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WITH HEATING, COOLING OR THERMAL INSULATION MEANS

Subclass of:

416 - Fluid reaction surfaces (i.e., impellers)

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Class / Patent application numberDescriptionNumber of patent applications / Date published
416096000 Changing state mass within or fluid flow through working member or carrier 303
Entries
DocumentTitleDate
20080247875HORIZONTAL AXIS WIND TURBINE - The purpose of the invention is to protect, in a horizontal axis wind turbine with an exhaust aperture for exhausting air from within the nacelle, the exhaust aperture and the internal structures from storm winds through facing the exhaust aperture away from the storm wind, even when storm winds are received from all directions relative to the nacelle. A rotary duct 10-09-2008
20100061854Turbine blade damper arrangement - A turbine blade damper arrangement in which a damper is positioned against the undersides of the platforms of adjacent turbine blades. In operation, the damper is centrifugally urged into engagement with the blade platforms to provide damping of relative movement between the blades. The damper and platform surfaces that it engages are of part-cylindrical configuration in order to minimise gas leakage paths between the damper and blade platforms.03-11-2010
20090087312Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method - A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss.04-02-2009
20130058787Turbine airfoil - A turbine airfoil includes an airfoil body with a leading edge, trailing edge, and an exterior surface including a suction side and a pressure side located opposite to the suction side. The exterior surface shows away from the interior of the airfoil body. A thermal barrier coating system is present on the exterior surface of the airfoil body in a coated surface region. The airfoil also includes an uncoated surface region where a thermal barrier coating system is not present. The uncoated region extends on the suction side of the exterior surface from the trailing edge towards the leading edge to a boundary line between the coated surface region and the uncoated surface region, wherein the boundary line is located on the suction side between the leading edge and the trailing edge. The airfoil body also includes a step in the exterior surface extending along the boundary line.03-07-2013
20130058788LIGHT WEIGHT SHROUD FIN FOR A ROTOR BLADE - A turbine blade is provided and includes a tip end carrying a shroud and at least one fin, which extends radially away from the shroud. The fin includes a first sidewall and a second sidewall, which are spaced apart, arranged parallel to each other, and are connected to the shroud, and a cutting edge, which is connected to the first and second sidewalls. The cutting edge thereby creates a hollow space between the sidewalls, the shroud, and the cutting edge, and further extends radially away from the first and second sidewalls. Also provided is a method of manufacturing the blade by casting the blade as single piece with the hollow fin or by forging the blade; and machining the fin to create the first and second sidewalls and cutting edge thereby opening the hollow space between said sidewalls and the cutting edge.03-07-2013
20090246023CHAMBERED AIRFOIL COOLING - An airfoil assembly includes an airfoil with at least one cavity that is in communication with a source of cooling air. A baffle is disposed within that cavity and includes a plurality of openings for directing cooling air against the hot wall. A plurality of dividers extends between the baffle walls and the internal cavity to direct cooling air toward one of a leading edge chamber and a trailing edge chamber.10-01-2009
20130164133SANDWICH LAMINATE AND MANUFACTURING METHOD - A sandwich laminate for wind turbine blades includes a sandwich core material and an upper laminate part and a lower laminate part, wherein the upper laminate part and the lower laminate part have a thermoplastic matrix material and heating elements. The heating elements are electrically conductive fibres constituting electric circuits in the interior part of the thermoplastic matrix. Further, a wind turbine blade including such a sandwich laminate as well as a method of manufacturing such a sandwich laminate are provided.06-27-2013
20090074575COOLING CIRCUIT FLOW PATH FOR A TURBINE SECTION AIRFOIL - A cooled airfoil includes an impingement rib having a multiple of openings which supply a cooling airflow from a cooling circuit flow path toward an airfoil leading edge. The multiple of openings are offset in the impingement rib opposite an outer airfoil wall which includes gill holes. Offsetting the multiple of openings opposite an outer airfoil wall which includes the gill holes focuses the cooling airflow across turbulators to increase the cooling airflow dwell time to increase the thermal transfer therefrom in higher temperature airfoil areas.03-19-2009
20100284807BLADE COOLING - Cooling of turbine blades within a gas turbine engine is important. Coolant flows are taken from the engine to provide cooling effects but diminish the efficiency of the engine. Blades rotate and therefore centrifugal effects stimulate flow and pressure to maintain coolant flow presentation upon the blade. More cooling effectiveness is required towards the root of a blade in comparison with the tip. By providing cavities which incorporate return apertures coolant flow can be recycled. The cavities incorporate return portions on one side of a feed passage and a constriction is provided in passage. Thus, a proportion of coolant within the cavities is returned to the passage with pressure maintained by the rotational and centrifugal effects upon the coolant flow through the feed passage. Coolant flow is presented through outlet apertures as a film upon a surface of a blade.11-11-2010
