WITH HEATING, COOLING OR THERMAL INSULATION MEANS
Patent class list (only not empty are listed)
|Class / Patent application number
|Number of patent applications / Date published
|Changing state mass within or fluid flow through working member or carrier
|Local 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.
|FAN - 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.
|Dual 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.
|HORIZONTAL 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
|Co-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.
|HEATED 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.
|Near 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.
|DEVICE 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.
|TURBINE 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.
|Apparatus 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.
|TURBINE 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.
|COOLING 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.
|Turbine 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.
|Turbine 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.
|SERPENTINE 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.
|ADVANCED 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.
|CHAMBERED 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.
|Blade 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.
|APPARATUS 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 hub
|Mast 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 orchards
|SYSTEM 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.
|Turbine 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.
|ROTOR 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.
|METHODS 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.
|TURBINE 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.
|Rotor 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.
|Seal 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.
|COOLED 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.
|Method for Coating a Blade and Blade of a Gas Turbine - A method is provided for coating a hollow, internally cooled blade (
|ROTOR 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.
|BLADE 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.
|OPEN-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.
|Arrangement 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.
|Arrangement 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.
|Arrangement 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.
|Arrangement 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.
|TURBINE 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.
|Guide 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.
|MODULAR TURBINE AIRFOIL AND PLATFORM ASSEMBLY WITH INDEPENDENT ROOT TEETH - A turbine airfoil (
|Boron-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.
|turbine 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.
|WIND-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.
|Wind 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.
|LUBRICANT 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.
|SYSTEM 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.
|ARTICLES 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.
|APPARATUS FOR PREVENTING ICE ACCRETION - Aerofoils (
|ROTOR 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.
|COMPRESSOR 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.
|TURBINE 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.
|TURBINE 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 sidewall
|APPARATUS 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.
|APPARATUS 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.
|APPARATUS 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.
|TURBINE 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.
|TURBOMACHINE 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.
|WIND 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.
|COOLING 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.
|TURBINE 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.
|WIND 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.
|PLATFORM 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.
|INFRARED 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.
|Methods 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.
|COMPONENTS 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.
|POWER 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.
|COOLING 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.
|Direct 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.
|HEATING 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.
|CONTROLLING 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.
|Turbine 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.
|LIGHT 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.
|SPOKED ROTOR FOR A GAS TURBINE ENGINE
|THERMAL PLUG FOR TURBINE BUCKET SHANK CAVITY AND RELATED METHOD
|THERMAL 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.
|DEVICE FOR REMOVING MOISTURE FROM A HYDRAULIC MEDIUM - The device according to the invention for removing moisture from a hydraulic medium (
|WIND 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.
|AEROFOIL 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.
|FAN ARRANGEMENT - A fan arrangement (
|AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING - A gas turbine engine including: an ambient-air cooling circuit (
|SANDWICH 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.
|WIND 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.
|Turbine 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.
|FIXATION 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.
|TAPERED THERMAL COATING FOR AIRFOIL - An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.
|ALUMINIDE OR CHROMIDE COATINGS OF CAVITIES - Disclosed is a process for producing an alloyed, in particular multiple-alloyed aluminide or chromide layer on a component by alitizing or chromizing. First a green compact layer (
|MOVING BLADE AND TURBOMACHINE - A moving blade for a turbomachine, in particular an aircraft engine, is disclosed, having an inner shroud which has a front elongation for forming an axial overlap with an upstream guide blade, and on which at least one flow guide element for deflecting a leakage flow of a cooling air flow in the peripheral direction is situated. The at least one flow guide element is guided beyond a leading edge of the elongation. A turbomachine having a plurality of these types of moving blades is also disclosed.
|SYSTEMS FOR HEATING ROTOR DISKS IN A TURBOMACHINE - A system includes a turbomachine. The turbomachine includes at least one rotor disk. The system also includes a rotor disk heating system configured to resistively heat at least a portion of the at least one rotor disk via an electrical current or voltage applied to the portion of the at least one rotor disk.
|TURBINE BLADE WITH CHAMFERED SQUEALER TIP FORMED FROM MULTIPLE COMPONENTS AND CONVECTIVE COOLING HOLES - A squealer tip usable in repair systems and formed from a pressure side outer weld rib and a suction side outer weld rib extending radially outward from a tip of the turbine blade and resting upon pressure side and suction side weld members separated by a mid-chord member is disclosed. The pressure and suction side outer weld ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure side outer weld rib may include a chamfered pressure side with film cooling holes having exhaust outlets positioned therein. The pressure and suction side weld members may be configured to retain the mid-chord member in position with over extending side surfaces.
|Near-Wall Serpentine Cooled Turbine Airfoil - Certain exemplary embodiments can provide a serpentine coolant flow path formed by inner walls in a cavity between pressure and suction side walls of a turbine airfoil and/or can be adapted to provide cooling matched to the heating topography of the airfoil, minimize differential thermal expansion, revive the coolant, and/or minimize the flow volume needed.
