Matches 1 - 50 out of 156 1 2 3 4 >


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US20140147258 HYDRAULIC BEARING FOR A STATIONARY GAS TURBINE  
A hydraulic bearing is provided for a stationary gas turbine that has an oil sump with an outflow for hydraulic oil, wherein the outflow has an outflow opening which is arranged in the oil sump...
US20140205427 DEVICE FOR DE-ICING A LEADING EDGE OF A TURBINE ENGINE BY SLANTING NOTCHES  
A device for de-icing a wall of a leading edge of a turbine engine, the leading edge being adapted to cooperate with a downstream guide vane subjected to a flow of fluid, the device including: a...
US20150044036 LUBE OIL SUPPLY SYSTEM AND METHOD OF REGULATING LUBE OIL TEMPERATURE  
A lube oil supply system of a turbine system and method of regulating lube oil temperatures. In one embodiment, the system includes a first valve positioned on a lube oil bypass conduit in fluid...
US20130287553 MANIFOLD FOR GEARED TURBOFAN ENGINE  
A geared architecture for a gas turbine engine includes a lubricant manifold for directing lubricant flow to the geared architecture. The manifold including annular channel and a bowl member...
US20140286762 TURBINE AIRFOIL ASSEMBLY  
A turbine airfoil assembly has an airfoil with an inner wall, an outer wall, a leading edge and a trailing edge. The airfoil has one or more chambers extending in a substantially chordwise...
US20140334921 PUMP FOR WATER COOLER  
A pump for a water cooler is positioned inside or outside an electronic device having heating parts in order to cool heat generated by the heating parts via a circulating refrigerant.
US20140069138 TURBO-COMPRESSOR-CONDENSER-EXPANDER  
An isothermal turbo-compressor-condenser-expander arrangement includes heat-transferring blades that are mounted on, or surround, individual conduits to promote air exchange and heat transfer. In...
US20140321995 RAM AIR FAN INLET SHROUD  
A ram air fan inlet shroud for a ram air fan assembly is provided. The ram air fan inlet shroud includes a shroud portion extending outwardly from a conical portion. The conical portion provides a...
US20140301834 TURBINE CYLINDER CAVITY HEATED RECIRCULATION SYSTEM  
A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is...
US20130302136 NON-AXISYMMETRIC RIM CAVITY FEATURES TO IMPROVE SEALING EFFICIENCIES  
Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second...
US20140205446 REGULATED OIL COOLING SYSTEM FOR A TURBINE ENGINE WITH DEICING OF THE NACELLE  
The invention relates to an oil cooling system of a turbine engine installed in an aircraft comprising a circuit suitable for circulating the oil between the engine and at least one external heat...
US20140060002 REGENERATIVE TURBINE FOR POWER GENERATION SYSTEM  
Disclosed is a power generation system and method. The system includes a combustor, and a turbine driven by products of the combustor. The turbine includes at least one disk supporting a plurality...
US20140064913 Impingement Plate for Damping and Cooling Shroud Assembly Inter Segment Seals  
An impingement plate is cooperable with a shroud assembly. The shroud assembly includes an outer shroud and plural inner shrouds with seals between the plural inner shrouds, respectively. The...
US20140255171 LUBRICATION SYSTEM FOR A TURBOPROPELLER  
A lubrication system for a turbopropeller, includes an oil feed device for at least one enclosure and one equipment, the equipment being connected to the feed device via a displacement pump, and a...
US20080044279 Adaptor Frame  
An adaptor frame comprising an isolated drain path formed in the adaptor frame at a first end of the adaptor frame is disclosed and claimed. An inboard wall is formed in the adaptor frame at the...
US20130101400 RAM AIR FAN INNER HOUSING  
A ram air fan inner housing for a ram air fan assembly comprises a center body housing, an end cup attached to the center body housing, and a perforated cone. The perforated cone is attached to...
US20140341723 GAS TURBINE VANE INSERT TO CONTROL PARTICULATE DEPOSITION  
A guide tube assembly in one embodiment includes a guide tube and a collection impingement feature. The guide tube includes an inlet and at least one first impingement opening. The inlet is...