20110293422SYSTEM AND METHOD FOR ENHANCED TURBINE WAKE MIXING VIA FLUIDIC-GENERATED VORTICES - A high pressure turbine (HPT) blade includes a substantially arcuate trailing edge including one or more fluid injection elements disposed therein. Each fluid injection element injects a fluid such as air into a desired trailing edge region of the HPT blade or vane to enhance mixing out of the wakes generated via the HPT blade or vane. The enhanced mixing out reduces HPT/LPT interaction losses and/or the axial gap between the HPT and LPT components in a gas turbine engine. The interaction losses include unsteady thermal wake segregation effects that lead to unexpected heat-up of endwalls (planforms and blade/vane-tips) of downstream blades/vanes, and further include aerodynamic losses, both transonic and subsonic.12-01-2011
20110293423ARTICLES WHICH INCLUDE CHEVRON FILM COOLING HOLES, AND RELATED PROCESSES - An article is described, including an inner surface which can be exposed to a first fluid; an inlet; and an outer surface spaced from the inner surface, which can be exposed to a hotter second fluid. The article further includes at least one row or other pattern of passage holes. Each passage hole includes an inlet bore extending through the substrate from the inlet at the inner surface to a passage hole-exit proximate to the outer surface, with the inlet bore terminating in a chevron outlet adjacent the hole-exit. The chevron outlet includes a pair of wing troughs having a common surface region between them. The common surface region includes a valley which is adjacent the hole-exit; and a plateau adjacent the valley. The article can be an airfoil. Related methods for preparing the passage holes are also described.12-01-2011
20130022466CONTROLLING OF A HEATING MAT ON A BLADE OF A WIND TURBINE - The present invention describes a blade for a wind turbine. The blade includes a heating mat for generating heat by resistive heating, wherein the heating mat is mounted to the blade. The heating mat includes a first heating power emitting section for emitting a first heating power and a second heating power emitting section for emitting a second heating power. The heating mat is coupleable to a power supply unit for transferring power to the heating mat in such a way that the first heating power differs to the second heating power.01-24-2013
20110142639MODULAR TURBINE AIRFOIL AND PLATFORM ASSEMBLY WITH INDEPENDENT ROOT TEETH - A turbine airfoil (06-16-2011
20100266410ROTOR BLADES FOR TURBINE ENGINES - A blade tip of a turbine rotor blade for a gas turbine engine, the turbine rotor blade including an airfoil and a root portion for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from the root portion to the blade tip, and a squealer tip cavity formed at the blade tip, the blade tip comprising: a trailing edge trench originating at the squealer tip cavity, wherein the trailing edge trench generally extends toward the trailing edge of the blade tip.10-21-2010
20100266409Method for Coating a Blade and Blade of a Gas Turbine - A method is provided for coating a hollow, internally cooled blade (10-21-2010
20120189447INFRARED RADIATION DEVICE, PARTICULARLY INFRARED RADIANT HEATING DEVICE HAVING AN INFRARED HEATER - An infrared device is provided, in particular an infrared radiation heating device having an infrared radiator for the heating of devices exposed to weather. The infrared device includes an emitter, wherein the emitter for radiating the infrared radiation is inserted in a housing, and the emitter is protected on the emitting side by a protection unit for the emitted radiation. The infrared radiator, the inner housing wall, and the unit are arranged such that cooling takes place by natural convection. A method is also provided for operating such a device in a wind turbine.07-26-2012
20100124499METHODS AND APPARATUS RELATING TO TURBINE AIRFOIL COOLING APERTURES - An airfoil assembly for a turbine engine, that may comprise: an airfoil that includes at least one panel opening formed therein; and an aperture panel that includes at least one cooling aperture; wherein the panel opening and the aperture panel are configured such that, upon installation of the aperture panel within the panel opening, a substantially smooth outer surface of the airfoil is formed and at least one of the cooling apertures of the aperture panel forms an exit passageway from at least one hollow internal cavity within the airfoil.05-20-2010
20110171028Boron-based Refractory Coating for a Wind Turbine Component - A wind turbine including at least one component with a surface is provided. The surface is coated at least in part with a refractory layer, preferably a boron-based refractory layer. Further, a wind farm including such a wind turbine and a method are provided.07-14-2011
20090280011Blade arrangement - With regard to gas turbine engines it will be appreciated that blades are typically cooled in order to ensure that the materials from which the blades are formed remain within acceptable operational parameters. Coolant is judiciously used in order to maintain engine operational efficiency. Unfortunately with regard to rotor blades horseshoe vortices tend to increase heating towards a pressure side of a blade resulting in localised overheating. Such localised overheating may result in premature failure of the blade component. Traditionally coolant flows have been presented over a forward projection of a blade platform. In such circumstances coolant flow will not be used as efficiently as possible with regard to protecting a pressure side of a platform in a blade assembly and arrangement. By provision of a deflector element on the forward blade platform coolant flow can be proportioned either side of a leading edge of the blade. In such circumstances generally asymmetric coolant flow is provided normally biased towards the pressure side in order to enhance cooling efficiency. A suction side in an adjacent blade assembly is cooled by spent coolant and hot gas flow from the pressure side of a neighbouring blade upstream in the assembly.11-12-2009
20100061853SYSTEM FOR HEATING AND COOLING WIND TURBINE COMPONENTS - A heating and cooling system for a wind turbine is provided and includes a gearbox, gearbox heat exchanger, generator, generator heat exchanger, and a cooling duct. The cooling duct is connected to the gearbox and generator heat exchangers, and is used to transport air across both heat exchangers to cool the gearbox and generator.03-11-2010