|ROTOR BLADE WITH HEATING DEVICE FOR A WIND TURBINE - There is provided a wind power installation rotor blade comprising at least one electrically operable heating mat which is fixed in the interior of the rotor blade.
|Wind Turbine Generator System - According to the present invention, a wind turbine generator system is provided which can not only remove the influence of salt damage in case the system is established off-shore, but even if the facility becomes larger, which can also cool equipment and the generator provided in the tower and can reduce the possibility of decreasing power generation efficiency. The wind turbine generator system of the present invention comprising a rotor having a hub and blades; a generator connected with the rotor by way of a main shaft connected with the hub; a nacelle which contains at least the generator and supports the rotor pivotally by way of the main shaft; a tower on a top of which the nacelle is supported, and opposite to the top the tower is fixed to a base, wherein a heat exchanger is provided at the tower close to the base and cooling medium passes through the heat exchanger by way of a pipe arrangement, and thereby the heat of the cooling medium and the heat of air inside the tower are exchanged and the air inside the tower is cooled.
|ROTORCRAFT ROTOR FITTED WITH LEAD-LAG DAMPERS HOUSED IN SLEEVES CONNECTING BLADES TO A HUB OF THE ROTOR - A rotorcraft rotor fitted with a device for damping lead-lag oscillations of the blades (
|TURBOFAN, AND AIR-CONDITIONING APPARATUS - A turbofan and air-conditioning apparatus that can suppress the separation of an airflow from the surface of each blade, and can reduce noise due to turbulence is obtained.
|WIND TURBINE BLADE COMPRISING RESISTIVE HEATING MEANS - A wind turbine blade
|Automatic Distributed Heating System for a Ram Air Turbine Power Train - A distributed heating system for a power train of a ram air turbine, which ram air turbine has a stowed position and a deployed position, has at least one electrical resistance heater element, with each electrical resistance heater element located proximate at least one respective lubrication surface for the power train; and an electrical controller for coupling electrical power to each electrical resistance heater element when the ram air turbine is in the stowed position and ambient temperature falls below a desired level.
|AEROFOIL COOLING ARRANGEMENT - An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall, a suction wall and a web that extends therebetween. One of the walls comprises an inner leaf and an outer leaf which defines a cavity, the other wall defines a first outlet, the aerofoil defines at least one first passage extending from the cavity through the web and to the outlet. Coolant in the cavity on one side wall of the aerofoil is thereby routed across the web to be used to cool the other wall by convention and formation of a coolant film.
|WIND TURBINE BLADE AND RELATED METHOD OF MANUFACTURE - A blade for a rotor of a wind turbine, said blade comprising a blade body element provided with a carrier surface to accommodate a heating element, an electrically conductive, elongated and substantially planar heating element disposed upon the carrier surface to extend longitudinally substantially along at least the leading edge of the blade preferably at least about 50% of the length of the blade, more preferably at least about 60% and most preferably at least about 70% respectively, an electrical power supplying conductor element located at one end of the heating element, the conductor element substantially extending over the width of the heating element on both sides thereof and electrically coupling thereto, and a joint structure comprising at least one electrically conductive joint element and substantially covering, on both sides of the heating element, the portions of the electrical conductor element that extend over the width of the heating element, wherein said blade preferably contains an instance of said electrical conductor element and joint structure substantially at both ends of the heating element. A corresponding method of manufacture is presented.
|CLEAT FOR OPEN-WORK BLADE FOOT - The principal aim of the invention is a cleat (
|PROPELLER COMPRISING A COUNTERWEIGHT SYSTEM PROVIDED WITH AN AIR DISCHARGE CHANNEL - The main aim of the invention is a propeller (
|DAMPER FOR A TURBINE ROTOR ASSEMBLY - A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate with a forward face and an aft face, and an aft plate with a forward face and an aft face. The aft face of the forward plate may be connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be greater than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a pocket on the forward face of the forward plate.
|THE SURFACE STRUCTURE OF WINDMILL ROTORS FOR SPECIAL CIRCUMSTANCES - The present invention relates to an improvement of windmill rotors—more specifically rotors that have been designed to be used in cold and wet climate, such as northern sea areas. This can be achieved by incorporating an electrically conducting layer on or in the surface of a windmill blade. The same coating can also be used to achieve a stealth property.