US20140294560 Gas Turbine Shroud Assemblies  
Embodiments of the present disclosure include a gas turbine shroud assembly. The shroud assembly may include a shroud structure that defines a first cooling chamber and a second cooling chamber....
US20150000298 FUEL CONDITIONER, COMBUSTOR AND GAS TURBINE IMPROVEMENTS  
Advanced gas turbines and associated components, systems and methods are disclosed herein. A gas turbine configured in accordance with a particular embodiment includes a rotor operably coupled to...
US20130323035 METHOD AND SYSTEM TO PREVENT EQUIPMENT CORROSION FROM HUMID AMBIENT AIR ENTRY INTO AN OFFSHORE WIND TURBINE  
A method and system to prevent the equipment corrosion in an offshore wind turbine by minimizing the humid ambient air entry into the turbine. The method uses the fact that the ambient air entry...
US20150016961 COOLED TURBINE GUIDE VANE OR BLADE FOR A TURBOMACHINE  
A turbine airfoil for a turbomachine is provided. The airfoil includes a suction side wall and a pressure side wall bordering an airfoil cavity, which receives a cooling fluid for cooling the...
US20130064641 Air Ducting Shroud For Cooling An Air Compressor Pump And Motor  
A compressor assembly having an air ducting shroud that can direct a cooling air stream from a fan to components of the compressor assembly, such as a pump assembly. The pump assembly can have at...
US20090180866 SELF-MONITORING SYSTEM FOR EVALUATING AND CONTROLLING ADJUSTMENT REQUIREMENTS OF LEAKAGE RESTRICTING DEVICES IN ROTODYNAMIC PUMPS  
A self-monitoring adjustment system is provided for evaluating and effecting adjustment of the leakage restricting mechanism between the rotating and non-rotating elements of a rotodynamic pump to...
US20150198050 INTERNAL COOLING SYSTEM WITH CORRUGATED INSERT FORMING NEARWALL COOLING CHANNELS FOR AIRFOIL USABLE IN A GAS TURBINE ENGINE  
An airfoil for a gas turbine engine in which the airfoil includes an internal cooling system formed from one or more midchord cooling channels with a corrugated insert positioned therein and...
US20140241853 VACUUM PUMP  
A vacuum pump, in particular to a turbomolecular pump, has a pump inlet, a pump outlet and a pump space for a gas to be pumped arranged between the pump inlet and the pump outlet, and at least one...
US20150219116 TURBO-MOLECULAR PUMP  
A turbo-molecular pump comprises a rotor having rotor blades and a cylindrical section; stationary blades; a plurality of spacers; a stator arranged with a gap from the cylindrical section, a...
US20140219788 IMPINGEMENT COOLING OF TURBINE BLADES OR VANES  
The present invention relates to a turbine assembly with a basically hollow aerofoil, having at least a cavity with an inner wall and having at least an aperture providing access to the cavity,...
US20140321967 Gas Turbine Power Augmentation System  
The present application provides a power augmentation system for use with a gas turbine engine. The power augmentation system may include a compressor discharge manifold, an inlet bleed heat...
US20150118034 TRAILING EDGE COOLING USING ANGLED IMPINGEMENT ON SURFACE ENHANCED WITH CAST CHEVRON ARRANGEMENTS  
A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality...
US20140238336 POWER SYSTEM COMPRISING A TURBOCHARGER BYPASS PASSAGE  
A power system, comprising a turbocharger, an oil sump, a supply passage, a return passage, and a turbocharger bypass passage. The supply passage is positioned fluidly between the turbocharger and...
US20150198092 DUAL FUNCTION AIR DIVERTER AND VARIABLE AREA FAN NOZZLE  
A modulating fan air diverter and annular air-oil cooler for a gas turbine engine located in the inner fixed structure adjacent to the core cowl is provided. The fan air diverter modulates between...
US20120027576 TURBINE STAGE SHROUD SEGMENT  
A shroud segment for a turbine stage of a gas turbine engine forms an endwall for the working gas annulus of the stage. The segment also provides a close clearance to the tips of a row of turbine...
US20080112797 Transpiration clearance control turbine  
A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling...