20080286104Near wall cooling for a highly tapered turbine blade - A turbine blade having a pressure sidewall and a suction sidewall connected at chordally spaced leading and trailing edges to define a cooling cavity. Pressure and suction side inner walls extend radially within the cooling cavity and define pressure and suction side near wall chambers. A plurality of mid-chord channels extend radially from a radially intermediate location on the blade to a tip passage at the blade tip for connecting the pressure side and suction side near wall chambers in fluid communication with the tip passage. In addition, radially extending leading edge and trailing edge flow channels are located adjacent to the leading and trailing edges, respectively, and cooling fluid flows in a triple-pass serpentine path as it flows through the leading edge flow channel, the near wall chambers and the trailing edge flow channel.11-20-2008
20100143132TURBINE BLADE WITH REVERSE COOLING AIR FILM HOLE DIRECTION - A gas turbine engine includes turbine blades having film cooling holes at an outer face of an airfoil wherein the film cooling holes are designed to be better filled with air. In a disclosed embodiment, the film cooling holes include a meter section extending along a direction having a main component extending from a blade tip to a blade root. In addition, a diffused section communicates with the meter section at a face of the airfoil. The diffused section is spaced toward the blade tip from the meter section. In this manner, centrifugal force ensures the diffused section is also filled with air.06-10-2010
20120093649TURBINE BLADES AND TURBINE ROTOR ASSEMBLIES - A turbine blade includes an airfoil defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root, and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the interior including an airfoil cooling circuit for directing airflow through the blade, and a platform supporting the airfoil and having a leading side edge, a trailing side edge, suction side edge, a pressure side edge, an airfoil-facing wall, and a root-facing wall, the platform including a platform cooling circuit having an inlet on the leading side edge and an outlet. The turbine blade may be included in a turbine rotor assembly.04-19-2012
20090004006DEVICE FOR COOLING SLOTS OF A TURBOMACHINE ROTOR DISK - The invention relates to a device for cooling the slots of a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange that extends upstream from a radially upstream face of the disk. The device also comprises a retaining annulus having a flange that is placed around the flange of the disk, co-operating therewith to provide a space forming a cooling air diffusion cavity, said cavity opening out into the bottom of each of the slots of the disk, and a plurality of air admission orifices opening out into the diffusion cavity at the upstream end thereof, the cavity having means at its downstream end for reducing the flow rate of air penetrating into the slots of the disk that are situated radially in register with air admission orifices.01-01-2009
20090097977SERPENTINE MICROCIRCUIT COOLING WITH PRESSURE SIDE FEATURES - In accordance with the present invention, there is provided a turbine engine component having an airfoil portion with a pressure side and a suction side, a first microcircuit embedded in a wall forming the pressure side, an internal cavity containing a supply of cooling fluid, the first microcircuit having an inlet leg, an intermediate leg, and an outlet leg, and a plurality of communication holes between the internal cavity and the outlet leg. In a preferred embodiment, the outlet leg is provided with at least one set of features for locally accelerating cooling flow in the outlet leg and for increasing heat pick-up ability.04-16-2009
20100014974APPARATUS AND METHOD FOR COOLING A WIND TURBINE HUB - A wind turbine, in an exemplary embodiment, includes a hub and at least one blade coupled to the hub, at least one electric pitch motor operatively coupled to the at least one blade, and a pitch motor control system operatively coupled to the at least one pitch motor. The pitch motor control system includes a plurality of components that produce excess heat during operation. The plurality of components that produce excess heat during operation are mounted to an inside surface of the hub01-21-2010
20120195758Methods and Systems For Controlling Thermal Differential In Turbine Systems - Method and system are provided for controlling a thermal differential within a turbine rotor for use with a turbine system. A thermal barrier coating is applied to a surface of the turbine rotor. The surface is proximate to a wheel rim of the turbine rotor.08-02-2012
20110129343Guide Vane for a Condensation Steam Turbine and Associated Condensation Steam Turbine - A guide vane of a condensation turbine steam turbine is provided, wherein the guide vane includes a heating resistor. The guide vane includes fiber composite material at least in some regions. The heating resistor may be embodied as a heating wire or as a heating film. A condensation steam turbine having a guide vane as described above is also provided.06-02-2011
20100178168Rotor Cooling Circuit - A cooling circuit serves to provide cooling air in a rotor having a compressor rotor and a turbine rotor. The cooling circuit includes a first cooling path through the compressor rotor in series with a second cooling path through the turbine rotor such that one amount of cooling air is used for cooling both the compressor rotor and the turbine rotor. The construction enables a reduction in cooling air requirements, thereby increasing power plant efficiency.07-15-2010