|WIND TURBINE GENERATOR WITH LOCALIZED AIR GAP CONTROL AND A WIND TURBINE HAVING SUCH A GENERATOR - A wind turbine component (
|ELECTRICAL POWER TRANSFER SYSTEM FOR PROPELLER SYSTEM - A propeller system for an aircraft includes a propeller assembly rotatable about a central axis and a reduction gearbox operably connected to the propeller assembly via a propeller shaft. An electrical power transfer system is positioned such that the gearbox is located axially between the electrical power transfer system and the propeller assembly. The electrical power transfer system includes a slip ring assembly secured to an oil transfer tube extending to the propeller assembly and a brush block interactive with the slip ring assembly to transfer electrical power to a plurality of lead wires extending from the slip ring assembly to the propeller assembly. The brush block is positioned such that brush block tips of the brush block extend toward the slip ring assembly in a substantially radial direction relative to the central axis of the propeller assembly.
|WIND TURBINE ROTOR BLADE DE-ICING ARRANGEMENT - A de-icing arrangement of a wind turbine rotor blade is provided. The de-icing arrangement includes an electrically conductive mat, an electrically conductive band for distributing an electric current along a first edge of the mat, and a current supply connector for connecting the band to a current supply, wherein at least the electrically conductive mat is embedded in the body of the rotor blade. A wind turbine including a number of rotor blades including such a de-icing arrangement according, and a current supply for connecting to the de-icing arrangements of a rotor blades. A method of incorporating a de-icing arrangement in a wind turbine rotor blade is also provided.
|METHODS OF MANUFACTURING TURBOMACHINES BLADES WITH SHAPED CHANNELS BY ADDITIVE MANUFACTURING, TURBOMACHINE BLADES AND TURBOMACHINES - A hollow blade for a turbomachine comprises an airfoil portion; the airfoil portion extends longitudinally for a length; the airfoil portion is defined laterally by an external surface; the airfoil portion has at least one internal cavity extending along said length and defined laterally by an internal surface; the airfoil portion has a set of channels extending from the external surface to the internal surface; the openings of said channels on said external surface are aligned along a curved line that reflects an isobar on said external surface.
|NACELLE CONSTRUCTION FOR A WIND TURBINE - A heli-hoist pad (
|PLATE FOR DIRECTING FLOW AND FILM COOLING OF COMPONENTS - An assembly includes a gas turbine engine component and a plate. The plate is spaced from a surface of the component and generally conforms to the shape of the surface. The plate and component form a passageway that allows for passage of a secondary gas flow between the component and the plate.
|GAS TURBINE ENGINE - The gas turbine engine (S
|Wind Power Generation System - Provided is a wind power generation system that is less likely to change its cooling performance depending on the wind direction. In order to solve the above problem, the wind power generation system of the invention includes blades adapted to rotate upon receiving wind, a generator for performing a power generating operation by rotating a rotor together with rotation of the blades, a nacelle for supporting the blades via a main shaft, a tower for rotatably supporting the nacelle, a power conditioning system or transformer accommodated in the tower, and a plurality of radiators disposed on an outer peripheral side of the tower for cooling the power conditioning system or the transformer. The radiators positioned substantially at the same height are arranged at substantially equal intervals in a circumferential direction of the tower.
|IMPELLER INTERNAL THERMAL COOLING HOLES - An impeller may include a hub section, a plurality of blades, and a shroud. The hub section may be mounted on a rotatable shaft. The hub section may define a central opening for the rotatable shaft to extend therethrough and may define a plurality of holes disposed in a circular manner about the central opening. The plurality of blades may be connected to or integral with the hub section. The shroud may be connected to or integral with the hub section and the plurality of blades. The plurality of holes may be either through holes or partially drilled holes. A bottom of some or all of the partially drilled holes may be flat, conical, or rounded. Some or all of the partially drilled holes may have one or more bleed holes that may permit quenching material to flow therethrough and prevent the quenching material from stagnating therein.
|COMPRESSOR - A compressor that includes a frame, a rotor assembly, and a heat sink assembly. The rotor assembly includes a shaft to which an impeller, a bearing assembly and a rotor core are secured. The heat sink assembly is then secured to the bearing assembly and to the frame.
|COMPRESSOR - A compressor that includes a frame, a rotor assembly, and a heat sink assembly. The rotor assembly includes a bearing assembly to which the heat sink assembly is secured. The compressor is configured such that, during use, air is drawn through the interior of the frame. The heat sink assembly then extends radially from the bearing assembly into the air path through the frame such that the air flows over the heat sink assembly.
|COMPRESSOR ROTOR HEAT SHIELD - A heat shield for a rotor in a turbine engine is provided. The heat shield includes a main body having a first pair of recesses. The first pair of recesses is adapted to fit around a portion of one or more rotor blades or between two axially adjacent rotor wheels. The first pair of recesses limits axial and radial movement of the heat shield by interaction with the rotor blades or by interaction with the two axially adjacent rotor wheels. The first pair of recesses engage axially adjacent rotor blades or the axially adjacent rotor wheels. The heat shield protects the rotor from hot gas.
