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US20130302150 |
OFF-SHORE WIND TURBINE WITH A THERMAL CONDITIONING SYSTEM
A thermal conditioning system for an off-shore wind turbine is provided. The thermal conditioning system comprises an insulating structure that reduces the thermal losses by convection of a... |
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US20140037436 |
TURBINE HOUSING FOR TURBOCHARGER
A turbine housing (3) applied to a turbine (2) incorporated in a turbocharger (1) includes a main body (10) in which a wheel housing chamber (13) housing a turbine wheel (4) and an exhaust passage... |
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US20140216056 |
HEAT EXCHANGE MODULE FOR A TURBINE ENGINE
A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a... |
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US20140112767 |
COOLING-AIR GUIDANCE IN A HOUSING STRUCTURE OF A TURBOMACHINE
A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel (14) in which guide vanes and rotor vanes are arranged. The housing... |
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US20130051994 |
RETRACTABLE GAS TURBINE INLET COILS
A gas turbine inlet heat exchange coil assembly includes a gas turbine inlet housing formed to include an inlet and an outlet and a flow path therebetween. A plurality of adjacent coils are... |
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US20130101386 |
DUAL-FLOW STEAM TURBINE WITH STEAM COOLING
A dual flow steam turbine includes coolant passageways which extract coolant steam from the main steam flow paths at locations downstream from the inlet. The coolant passageways conduct the... |
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US20100251716 |
COOLED EXHAUST HOOD PLATES FOR REDUCED EXHAUST LOSS
Cooled exhaust hood plates are provided in areas of high velocity steam flow within an exhaust steam flow of a steam turbine. Coolant is directed within double walled exhaust hood plates to cool... |
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US20140147259 |
GAS TURBINE ENGINE TURBINE NOZZLE IMPINGEMENT COVER
An impingement cover (460) for fusing to a gas turbine engine turbine nozzle (451) with a nozzle rail (455) includes a body and a plurality of tabs for forming a first fuse with the nozzle rail... |
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US20130343882 |
PUMP
An impeller radial pump includes a pump chamber with a central suction and with a pump chamber outlet, wherein an impeller is provided in the pump chamber. Radially outside of the impeller, a... |
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US20050109016 |
Turbine tip clearance control system
An apparatus and method for selectively cooling a gas turbine engine component for the purpose of controlling blade tip clearance during transient conditions, wherein cooling air is admitted... |
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US20120063891 |
COOLED COMPONENT FOR A GAS TURBINE
A cooled component for a gas turbine is disclosed, which by an outer side of a wall delimits hot gas passage of the gas turbine and on an inner side has a device for impingement cooling. The... |
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US20150033696 |
TURBINE CASING FALSE FLANGE FLOW DIVERTER
A system includes a turbine casing assembly that includes an outer shell and an inner shell positioned substantially concentrically within the outer shell. The inner shell includes an inner... |
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US20150110611 |
AIRFOIL COOLING CIRCUIT AND CORRESPONDING AIRFOIL
An airfoil cooling circuit for a gas turbine engine having at least one internal cavity with a lobed cross-sectional shape. |
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US20140093361 |
AIRFOIL WITH VARIABLE TRIP STRIP HEIGHT
An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A... |
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US20080273968 |
System for regulating a cooling fluid within a turbomachine
A system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid... |
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US20130156554 |
BLOWER MOTOR COOLING TUBE NOISE SUPPRESSOR FOR TICKING/CHIRPING
A blower unit for a vehicle including a fan, a motor, a scroll case, a cooling chamber, a first partition, and a second partition. The fan is configured to generate airflow. The motor is connected... |
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US20150175269 |
CASING FOR A PROPULSION UNIT
An aircraft propulsion unit comprising an engine and a nacelle including an axisymmetric casing (16) delimiting an air flow path, wherein this casing has at least two openings closed by removable... |
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US20120251309 |
CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY AN AXIAL CONTACT
Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to... |
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US20080159852 |
HEAT TRANSFER SYSTEM FOR TURBINE ENGINE USING HEAT PIPES
A heat transfer system is provided for a turbine engine of the type including an annular inlet cowling. The heat transfer system includes at least one heat pipe disposed in contact with an... |
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US20130202421 |
Passive Liquid Cooling System for Inverters Utilized for Wind Turbine Applications
A wind turbine with a thermal siphoning system is disclosed. The wind turbine comprises a tower of a wind turbine, the tower having a top and a base, and a thermal siphoning system for cooling... |
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US20130209217 |
PLATFORM SEGMENT FOR SUPPORTING A NOZZLE GUIDE VANE FOR A GAS TURBINE AND NOZZLE GUIDE VANE ARRANGEMENT FOR A GAS TURBINE
A platform segment for supporting a nozzle guide vane for a gas turbine is provided. The platform segment includes a gas passage surface arranged to be in contact with a streaming gas exhausted... |
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US20140000285 |
GAS TURBINE ENGINE TURBINE VANE PLATFORM CORE
A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure... |
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US20150176412 |
ROTOR BLADE AND GUIDE VANE AIRFOIL FOR A GAS TURBINE ENGINE
The invention refers to a rotor blade or guide vane airfoil for a gas turbine engine having a longitudinal axis and a source of cooling fluid. The airfoil has a pressure wall, a suction wall, a... |
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US20090252603 |
AIRFOIL FOR NOZZLE AND A METHOD OF FORMING THE MACHINED CONTOURED PASSAGE THEREIN
A nozzle in which an airfoil includes a pressure surface and a suction surface that join at substantially opposing chordal ends of the airfoil to form a leading edge of the airfoil and a trailing... |
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US20110135455 |
OIL COOLER
An air-cooled oil cooler for the wall of an air flow passage of a gas turbine engine is provided, the oil cooler allowing improved heat exchange performance to be obtained. This is achieved by:... |
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US20110182723 |
TURBOMACHINE AIRCRAFT PROPELLER
The invention relates to an aircraft propeller (1) comprising a turbomachine (8) housed in a nacelle (10) and a cooler (14) capable of being traversed by a hot fluid, which is to be cooled by... |
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US20110150634 |
Integration of an Air-Liquid Heat Exchanger on an Engine
A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at... |
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US20080314047 |
COOLING SYSTEMS FOR USE ON AIRCRAFT
Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet.... |
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US20100119360 |
Heatable part of a pump housing
The description relates to a heatable pump housing part comprising a heat distribution sheet fixed on the housing part and a tubular heating element fixed on the heat distribution sheet. According... |
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US20140271129 |
Cast-in cooling features especially for turbine airfoils
A method is provided for making a mold for casting advanced turbine airfoils (e.g. gas turbine blade and vane castings) which can include complex internal and external air cooling features to... |
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US20090169359 |
HEAT EXCHANGER ARRANGEMENT FOR TURBINE ENGINE
A turbine engine cooling arrangement includes a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a... |
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US20100284824 |
Cooling an Electrically Controlled Turbocharger
An electrically controlled turbocharger has a motor mounted on a shaft in a motor housing between a turbine and compressor. Oil is sprayed onto the motor stator to cool the stator. An oil gallery... |
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US20080187435 |
TURBINE SHROUD COOLING SYSTEM
A method of cooling a shroud ring in a turbine section of gas turbine engine includes identifying a series of alternating high temperature regions and lower temperature regions of a... |
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US20100092280 |
Steam Cooled Direct Fired Coal Gas Turbine
A gas turbine includes a combustor configured to burn a hydrocarbon fuel input and provide a combustion product hot gas output to a turbine inlet having a turbine inlet temperature exceeding about... |
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US20150167494 |
WATER COOLED TURBINE HOUSING