20100014975Mast mounted heating system for a wind machine - An air flow heating system for wind machine is provided, which can be mounted to a conventional, propeller driven wind machine's mast or tower, to provide a stream of heated updrafting air, for use by the wind machine, to supplement the overall convective air current in the vicinity of the wind machine. The system includes a heater assembly with a plurality of heater arms, each heater arm having at least a single burner, and each burner provided with a combustible fuel. The heater assembly mounts to the middle portion of the wind machine mast, below the propeller blade's rotation, thereby providing increased induced updraft and air mixing effects, while heating the air supplied to the propeller, without interfering with air flow to, or from the propeller, which is especially useful in freeze protection for crops and orchards01-21-2010
20090074576Turbine blade with cooling breakout passages - A turbine airfoil with a plurality of breakout passages located just beneath a thermal barrier coating or just beneath the metal surface of the airfoil. The breakout passages are connected to an internal cooling air passage and allow for film cooling air to flow when a surface over the breakout passage has been chipped or eroded away to provide for additional cooling to the damaged airfoil surface. The breakout passages are formed during the casting process of the airfoil using a plurality of molding pieces. The breakout passages are formed along a direction of the pulling direction of the respective mold piece. This allows for the solidified airfoil to be easily removed from the mold assembly.03-19-2009
20110123335Arrangement with a nacelle and a radiator - An arrangement with a nacelle and a radiator of a wind turbine is provided. The nacelle is rotatable connected with the radiator. Thus, a joint component of the wind turbine is built by these elements. The connection is constructed and arranged such that the radiator is allowed to pivot between a first position and a second position. The radiator is locked in the first position and projects above the nacelle when the radiator is used to remove heat from the nacelle to the environment. When the radiator is locked in the second position the radiator is close to a side of the nacelle. Thus a minimum height of the joint component is achieved.05-26-2011
20110123336Arrangement with a nacelle and a radiator arrangement - An arrangement with a nacelle and a radiator arrangement of a wind turbine is provided. The radiator arrangement includes a guiding assembly. The nacelle includes a guiding assembly, too. The guiding assembly of the radiator is positioned and constructed in a way that the guiding assembly interacts with the guiding assembly of the nacelle. Thus, the radiator arrangement is lifted and passed to a final position on top of the nacelle by the engaged guiding assemblies.05-26-2011
20110123333Arrangement with a nacelle and a radiator arrangement - A radiator arrangement is arranged on a nacelle of a wind turbine via a sliding arrangement. The sliding arrangement is constructed and arranged in a way that the radiator arrangement is allowed to change its position in reference to the nacelle between a first position and a second position. The radiator arrangement allows service from inside the nacelle if the radiator arrangement is the first position and the radiator arrangement transfers heat in its second position.05-26-2011
20110123334Arrangement with a nacelle and an instrument bar - An arrangement with a nacelle and an instrument bar is provided. The instrument bar is arranged on top of the nacelle. A rotational axis interacts with the nacelle and with the instrument bar. The rotational axis is constructed and arranged such that the instrument bar is allowed to pivot between a first position and a second position in reference to the top side of the nacelle. The instrument bar projects above the top side of the nacelle when locked in the first position, while the instruments are operated. The instrument bar is locked close to the top side of the nacelle in the second position to allow access to the instruments.05-26-2011
20130136598WIND TURBINE ROTOR BLADE HAVING A HEATING ELEMENT AND A METHOD OF MAKING THE SAME - The invention relates to a wind turbine rotor blade having a blade root, a blade tip, two interconnected rotor blade half shells, which include a fiber-reinforced plastics material, and an electrical heating element, which is arranged on an outer side of the rotor blade and has a blade root end and a blade tip end, wherein the blade tip end is connected via an electrical line leading to the blade root and at least a first segment of the electrical line, which is arranged on an inner side of one of the rotor blade half shells, is made of a carbon fiber material. Further, the present invention relates to a method for making a wind turbine rotor blade having an electrical heating element.05-30-2013
20130136599AEROFOIL COOLING ARRANGEMENT - An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall and a suction wall, at least one of the pressure and suction walls comprise corrugations and a coolant hole on an inner surface, the corrugations define a downstream surface and the coolant hole having an inlet defined in the downstream surface.05-30-2013
20110129342TURBINE ASSEMBLIES WITH IMPINGEMENT COOLING - A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.06-02-2011
20110116928OPEN-HUB CENTRIFUGAL BLOWER ASSEMBLY - An open-hub centrifugal blower includes a hub rotatable about an axis, an outer rim concentric with the hub, a plurality of blades coupled to the outer rim, a plurality of spokes interconnecting the hub and the outer rim, and a cooling rib extending from at least one of the spokes.05-19-2011
20120243995COMPONENTS WITH COOLING CHANNELS FORMED IN COATING AND METHODS OF MANUFACTURE - A method of fabricating a component is provided. The method includes depositing a structural coating on an outer surface of a substrate, where the substrate has at least one hollow interior space. The method further includes forming one or more grooves in the structural coating. Each groove has a base and extends at least partially along the substrate. The method further includes depositing at least one additional coating over the structural coating and over the groove(s), such that the groove(s) and the additional coating together define one or more channels for cooling the component. The method further includes forming one or more access holes through the base of a respective groove, to connect the respective groove in fluid communication with the respective hollow interior space, and forming at least one exit hole through the additional coating for each channel, to receive and discharge coolant from the respective channel. A component with cooling channels formed in a structural coating is also provided.09-27-2012