US20140248166 PUMP  
A vacuum pump has at least one side passage pump stage which comprises a side passage bounded by at least one stator element and having a coolant circuit for cooling the vacuum pump with a...
US20140348636 AIRFOIL COOLING CIRCUIT  
An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an...
US20130251513 FABRICATED HEAT SHIELD  
A multi-pieces gas turbine engine combustor heat shield is fabricated from sheet metal. The fabrication involves: sheet metal forming a base sheet having opposed hot and cold facing sides,...
US20140086732 AIR BAFFLE SYSTEM IN A COOLING SYSTEM FOR ELECTRONICS  
A cooling apparatus of an array of fan cradles holding fans where a movable baffle assembly directs airflow and blocks removal of more than one fan at a time. A plurality of fans held in a fan...
US20150147164 MODIFIED TURBINE COMPONENTS WITH INTERNALLY COOLED SUPPLEMENTAL ELEMENTS AND METHODS FOR MAKING THE SAME  
Modified turbine components include an original turbine component comprising an outer wail enclosing an internal cavity, wherein the outer wall has an original portion removed therefrom to expose...
US20140271151 OIL TRANSFER SYSTEM ON ROTATING SHAFT  
Lubrication system for a device (13) located between an internal shaft (12a) and an external shaft (12b) of an aircraft turbine (10), that are free to rotate, concentric and arranged at least...
US20080134657 Oil Scavenge System for a Gas Turbine Engine  
An oil scavenge system includes a scavenge pipe which extends forward into a relatively long and narrow compartment area of a rear bearing compartment of a gas turbine engine with aggressive core...
US20080095617 Turbine Runner With Reduced Leakage Of Servo Oil  
Due to increasing environmental requirements, oil must be prevented from leaking from a turbine rotor disk and reaching the medium circulating around the turbine. In Kaplan turbines comprising a...
US20140193246 COOLING HOLE WITH CRENELLATION FEATURES  
A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section...
US20150176429 TURBOCHARGER  
A turbocharger includes a turbine housing adapted to be arranged in the middle of an engine exhaust passage, a bearing housing coupled to the turbine housing, a turbine wheel located inside the...
US20150184524 TURBINE AIRFOIL WITH AN INTERNAL COOLING SYSTEM HAVING TRIP STRIPS WITH REDUCED PRESSURE DROP  
A turbine airfoil usable in a turbine engine and having at least one cooling system with an efficient trip strip is disclosed At least a portion of the cooling system may include one or more...
US20090324396 ACCESSORY GEARBOX SYSTEM WITH COMPRESSOR DRIVEN SEAL AIR SUPPLY  
An accessory gearbox system for a gas turbine engine includes a accessory compressor mounted to a gearbox housing.
US20080240910 TURBO-MOLECULAR PUMP, SUBSTRATE PROCESSING APPARATUS, AND METHOD FOR SUPPRESSING ATTACHMENT OF DEPOSITIONS TO TURBO-MOLECULAR PUMP  
A turbo-molecular pump that enables reliable suppression of attachment of depositions onto component parts thereof. The turbo-molecular pump discharges a deposition-causing gas from a processing...
US20070280824 Combination hydrodynamic and rolling bearing system  
The present invention is directed toward a hybrid bearing which will have the advantages of ball bearings as well as hydrodynamic oil films. The present invention is a hybrid bearing assembly for...
US20140341724 STATIC CORE TIE RODS  
A core tie having a varying cross sectional diameter, a component including such a core tie, and a method of casting a hot gas path component for a turbomachine are provided herein. In an...
US20120243978 STEAM TURBINE  
A steam turbine 10 of an embodiment has seal rings 60 between an inlet sleeve 40 for introducing steam and an inner casing 20 and an outer casing 21 into which the inlet sleeve 40 is inserted. The...
US20130315719 Turbine Shroud Cooling Assembly for a Gas Turbine System  
A turbine shroud cooling assembly for a gas turbine system includes an inner shroud component disposed within a turbine section of the gas turbine system and proximate a hot gas path therein,...

Matches 1 - 50 out of 156 1 2 3 4 >