|REPAIR TOOL FOR A TURBINE ROTOR WHEEL, AND A TURBINE ROTOR WHEEL - A process of preparing a turbine rotor wheel, a repair tool for machining a turbine rotor wheel, and a turbine rotor wheel are disclosed. The process includes providing the turbine rotor wheel, the turbine rotor wheel having a dovetail slot, a cooling slot, and a dovetail acute corner formed by the dovetail slot and the cooling slot and removing a stress region from the dovetail acute corner. The repair tool permits removal of strained material while also reducing the operating stress of the feature. The turbine rotor wheel includes a machined portion resulting in lower stress for the turbine rotor wheel.
|WIND TURBINE ROTOR BLADE HAVING AN ELECTRICAL HEATING DEVICE AND A PLURALITY OF LIGHTNING CONDUCTORS - A wind turbine rotor blade includes: a rotor blade root; a rotor blade tip; an electrical heating device; a first lightning receptor disposed in the region of the rotor blade tip; precisely two lightning conductors leading from the lightning receptor to the rotor blade root; a second lightning receptor arranged at a distance to the rotor blade tip and connected to one of the lightning conductors; and, each one of the two lightning conductors being electrically conductively connected to the electrical heating device at a multiplicity of points between the rotor blade root and the rotor blade tip so as to cause equipotential bonding between the two lightning conductors via the electrical heating device in response to a lightning strike to the rotor blade.
|COOLING SYSTEM OF A WIND TURBINE - A cooling system of a wind turbine is provided which includes a generator (
|CONTROL DEVICE FOR THE PITCH OF BLADES, AND PROPELLER - The invention relates to a control device (
|EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger (
|MANUFACTURING METHOD FOR STRUT SHIELD COLLAR OF GAS TURBINE EXHAUST DIFFUSER - A method for casting a collar (
|TURBOCHARGER HAVING A CONNECTOR FOR CONNECTING AN IMPELLER TO A SHAFT - A connector for connecting an impeller to a shaft is provided. The impeller has a shaft-side hub extension with a central recess. The impeller is formed of a material having a greater coefficient of thermal expansion than the material of the shaft. The connector is inserted into the recess to frictionally connect an outwardly facing surface of the connector with a radially inner surface of the hub extension. The connector has a threaded portion carrying a thread which screws onto a corresponding threaded portion of the shaft, such that the connector provides a rotationally fixed connection between the impeller and the shaft. The connector is formed of a material having a coefficient of thermal expansion which is greater than the coefficient of thermal expansion of the material of the shaft.
|Compound Cooling Flow Turbulator for Turbine Component - Multi-scale turbulation features, including first turbulators (
|BRUSH DESIGN FOR PROPELLER DEICING SYSTEM - A brush configured to engage a rotating component to transfer an electrical signal and/or power is provided including a body formed from a core material. A coating material is disposed over a portion of the body configured to contact the rotating component. A contact area between the brush and the rotating component increases as the coating material wears.
|AIRFOIL WITH IMPROVED COOLING - The present invention relates to an airfoil for a gas turbine, including an improved turbulator arrangement formed on an inner cooling channel of the airfoil. According to preferred embodiments of the invention, in order to ensure a constant angle of the cooling flow inside the channel relative to each turbulator, the angle formed between the turbulator and the vertical axis is advantageously adapted, in the curved area, for every single turbulator. Furthermore, the same principle may be applied to all the cooling channels present within the airfoil.
|GAS PATH COMPONENTS OF GAS TURBINE ENGINES AND METHODS FOR COOLING THE SAME USING POROUS MEDIUM COOLING SYSTEMS - Gas path components of gas turbine engines and methods for cooling the same using porous medium cooling systems are provided. The gas path component comprises a wall at least partially defining a cooling plenum and a porous medium cooling system. The wall includes a wall surface comprising a gas path surface and an opposing wall surface proximate the cooling plenum. The porous medium cooling system is disposed between the cooling plenum and the opposing wall surface. The porous medium cooling system comprises a perforated baffle and a porous material layer disposed between and adjacent the perforated baffle and the opposing wall surface. The wall includes a plurality of openings in fluid communication with the cooling plenum via the porous medium cooling system.
|AIRFOIL TIP POCKET WITH AUGMENTATION FEATURES - A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge. The airfoil extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.
|FASTBACK VORTICOR PIN - A structure for disrupting the flow of a fluid, the structure comprising: (a) a first lateral wall and a second lateral wall spaced apart from one another, yet joined, by a floor and a ceiling; and, (b) a vorticor pin extending incompletely between the first lateral wall and the second lateral wall in a direction parallel to an X-axis, the vorticor pin concurrently rising above and extending away from the floor to a height, in a direction parallel to a Y-axis, to provide a gap between the vorticor pin and the ceiling, the vorticor pin comprising: (i) a front surface extending incompletely between the first lateral wall and the second lateral wall, the front surface extending above the floor and having an arcuate portion that is transverse with respect to a Z-axis, which is perpendicular to the X-axis and the Y-axis, and (ii) a rear surface extending between the first lateral wall and the second lateral wall, the rear surface extending between the front surface and the floor, the rear surface having an inclining section that tapers in height, taken parallel to the Y-axis, in a direction parallel to the Z-axis.