20100178169Seal Coating Between Rotor Blade and Rotor Disk Slot in Gas Turbine Engine - A gas turbine rotor blade and rotor disk arrangement is provided. The rotor blade and the rotor disk includes a coating in order to seal the gap which normally exists between the bottom part of the blade root and the bottom part of the disk slot. The coating may be applied to the blade root or to the disk itself on the bottom part of the disk slot. The coating is preferably an abradable nickel-alloy Bentonite coating. The coating may also be applied to only a portion of the areas being sealed, omitting a portion at the start of the slot or at the start of one of the lobes of the blade root, so that a lead-in is formed, whereby the blade can more easily be inserted into the slot.07-15-2010
20090028707Apparatus and method for repairing airfoil tips - A method of repairing an airfoil for a gas turbine engine includes removing a damaged portion of the airfoil at a radially outward tip of the airfoil, securing temporarily a portion of a ceramic core stub within an internal cavity of the airfoil, applying new metallic material to the airfoil covering an exposed portion of the ceramic core stub, machining the airfoil to remove an excess portion of the new metallic material, and removing the ceramic core stub from the internal cavity of the airfoil.01-29-2009
20110211958WIND-POWER-GENERATOR FAN UNIT AND WIND POWER GENERATOR - There are provided a wind-power-generator fan unit and a wind power generator in which the consumption of driving power for a cooler fan that cools a device provided in the wind power generator can be reduced. This wind-power-generator fan unit includes cooler fans that discharge air in a housing that accommodates devices that perform at least power generation by the rotational operation of rotor blades to the outside of the housing through the devices; and a control unit that controls the operation of the cooler fans on the basis of the temperatures of the devices and the operating states of the devices.09-01-2011
20120034081COMPRESSOR BLADE ROOT HEATING SYSTEM - A compressor blade root heating system for a turbine engine is disclosed. The compressor blade root heating system may be formed from one or more induction heaters formed from one or more induction coils positioned in close proximity to a root of a compressor blade. In one embodiment, the induction heater may be coupled to a static casing component positioned immediately upstream of a first row of compressor blades on a rotor assembly such that the induction heater is stationary during turbine engine operation. The induction heater causes eddy current formation, which heats the row one compressor blades. This heating increases the fracture toughness of the material forming the rotor and compressor blades, thereby increasing the mechanical life cycle.02-09-2012
20120148406TURBINE ROTOR DISKS AND TURBINE ASSEMBLIES - A turbine rotor disk is provided. The turbine rotor disk includes a hub, a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface.06-14-2012
20120121415TURBOMACHINE VANE AND METHOD OF COOLING A TURBOMACHINE VANE - A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.05-17-2012
20110189015turbine engine component for adaptive cooling - A turbine engine component, particularly an aerofoil, including a body is provided. The turbine engine component includes a first surface exposed to a working fluid of high temperatures during operation, a second surface including a depression, the depression is exposed to a cooling fluid during operation and oriented such that, starting from the second surface, the depression deepens in the direction of a back face of the first surface. Furthermore the body includes a body portion between the back face and the first surface. The depression is defined such that a diameter of the depression decreases from the second surface in direction of the back face.08-04-2011
20110217169Wind turbine with liquid medium distribution system - A wind turbine with a tower, a nacelle, a main shaft, a hub and blades is provided. The wind turbine also includes a liquid medium distribution system for transport of liquid medium in the wind turbine. The liquid medium distribution system has a first distribution sub-system located in the tower, a second distribution sub-system located in the nacelle, a third distribution sub-system located in the hub, a tower-nacelle-interface connecting the first distribution sub-system to the second distribution sub-system, and a nacelle-hub-interface connecting the second distribution sub-system to the third distribution sub-system. Further, a method of transporting liquid medium in a wind turbine is provided.09-08-2011
20100196160COOLED TURBINE BLADE SHROUD - A turbine blade for use in high temperature applications includes an as-cast airfoil portion and an as-cast outer tip shroud portion and the outer tip shroud portion has at least one as-cast internal cooling circuit for cooling the outer tip shroud, and the at least one as-cast internal cooling circuit having a plurality of exits for discharging cooling air over exterior surfaces of the shroud. A process for forming a turbine blade comprises the steps of forming an as-cast turbine blade having an airfoil portion and a tip shroud and the forming step comprising forming at least one as-cast cooling circuit within the tip shroud.08-05-2010
