamber, and an inverter assembly, wherein the pump seal plate thermally couples the inverter assembly to the water chamber. | 12-17-2015 |
20160010558 | VENTILATION INLET | 01-14-2016 |
20160017750 | ANNULAR RING ASSEMBLY FOR SHROUD COOLING - A gas turbine engine includes an annular casing and a plurality of shroud segments forming an annular shroud. The annular shroud forms with the annular casing an annular cavity therebetween. The annular cavity includes an inlet and an outlet. An annular ring assembly is disposed in the annular cavity between the casing and the shroud and cooperating therewith to provide a first annular chamber and a second annular chamber. The annular ring assembly and a first portion of the shroud form the first annular chamber. The annular ring assembly and a second portion of the shroud form the second annular chamber. The annular ring assembly forms an intermediate annular chamber disposed between the first annular chamber and the second annular chamber. A flow path for coolant air is sequentially defined through the inlet, the first annular chamber, the intermediate annular chamber, the second annular chamber and the outlet. | 01-21-2016 |
20160017751 | COOLING DEVICE FOR A TURBOJET ENGINE OF AN AIRCRAFT NACELLE - The present disclosure provides a cooling device for a turbo engine of an aircraft nacelle, including: a heat exchanger and an air outlet pipe. The nacelle includes a front housing that has a front lip forming a hollow leading edge that delimits an annular de-icing chamber. In particular, the cooling device further includes a pipe for supplying pressurized air that extends from an inlet end linked to a pressurized air source, to an outlet end forming an air ejection nozzle opening into the de-icing chamber, and the outlet pipe of the heat exchanger has an air outlet section that is arranged in the de-icing chamber in a position designed such that the pressurized air ejection nozzle forms an air suction pump in the outlet pipe of the exchanger. | 01-21-2016 |
20160054011 | Outdoor Unit and Air Conditioner Having the Outdoor Unit - The present invention provides an outdoor unit including: a housing; an air blower that is disposed at an upper part of the housing to supply air from the inside of the housing to the outside of the housing; a heat exchanger that is disposed on a side of the housing; and electric components that are disposed on a side of the housing. A rotational axis of the air blower is inclined towards the heat exchanger side relative to the vertical direction of the housing, and an end of the air blower on a sucking side is disposed at a position overlapped with the electric components in the height direction. | 02-25-2016 |
20160123349 | Electric Air Pump for Inflatable Body - An electric air pump for pumping air into an inflatable body includes a housing having an air inlet and an air outlet, an impeller disposed in the housing, a motor configured to drive the impeller, an air passage connecting the air inlet and the air outlet, a first chamber receiving the motor and including a ventilation inlet and ventilation outlet, and a heat dissipation impeller configured to be driven by the motor so that air flows into the first chamber through the ventilation inlet and flows out of the first chamber through the ventilation outlet for heat dissipation of the motor. | 05-05-2016 |
20160160872 | TURBOCHARGER PURGE SEAL INCLUDING AXISYMMETRIC SUPPLY CAVITY - A turbocharger rotating assembly ( | 06-09-2016 |
20160376923 | PUMP FOR A TURBINE ENGINE - A pump for a gas turbine engine is provided. The pump includes a first drive track having a spline and a first gear each rigidly attached to a first driveshaft. The pump also includes a second drive track having a second gear rigidly attached to a second driveshaft. The second gear is mechanically coupled to the first gear. Additionally, a first lubrication supply pump is mechanically coupled to the first driveshaft and a second lubrication supply pump is mechanically coupled to the second driveshaft. The first and second lubrication supply pumps are together configured to provide a desired amount of lubrication to the gas turbine engine. | 12-29-2016 |
20180023592 | BLOWING SYSTEM | 01-25-2018 |
415176000 | Means subjected to or is working fluid | 12 |
20090104028 | METHOD AND APPARATUS FOR DISTRIBUTING FLUID INTO A TURBOMACHINE - An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port. | 04-23-2009 |
20090317242 | METHOD AND DEVICE FOR COOLING A COMPONENT OF A TURBINE - A method for cooling a component of a turbine is provided, wherein a fluid with a pressure below 1 bar is guided away from the component. Moreover, a turbine is described comprising a component, a conduit which is connected to the component so that a fluid can be guided away from the component, and a fluid discharge which is connected to the conduit. The fluid discharge is constructed so that it removes a fluid with a pressure below 1 bar. | 12-24-2009 |