|ANGLED IMPINGEMENT INSERT - An engine component with particulate mitigation features is provided. The engine component comprises an internal engine component surface having a cooling flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.
|GAS TURBINE ENGINE AIRFOIL WITH LARGE THICKNESS PROPERTIES - An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.
|BLADE FOR A TURBOMACHINE - A blade for a turbomachine includes an airfoil portion and a root portion, the airfoil portion has an outer wall having a pressure side, suction side, leading edge and trailing edge, the outer wall extending between the leading edge and a trailing edge of the airfoil portion, a first cavity between the pressure side of the outer wall and a first inner wall, a second cavity between the suction side of the outer wall and a second inner wall. The first and second inner wall form a receiving cavity therebetween. The receiving cavity is fluidly connected to both the first and second cavity. The cooling fluid in the first and second cavity is conducted in a direction from the trailing edge to the leading edge and the cooling fluid in the receiving cavity is conducted in a direction from the leading edge to the trailing edge.
|ROTOR AND GAS TURBINE ENGINE INCLUDING SAME - A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk. One or more cooling features may be incorporated radially inboard from the rotor disk rim that operate to induce vortices adjacent to the disk rim and/or disk web. The vortices increase the local velocity in the secondary cooling air flow path and therefore increase the heat transfer rate from the rotor to the secondary cooling air flow path.
|GAS TURBINE ENGINE AIRFOIL PLATFORM COOLING PASSAGE AND CORE - A gas turbine engine blade includes a platform arranged between a root and an airfoil. A cooling passage extends from the root through the platform to the airfoil. The cooling passage includes an inlet that splits into first and second branches that rejoin one another in a platform passage arranged in the platform. An airfoil passage extends from the platform passage and is arranged in the platform.
|GAS TURBINE ENGINE COMPONENT EXTERNAL SURFACE MICRO-CHANNEL COOLING - A gas turbine engine component that includes a structure having a surface which includes multiple cooling channels having a width of 20-30 μm and a depth of 25-50 μm.
|COMPONENT CASTING - A method includes forming a mould, the mould having at least one mould portion defining the shape of an element to be removed from the component in a subsequent manufacturing step and having a reduced cross-sectional area. The at least one mould portion includes at least one recess which further reduces the cross sectional area of the cavity and increases the surface area of the at least one mould portion or the at least one mould portion includes a plurality of projections which increase the surface area of the least one mould portion thereby increasing radiative heat loss from said at least one mould portion during said process. A mould for use in this method and a turbine blade formed using this method, are also provided
|GAS TURBINE ENGINE COMPONENT COOLING WITH INTERLEAVED FACING TRIP STRIPS - A gas turbine engine component includes first and second walls spaced apart from one another to provide a cooling passage. First and second trip strips are respectively provided on the first and second walls and arranged to face one another. The first and second trip strips are arranged in an interleaved fashion with respect to one another in a direction.
|INTERLOCKING ROTOR ASSEMBLY WITH THERMAL SHIELD - A rotor assembly includes a first rotor, a second rotor mounted on the first rotor and co-rotatable there with, and a thermal shield interlocked with the second rotor for co-rotation there with.
|GAS TURBINE ENGINE TURBINE IMPELLER PRESSURIZATION - A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.
|Injecting Gas Into A Vessel
|GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT - An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body and a cooling circuit disposed inside the airfoil body and including a leading edge cavity with a first portion extending from a radially inner wall to a radially outer wall of the airfoil body and a second portion that extends from a leading edge inner wall to a trailing edge inner wall of the airfoil body. The cooling circuit is configured to communicate cooling airflow through the first portion and the second portion prior to exiting the leading edge cavity into a second cavity of the cooling circuit.
|TURBULATING COOLING STRUCTURES - In a first embodiment, a hollow gas turbine engine workpiece comprises first and second walls formed via additive manufacturing, and a cooling passage defined between the first and second walls by a surface of the first and second walls having arithmetic average surface roughness of at least 100 μin (0.0025 mm). In a second embodiment, a method of manufacture of a gas turbine engine component comprises depositing successive layers of pulverant material via additive manufacturing to form first and second walls defining a cooling passage therebetween, and loading a grain size of the pulverant material to produce lattice convective cooling design networks of various size and proportions with each having a range of relative roughness values, 0.10<ε/Dh<0.50 to achieve optimal thermal cooling performance along the cooling passage.
|GAS TURBINE ENGINE BLADE WITH VARIABLE DENSITY AND WIDE CHORD TIP - A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.