20120148407WIND TURBINE GENERATOR - A wind turbine generator includes a tower, at least one blade, a hub supporting the blade, a nacelle supported by the tower and having a duct part with an intake port and an exhaust port, and a heat exchanger provided in the duct part and cooling a cooling medium for a heat-producing component inside the tower or nacelle. The wall of the nacelle has a double wall structure constituted of an inner wall and an outer wall in an area where the duct part is provided. The inner wall forms a bottom surface of the duct part and has a curved portion which curves inward toward a center line of the nacelle with increasing distance from the hub. The duct part increases in cross-section from a side of the intake port to a side of the exhaust port at least in an area where the curved portion is formed.06-14-2012
20120148405COOLING CIRCUIT FOR A DRUM ROTOR - A cooling circuit for a drum rotor of a multi-stage steam turbine including tangential female dovetail slots in the drum rotor for tangential entry dovetailed buckets. Axial female dovetail slots are cut into drum rotor projections between stages of the tangential entry buckets for mounting axial inserts. The axial inserts may include axial and radial cooling passages allowing cooler external steam to cool the drum rotor flow through tangential cooling spaces between the tangential female dovetail slots and the tangential entry dovetailed buckets.06-14-2012
20110318181APPARATUS FOR PREVENTING ICE ACCRETION - Aerofoils (12-29-2011
20080279688HEATED ENGINE NOSE CONE USING SPIRAL CHANNELS - A nose cone of a turbomachine, such as an aircraft engine, is heated to prevent ice formation. The nose cone is configured as a conical shell positioned concentrically over an inner shell with a space therebetween. Spiral spacers in the space provide distributed passages through which heated lubricating oil flows. A system for separating entrained air from the lubricating oil as part of this mechanism is disclosed.11-13-2008
20120003091ROTOR ASSEMBLY FOR USE IN GAS TURBINE ENGINES AND METHOD FOR ASSEMBLING THE SAME - A method of assembling a rotor assembly for use with a turbine engine. The method includes providing a rotor shaft and coupling at least one rotor disk to the rotor shaft such that a cooling path is defined between the rotor shaft and the rotor disk. The rotor disk includes a substantially cylindrical body that has upstream and downstream surfaces extending between a radially inner edge and a radially outer edge. A first cooling plate is coupled to the downstream surface of the rotor disk to define a cooling duct between the first cooling plate and the downstream surface. The cooling duct is configured to channel a cooling fluid from the cooling path to the towards the outer edge.01-05-2012
20090104035ADVANCED TURBULATOR ARRANGEMENTS FOR MICROCIRCUITS - A passageway is provided through which a cooling fluid flows in a first direction. The passageway has a plurality of trip strips positioned within the passageway. Adjacent one of the trip strips are oriented to converge towards each other at a first end to form an apex portion and to form a region in which turbulence is created. The apex portion is oriented at an angle with respect to the first direction.04-23-2009
20120282096Direct drive wind turbine with a thermal control system - A direct drive wind turbine with a thermal control system has a generator with a rotor and a stator and a bearing with an inner ring and an outer ring connecting the rotor and the stator rotatively. The thermal control system includes a cooling system and a heating system. The cooling system includes at least one heat sink which is in thermal communication with the inner ring of the bearing and a heat dissipater which is in thermal communication with the heat sink. The heating system includes at least one heating element being in thermal communication with the outer ring of the bearing.11-08-2012
20100092293ROTOR FOR A GAS TURBINE - A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.04-15-2010
20120163975PLATFORM WITH COOLING CIRCUIT - A turbine engine component has an airfoil portion, which airfoil portion is bounded by a platform at one end. The platform has an as-cast open cavity bordered by at least one as-cast landing. A plate is welded to the at least one as-cast landing to cover and close the as-cast open cavity. A process for forming the turbine engine component is described.06-28-2012
20120134818WIND TURBINE GENERATOR - A wind turbine generator includes: a rotor hub configured to be provided inside a rotor head and contain apparatuses; a hatch configured to be provided in a front of the rotor hub; and a heat exchanger configured to be provided in an opening of the hatch. The heat exchanger includes: a partition portion configured to be put on the opening, and heat exchanging members configured to be provided so as to penetrate the partition portion, a side of one end being located inside the rotor hub and a side of the other end being located outside the rotor hub.05-31-2012
20120076654TURBINE AIRFOIL AND METHOD FOR COOLING A TURBINE AIRFOIL - According to one aspect of the invention, a turbine includes a first sidewall, an airfoil positioned between the first sidewall and a second sidewall and a first passage in the airfoil proximate a high temperature region, the first passage configured to receive a cooling fluid, wherein the high temperature region is near an interface of the first sidewall and a trailing edge of the airfoil. The turbine further includes a first diffuser in fluid communication with the first passage, the first diffuser configured to direct the cooling fluid to form a film on a surface of the first sidewall03-29-2012
20120076653TURBINE BLADE TIP WITH VORTEX GENERATORS - A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.03-29-2012
20090060741TURBINE ENGINE BLADE COOLING - A blade is provided for a turbine engine that includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating and an uncoated shelf adjacent to the thermal barrier coating without the thermal barrier coating. A cooling hole extends from an internal passageway through the exterior surface to an exit. A scarfed channel is recessed in the exterior surface and interconnected to the cooling hole at the exit. The scarfed channel extends to a blade tip end surface. The scarfed channel protects the cooling fluid exiting the cooling hole from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels also increase the surface area exposed to the cooling fluid to increase the heat transfer rate.03-05-2009