20100021288 | UAV Pod Cooling Using Integrated Duct Wall Heat Transfer - Electronic equipment frequently requires cooling to maintain the integrity and reliability of the equipment, and to elongate the life expectancy of the equipment. When in operation, the fan of a UAV creates airflow comprising outside air directed across the duct of the UAV. Utilizing this airflow generated by the fan of a UAV to provide heat transfer from a equipment enclosure accomplishes efficient heat transfer. The methods described herein for transferring heat from an equipment enclosure using an airflow generated by a fan of a UAV may be employed for UAVs having a variety of duct shapes, and having equipment enclosures inside the duct or in detachable equipment enclosures located on the duct of the UAV. | 01-28-2010 |
20100028137 | SYSTEM FOR VENTILATING A DOWNSTREAM CAVITY OF AN IMPELLOR OF A CENTRIFUGAL COMPRESSOR - A system for ventilating a downstream cavity of an impellor of a centrifugal compressor in a turbomachine, this system comprising flow diversion means ( | 02-04-2010 |
20110002777 | SYSTEMS AND APPARATUS RELATING TO TURBINE ENGINES AND SEALS FOR TURBINE ENGINES - A turbine engine that includes a vortex protrusion disposed upon a component that rotates during operation of the turbine engine; wherein the vortex protrusion includes an outer surface that is configured to induce a vortex flow pattern as the component rotates during operation. | 01-06-2011 |
20130115059 | BUCKET ASSEMBLY FOR TURBINE SYSTEM - A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit. The bucket assembly further includes a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face and further includes a forward face, an aft face, and a top face. The bucket assembly further includes a plenum at least partially defined in the platform. The plenum is in fluid communication with the main cooling circuit and extends from the main cooling circuit towards the suction side slash face. | 05-09-2013 |
20130115060 | BUCKET ASSEMBLY FOR TURBINE SYSTEM - A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit, and a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face and further includes a forward face, an aft face, and a top face. The platform cooling circuit includes an upper surface and a lower surface. The bucket assembly further includes a passage extending between and providing fluid communication between the main cooling circuit and the platform cooling circuit. An end opening of the passage is defined in the lower surface of the platform cooling circuit. | 05-09-2013 |
20130177406 | GAS TURBINE ENGINE BEARING CHAMBER SEALS - A gas turbine engine sealing air system including a bearing chamber seal to prevent lubricant fluid loss from a fluid chamber, the sealing effected by ingress of sealing air. The system includes an air vent duct coupled to the bearing chamber seal. An ejector is located within the air vent duct to pump sealing air from the bearing chamber seal and through the air vent duct. A first duct is coupled between a starter air system of the gas turbine engine and the ejector to provide motive fluid to the ejector during gas turbine engine starting. | 07-11-2013 |
20140105733 | COMPRESSOR WITH COOLING FUNCTION - The inner wall surfaces on the discharge sides of a cooling area have arc-like curved surfaces. The curvature of upper-side inner wall surfaces above a boundary part and the curvature of lower-side inner wall surfaces below the boundary part are set to be different from one another, the boundary part being located above the center line of cooling devices. | 04-17-2014 |
20140161597 | Axial turbomachine blade with platforms having an angular profile - The present application relates to a splitter nose of an axial turbomachine designed to separate an annular flow into the turbomachine into a primary flow and a secondary flow for undergoing a thermodynamic cycle. The nose includes a de-icing device with a wall defining, at least partially, an annular channel. A hot oil stream created by the turbomachine circulates in this latter. The oil runs through the circular nose and de-ices it while itself getting cooled. The wall is located so as to form the leading edge of the said splitter nose. The wall is an open or closed strip such as a tube which can be fixed by bonding, welding or recessing. The present application also relates to a multi-flow turbomachine with splitter noses fitted with de-icing devices. | 06-12-2014 |
20140212279 | ENGINE COWL INCORPORATING AN EQUIPMENT VENTILATION CIRCUIT - The invention relates to an aircraft propulsion engine ( | 07-31-2014 |
20140356147 | CENTRIFUGAL COMPRESSOR HAVING COOLING SYSTEM - Embodiments of the present disclosure are directed towards a centrifugal compressor, a heat exchanger integral with the centrifugal compressor and configured to transfer heat from a fluid pressurized by the centrifugal compressor to a cooling fluid flow, and a cooling fluid supply head of the heat exchanger comprising an integral flow control valve configured to regulate a cooling fluid flow rate through the heat exchanger. | 12-04-2014 |