|LOW PRESSURE LOSS COOLED BLADE - A rotor blade comprises a root section, an airfoil section, a leading edge cooling cavity, an intermediate cooling cavity, and a trailing edge cooling cavity. The leading edge, intermediate, and trailing edge cooling cavities each extend spanwise through the airfoil section from a coolant inlet passage in the root section, and each terminate proximate the airfoil tip.
|MULTI-LOBED COOLING HOLE - A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first surface, an outlet located at the second surface, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and having a first downstream end adjacent the outlet and spaced from the inlet by a first distance, a second lobe diverging longitudinally from the metering section and having a second downstream end adjacent the outlet and spaced from the inlet by a second distance different from the first, and a transition region positioned between the lobes, the transition region having a third downstream end adjacent the outlet.
|GAS TURBINE ENGINE AXIAL COMPRESSOR REAR HUB - A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub.
|GAS TURBINE ENGINE AIRFOIL GEOMETRIES AND CORES FOR MANUFACTURING PROCESS - An airfoil for a gas turbine engine includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness. The second thickness is less than 0.060 inch (1.52 mm).
|GAS TURBINE ENGINE WITH AXIAL COMPRESSOR HAVING IMPROVED AIR SEALING - A gas turbine engine including an axial high pressure compressor having expansion slots in the outer rim of the rotor section. The expansion slots may be positioned between blades of a rotor segment. The fore end of the slots may have an axial seal which is coupled to the inner surface of the outer rim in the first rotor segment, and may comprise a fin configuration. The axial seal may be integral to the inner surface of the outer rim. The compressor may comprise a plurality of expansion slots and axial seals, including in a plurality of rotor segments.
|GAS TURBINE ENGINE ROTOR ARRANGEMENT - A gas turbine engine rotor arrangement comprising at least one blade and a disc is disclosed. The blade extends radially outwards from the disc and is secured thereto by cooperating shank of the blade and recess of the disc. The shank comprises a bottom surface facing a base surface of the recess, the bottom surface having axially extending peripheral edges. The bottom surface is shaped so that when the engine rotor arrangement is in use, liquid in a cavity between the bottom surface and base surface, acted upon by an unbalanced force in the radially outward direction, is guided by the bottom surface to flow between and away from the axial edges.
|CASTING OF ENGINE PARTS - Investment casting of engine part defined during casting by pair of core members having respective opposed faces, major portions of opposed faces being spaced apart by first distance corresponding to predetermined thickness of a portion of resulting cast wall, face of each opposing core member which face each other being provided with respective open recesses, each protrusion on first core member facing a respective one of second core member, wherein during part of casting procedure first and second core members are maintained positioned relative to each other so major portions of the opposed faces of first and second core members assume mutual spacing equaling corresponding predetermined thickness of portion of resulting cast wall; and at least head portion of protrusion on first core member is located within respective open recess in second core member, such that respective protrusion and respective open recess define respective minor portion of resulting cast wall.
|METHOD OF BLADE TIP REPAIR - A method for repairing a blade for use in a gas turbine engine, the method comprising removing a distal tip of an airfoil included in the blade to remove damaged portions of the airfoil and to expose previously internal cooling passages. The method further comprising positioning a tip cap in the place of the removed distal tip to cover the internal cooling passages, and welding the tip cap to the airfoil by applying a directed energy beam onto the tip cap and the airfoil at a joint between the tip cap and the airfoil.
|LIQUID-CAPTURING SHAFT - There is provided a liquid-capturing shaft (
|GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE TURBULATOR PEDESTAL - A gas turbine engine component includes a structure that provides a cooling passage. The structure has a turbulator with a pedestal joining opposing first and second surfaces. The turbulator includes first and second legs spaced apart from one another and adjoining the pedestal. The first leg adjoins the second surface, and the second leg adjoins the first surface.
|TURBOMACHINE ROTORS WITH THERMAL REGULATION - A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body, a bore defined in a radially inward portion of the disk body and configured to be radially adjacent to a shaft, and a thermal regulation aperture defined in the disk body, radially inward of the rim, for allowing flow to pass axially through the disk body when disposed in a stage of a turbomachine, and a thermal regulation aperture defined in the disk body for allowing flow to pass through the disk body when disposed in a stage of a turbomachine.
|HIGH PRESSURE TURBINE BLADE COOLING HOLE DISTRIBUTION - A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one set of holes selected from the group consisting of a first set, a second set, a third set, a fourth set, a fifth set and a sixth set, wherein the first, second, third, fourth, fifth and sixth sets of holes respectively include the holes numbered A
|GAS TURBINE ENGINE BLADE SLOT HEAT SHIELD - A gas turbine engine rotor assembly includes a rotor disk with a slot. A rotor blade has a root supported within the slot. A heat shield is arranged in a cavity in the slot between the root and the rotor disk. An axial retention feature is configured to axially maintain the heat shield within the slot.
|GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE CONFIGURATION - A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another. The first pass includes first and second portions nested relative to one another and overlapping in a thickness direction. The first and second portions are adjacent to one another by sharing a common wall. The first portion is provided on the suction side. The second portion is provided on the pressure side.
|DUAL WALL COMPONENTS FOR GAS TURBINE ENGINES - A dual wall component for use in a gas turbine engine and a method for making the same are disclosed herein. The dual wall component includes an inner support wall and an outer shield wall that extends around the inner support wall to act as a heat shield for the inner support wall.
|FAN ROTOR WITH COOLING HOLES - A disc for a fan rotor (with a pilot to connect to a rotating shaft, a hub and a plurality of blades) includes a flat circular portion connecting to the pilot at an inner edge and to the hub at an outer edge; a plurality of first circular cooling holes of a first diameter located around the inner edge of the disc; and a plurality of second circular cooling holes of a second diameter located around the outer edge of the disc, wherein the second diameter is larger than the first diameter.
|VIBRATION DAMPERS FOR TURBINE BLADES - A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.
|GAS TURBINE BLADE CONFIGURATION - A gas turbine engine blade (
|GAS TURBINE ENGINE TURBINE BLADE TIP COOLING - An airfoil for a gas turbine engine includes pressure and suction walls that are spaced apart from one another and joined at leading and trailing edges to provide an airfoil that has an exterior surface that extends in a radial direction to a tip. A film cooling hole is provided in the tip and extends at an angle relative to the radial direction. The film cooling hole includes a diffuser.
|COOLING ARRANGEMENT FOR GAS TURBINE BLADE PLATFORM - A gas turbine engine blade (
|HYBRID POWER ROTARY WING AIRCRAFT - A rotary wing aircraft includes a main rotor; an electric motor for rotating the main rotor; an electric generator for supplying electric power to the electric motor; an engine for driving the generator; and battery storage for providing battery power. The aircraft further includes a flight control system for controlling the engine to run at idle and causing the electric motor to receive the battery power to rotate the main rotor during takeoff; for controlling the engine to increase speed above idle and operate the generator to recharge the battery storage during flight; and for controlling the engine to return to idle and controlling the electric motor to receive the battery power for landing.
|PARTIALLY COATED BLADE - A partially coated blade for a gas turbine engine, including a fillet surface surrounding the airfoil section and connecting it to the platform section. A radially outermost portion of the pressure side and leading edge is covered by a thermal barrier coating. This portion extends radially from a first limit to the blade tip. The first limit is located at a radial distance from the platform of at most 21% of the maximum span. The fillet surface is free or substantially free of the thermal barrier coating. In another embodiment, a second portion of the pressure side and of the leading edge is free or substantially free of the thermal barrier coating, extending radially from the platform section to a second limit located a radial distance from the platform section corresponding to at least 5% of the maximum span. A method of applying a thermal barrier coating is also discussed.
|COOLING FOR TURBINE BLADE PLATFORM-AEROFOIL JOINTS - The invention concerns a turbine blade for a gas turbine having a platform part and an aerofoil part. The platform part includes a platform surface arranged to be attached to a corresponding aerofoil surface of the aerofoil part. The turbine blade further includes a cooling duct for cooling the platform and aerofoil surfaces, the cooling duct having at least one cavity in the platform surface and at least one cavity in the corresponding aerofoil surface, and the platform and aerofoil surface cavities are aligned such that when the platform surface and the aerofoil surface are touching, the cooling duct remains open. This provides a reliable cooling of both the platform and aerofoil surfaces.
|DAMPING INLAY FOR TURBINE BLADES - The invention concerns a turbine blade comprising a surface, a recess within the surface, and a damping inlay within the recess. The damping inlay comprises a chamber with a damping material, for example particles. The damping inlay should substantially maintain the aerodynamic profile of the blade to enable normal operation. A further embodiment of the invention describes the method of manufacture of a turbine blade with a damping inlay. The method comprises the steps of manufacturing a turbine blade having a surface and a recess in the surface, and providing one or more damping inlays within the recess such that the damping inlay substantially maintains the aerodynamic profile of the blade, the damping inlay comprising a chamber and a damping material disposed within the chamber.
|SYSTEM AND METHOD FOR FORMING A COOLING HOLE IN AN AIRFOIL - A system for forming a cooling hole in an airfoil includes a liquid-jet guided laser. The liquid-jet guided laser generates a laser beam confined within a fluid column. The fluid column/laser beam is directed at an outer surface of the airfoil. The system also includes a purge medium supply that is fluidly coupled to an aperture of the airfoil. The purge medium supply provides a purge medium into an inner cavity of the airfoil. The purge medium flow is oriented to flow in a flow direction that is substantially parallel to an inner surface of the cavity. A cooling hole is formed in the airfoil and extends through the outer surface and penetrates the inner surface of the cavity. A centerline of the cooling hole forms an acute angle with respect to the purge medium flow direction. The system described herein provides a method for manufacturing an airfoil.