20120257970POWER GENERATING APPARATUS OF RENEWABLE ENERGY TYPE - A power generating apparatus of renewable energy type includes a tower, a nacelle which is supported rotatably by a tip portion of the tower; a main shaft rotatable with a blade; a hydraulic pump which is housed in the nacelle and is driven by rotation of the main shaft; a hydraulic motor which is driven by operating oil supplied from the hydraulic pump; a generator which is coupled to the hydraulic motor; an operating-oil line which is provided between the hydraulic pump and the hydraulic motor and through which the operating oil circulates; a cooling-medium line through which cooling medium for cooling the operating oil circulates via an intermediate heat exchanger; and a main heat exchanger which cools the cooling medium by heat exchange with cool water source around a base portion of the tower, and one of the operating-oil line.10-11-2012
20120082550APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES - A platform cooling configuration in a turbine rotor blade that includes platform slot formed through at least one of the pressure side slashface and the suction side slashface; a removably-engaged impingement insert that separates the platform into two radially stacked plenums, a first plenum that resides inboard of a second plenum; a high-pressure connector that connects the first plenum to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the second plenum to the low-pressure coolant region of the interior cooling passage.04-05-2012
20120082549APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES - A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that in operation, includes at least a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside. The platform cooling arrangement may include: a plate that comprises a plate topside; a channel formed on the plate topside, the channel comprising an upstream end and a downstream end, and being open through the plate topside such that, upon attaching the plate to the platform, the platform underside comprises a channel ceiling; a high-pressure connector that connects the upstream end of the channel to the high-pressure coolant region of the interior cooling passage; and a low-pressure connector that connects the downstream end of the channel to the low-pressure coolant region of the interior cooling passage.04-05-2012
20120082548APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES - A platform cooling arrangement in a turbine rotor blade having a platform, wherein the rotor blade includes an interior cooling passage, and wherein, in operation, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside. The platform cooling arrangement may include: a first plate that resides inboard and in spaced relation to the platform underside and forming a first plenum; a second plate that resides inboard and in spaced relation to the first plate, the second plate forming a second plenum. The second plenum includes an inlet channel that connects to the high-pressure coolant region of the interior cooling passage, and the first plenum includes an outlet channel that connects to the low-pressure coolant region of the interior cooling passage.04-05-2012
20090016881TURBINE BLADE AND GAS TURBINE EQUIPPED WITH A TURBINE BLADE - The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane and has a platform that extends transversally to the blade axis. The aim of the invention is to guarantee the improved cooling of a platform region and the transition region from a turbine blade to a platform of a turbine blade, thus ensuring the cooling of the delimitation of a flow channel in a gas turbine. To achieve this, the platform comprises a first platform wall that does not support the vane and a second platform wall that supports said vane. According to the inventive concept, at the root of the vane and over the course of the transition region from the turbine blade to the platform, said first platform wall is aerodynamically curved and the course of the second platform wall has a receding shoulder in relation to the first platform wall, as a continuation of the vane.01-15-2009
20130022465HEATING MATS ARRANGED IN A LOOP ON A BLADE - A wind turbine blade is disclosed. The blade includes a heating mat for generating heat. The heating mat is mounted at an outer surface of the blade. The heating mat includes a first section with a first end section and a second section with a second end section. The first end section and the second end section are electrically connectable to a respective power terminal for supplying power to the heating mat. The second end section defines an opposite end section of the heating mat in a longitudinal direction of the heating mat with respect to the first end section. The first section and the second section run along the surface of the blade in one or more loops from the first end section to the second end section.01-24-2013
20080253890Co-forged nickel-steel rotor component for steam and gas turbine engines - A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an inner disk formed from a first material, such as steel, and an outer ring formed from a second material, such as a nickel alloy, having a larger thermal expansion coefficient than the first material forming the inner disk. The ring may include an inner aperture having a conical shape, and the disk may have an outer surface with a conical shape and a diameter with a portion that is larger than a portion of the ring. The ring may be heated such that the aperture expands to a size greater than the largest diameter of the inner disk. The ring may be positioned over the disk and allowed to cool to allow the ring to be attached to the disk. The ring and disk may then be co-forged.10-16-2008