A gas passage that is connected to an exhaust passage and a water passage that is connected to a water jacket are formed in a turbine housing. The water passage and the gas passage are arranged... |
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US20140079540 |
TURBINE STATOR AIRFOIL ASSEMBLIES AND METHODS FOR THEIR MANUFACTURE
In accordance with an exemplary embodiment, a method of manufacturing a stator airfoil assembly includes forming an interior wall of a stator airfoil using an additive manufacturing technique,... |
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US20130000321 |
GAS TURBINE INLET HEATING SYSTEM
A gas turbine inlet heating system is disclosed. In one embodiment, the system includes: a compressor having: an inlet bellmouth adjacent to a set of inlet guide vanes (IGVs); and an outlet... |
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US20080222874 |
HOT GAS DUCT AND DUCT SPLITTER ARRANGEMENT
A hot gas duct, such as a combustion casing in a gas turbine engine, includes a duct splitter held within the hot gas duct in at least three, preferably four, locations spaced around a peripheral... |
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US20050089401 |
Turbine blade tip clearance system
A stage of gas turbine engine turbine blades (22) is surrounded by segments (26) that in turn, are suspended from a flexible casing (24). The inner surface of casing (24) is exposed to compressor... |
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US20140010640 |
REGEANT DOSING PUMP ASSEMBLY
A pump assembly having improved cooling for use in a selective catalytic reduction system is disclosed. The pump assembly comprises a pump housing having a body portion and a nozzle portion... |
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US20150219117 |
WALL RING FOR A FAN WITH HEATING ELEMENT
A wall ring for a fan, with a fan wheel, includes at least one heating element for heating the wall ring. The heating element includes an electrically conductive heating layer which is disposed on... |
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US20120023945 |
METHOD AND DEVICE FOR COOLING STEAM TURBINE GENERATING FACILITY
In a steam turbine 40 of opposed-current single-casing type in which a high pressure turbine part 31a and an intermediate-pressure turbine part 32a are housed in a single casing, a dummy ring 10... |
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US20090324397 |
Gas Turbine Engine With Insulated Cooling Circuit
A gas turbine engine is provided comprising a compressor with an insulated cooling circuit. The compressor comprises a compressor casing having a compression chamber and at least one stator and at... |
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US20120057967 |
GAS TURBINE ENGINE
A gas turbine engine includes a diffuser section supplying cooling fluid, a rotatable shaft, shaft cover structure disposed about the rotatable shaft, support structure, and a cooling fluid... |
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US20130149121 |
GAS TURBINE ENGINE WITH MULTIPLE COMPONENT EXHAUST DIFFUSER OPERATING IN CONJUNCTION WITH AN OUTER CASE AMBIENT EXTERNAL COOLING SYSTEM
An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment... |
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US20140271154 |
CASING FOR TURBINE ENGINE HAVING A COOLING UNIT
A turbine inner shell for a turbine engine includes one or more mounting grooves, each of which receives a fluid conduit. A temperature controlling fluid is circulated through fluid conduit to... |
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US20080075584 |
SET OF INSULATING SHEETS ON A CASING TO IMPROVE BLADE TIP CLEARANCE
The present invention relates to a turbine stator of a gas turbine engine comprising a turbine casing (9), a turbine shroud ring (13) and a shroud ring support (11) connecting the shroud ring (13)... |
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US20150210400 |
COMPONENT OF A NACELLE HAVING IMPROVED FROST PROTECTION
The present disclosure concerns a component of an aircraft nacelle formed from at least one composite structure and one heating element. The nacelle includes frost protector, and the composite... |
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US20150152736 |
TURBINE ENDWALL WITH MICRO-CIRCUIT COOLING
A micro-circuit cooling module for providing endwall cooling for a vane assembly in a gas turbine engine. The micro-circuit cooling module includes an outer perimeter rail, an upper plate and a... |
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US20140208768 |
COOLANT SUPPLY SYSTEM
A cooling system for a gas turbine engine (10) having a compressor (14), a combustor (16) and a turbine section arranged to receive combustion products from the combustor. The cooling system... |