|LEADING EDGE COOLING CHANNEL FOR AIRFOIL - Methods and systems of cooling airfoils are provided. The present invention provides systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.
|COMPOSITE BLADES FOR GAS TURBINE ENGINES - A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.
|TURBINE ENGINE ROTOR SHAFT COMPRISING AN IMPROVED HEAT EXCHANGE SURFACE - A turbine engine rotor shaft includes at least one portion having an outer periphery having a determined diameter forming a free surface for heat exchange with the environment of said rotor. The outer periphery comprises includes a plurality of irregularities which are designed to provide a heat exchange surface of the shaft of the rotor which is greater than a surface of the periphery of a cylinder having the same determined average diameter.
|DRILL TO FLOW MINI CORE
|ROTOR HEAT SHIELD AND METHOD FOR SECURING THE SAME INTO A ROTOR ASSEMBLY - The present disclosure generally relates to a rotor assembly, and in particular relates to an improved rotor heat shield which provides an innovative configuration for securing the same to the rotor assembly. The rotor heat shield element is secured to the rotor assembly in correspondence of the groove in which it is inserted. Embodiments of the present disclosure can allow the removal of current fixation features on heat shields and blades. Furthermore, since the heat shield is no longer connected to a blade but directly to the rotor assembly, there is more freedom in selecting the number of heat shield elements to be provided to form the circumferential heat shield.
|DIFFUSED PLATFORM COOLING HOLES
|ROTATING BLADE FOR A GAS TURBINE
|METHOD OF FORMING COOLING HOLES
|TURBINE BLADE HAVING HEAT SINKS THAT HAVE THE SHAPE OF AN AEROFOIL PROFILE
|MIXING PLENUM FOR SPOKED ROTORS - A gas turbine engine may comprise a first rotor with a primary flowpath along an outer diameter of the first rotor. A secondary flowpath may be radially inward from the primary flowpath. The secondary flowpath may pass through an opening through the first rotor. A blade may be disposed on a distal end of the first rotor. The blade may extend into the primary flowpath. A bleed tube may be in a wall of the primary flowpath and forward of the blade. The bleed tube may extend radially inward from the primary flowpath. The bleed tube may fluidly connect to the opening through the first rotor. A plenum may be aft of the blade and radially inward from the primary flowpath. The plenum may be fluidly connected to the opening through the first rotor. A second rotor may be aft of the plenum.
|INTERIOR COOLING CHANNELS IN TURBINE BLADES - A blade for a turbine of a gas turbine engine that includes an airfoil, the airfoil having a leading edge, a trailing edge, an outboard tip, and an inboard end. The airfoil may further include a cooling configuration that includes a plurality of cooling channels for receiving and directing a coolant. The cooling channels may include a linear cooling channel and a curved cooling channel. The blade may also include a contoured shape defined by the airfoil between the inboard end and the outboard tip, with the contoured shape being configured so to include a target area inaccessible to a linear reference line extending radially from a position at the inboard end of the airfoil. The curved cooling channels may be configured to extend between an upstream end and a downstream end so to intersect the target area therebetween.
|HOT GAS PATH COMPONENT AND METHODS OF MANUFACTURE - Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.
|COOLING CONFIGURATIONS FOR TURBINE BLADES - A blade in a turbine of a gas turbine engine that includes: an outer surface bending along an edge at an angle greater than about 120° so to define a first outer surface to a first side of the edge and a second outer surface to a second side of the edge; an internal flow passage; and a forked cooling channel configured so to fluidly connect the internal flow passage to a first film cooling port and a second film cooling port formed to each side of the edge.
|ENGINE COMPONENT - An engine component includes a hot surface in thermal communication with a hot combustion gas flow, and a cooling surface, opposite the hot surface, along which a cooling fluid flows. At least one vortex generator is provided on the cooling surface, and can induce a vortex in the cooling fluid in response to contact with the flowing cooling fluid.
|COOLING HAVING TAILORED FLOW RESISTANCE
|ROTOR FOR A THERMAL TURBOMACHINE
|REVERSIBLE BLADE ROTOR SEAL WITH PROTRUSIONS - A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a first condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.
|TURBINE ROTOR BLADE WITH COUPON HAVING CORRUGATED SURFACE(S)
|BLADE WITH PARALLEL CORRUGATED SURFACES ON INNER AND OUTER SURFACES
|GAS TURBINE ENGINES WITH IMPROVED AIRFOIL DUST REMOVAL
|BUSBARS IN A STACKING ARRANGEMENT
Patent applications in class WITH HEATING, COOLING OR THERMAL INSULATION MEANS
Patent applications in all subclasses WITH HEATING, COOLING OR THERMAL INSULATION MEANS