20080247874Dual flow fan heat sink application - A cooling system includes a fan assembly that is rotated to move air in a primary path through a housing. The fan assembly includes a hub and a plurality of spaced reinforcing ribs that establish channels between a motor casing and the interior of the hub. A heat sink assembly is axially spaced from a hub bottom to define an air cavity that is in communication with a gap. The hub includes a tube that defines an air passage to establish communication with the cavity. A plurality of air vanes extend in a spiral path from the hub bottom and into the air cavity to move air through the air passage and create turbulence over the heat sink assembly. The air vanes move the air over the heat sink assembly and through the air passage to establish communication between the channels and the air cavity.10-09-2008
20130170992WIND TURBINE ROTOR BLADE HAVING AN ELECTRICAL HEATING ARRANGEMENT AND METHOD OF MAKING THE SAME - A wind turbine rotor blade is assembled from a first and a second rotor blade half shell made of a fiber-reinforced plastics material. An electrical heating arrangement includes a first heating element connected to the first rotor blade half shell and having a blade root end and a blade tip end and a second heating element connected to the second rotor blade half shell also having a blade root end and a blade tip end. The heating arrangement also includes a third heating element connected to the rotor blade half shells and having a blade root end and a blade tip end. The blade tip ends of the first, second and third heating elements are mutually electrically connected. The blade root ends of the first, second and third heating elements are connected to respective electrical connecting lines.07-04-2013
20130177420Turbine Vane Seal Carrier with Slots for Cooling and Assembly - The present application provides a seal carrier for use about a number of flow orifices of a platform of a turbine nozzle. The seal carrier may include an inner surface facing the platform with the inner surface having a number of slots therein aligning with the flow orifices of the platform and an opposed outer surface with a seal positioned about the outer surface.07-11-2013
20080219845FAN - A fan includes an impeller, a motor, a plurality of first engaging members and a plurality of second engaging members. The impeller includes a hub and a plurality of blades disposed around the hub. The motor includes a rotor housing coupled with the hub, and the motor is for driving the impeller to rotate. The first engaging members are disposed on an inner side of the top surface of the hub, and the second engaging members are disposed on the top surface of the housing. When the impeller and the rotor housing are assembled, the second engaging members are disposed corresponding to the first engaging members, so that parts of the first engaging members are engaged into and assembled with the second engaging members.09-11-2008
20130115085THERMAL BARRIER FOR TURBINE BLADES, HAVING A COLUMNAR STRUCTURE WITH SPACED-APART COLUMNS - A process for depositing a ceramic layer on a metal substrate for producing a thermal barrier, the process including depositing the ceramic in a columnar structure. The deposition is carried out through a grid pierced with holes, which is positioned parallel to a surface of the substrate so as to produce ceramic columns separated from one another by a space. The process can further include a subsequent depositing of an isotropic ceramic layer in the spaces.05-09-2013
20130129512DEVICE FOR REMOVING MOISTURE FROM A HYDRAULIC MEDIUM - The device according to the invention for removing moisture from a hydraulic medium (05-23-2013
20130142652FAN ARRANGEMENT - A fan arrangement (06-06-2013
20080199317Local indented trailing edge heat transfer devices - A turbine engine component has an airfoil portion having a pressure side and a suction side, a trailing edge discharge slot, and a suction side lip downstream of an exit of the trailing edge slot. The suction side lip is provided with negative features for increasing local heat transfer coefficient in the region of the suction side lip.08-21-2008
20130156579AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING - A gas turbine engine including: an ambient-air cooling circuit (06-20-2013
20120282095COOLING ARRANGEMENT OF A WIND TURBINE - A cooling arrangement is provided for a wind turbine. The wind turbine has a nacelle. The cooling arrangement includes a cooling device and a platform. The cooling device is arranged on top of the nacelle and which is configured to remove heat of the wind turbine to the ambient air. The platform is located on top of the nacelle and which is configured to be approached by a helicopter. The platform includes a barrier, which surrounds at least a part of the platform. The barrier includes at least a part of the cooling device.11-08-2012
20110286844LUBRICANT HEATING MECHANISM, GEAR MECHANISM , AND WIND TURBINE GENERATOR USING THE SAME - A lubricant heating mechanism is provided with a tank accumulating therein lubricant; a lubricant pump; a heater provided in the tank to heat the lubricant; and a baffle plate at least partially covering the heater. The tank is provided with a suction port drawing out the lubricant from the tank to the lubricant pump. The baffle plate is provided to convect the heated lubricant toward the suction port.11-24-2011
20130195661FIXATION OF A HEATING MAT TO A BLADE OF A WIND TURBINE - A blade for a wind turbine includes at least one heating mat for generating heat, wherein the heating mat is mounted at an outer surface of the blade. The blade further includes at least one through-hole running from an inner space of the blade to the outer surface of the blade. The blade further has at least one conductive element, wherein the conductive element is electrically coupled to the heating mat. The conductive element is inserted in the through-hole for generating an electric connection between the inner space and the outer surface.08-01-2013

Patent applications in class WITH HEATING, COOLING OR THERMAL INSULATION MEANS

Patent applications in all subclasses WITH HEATING, COOLING OR THERMAL INSULATION MEANS