Matches 1 - 50 out of 136 1 2 3 >


Match Document Document Title
US20090104028 METHOD AND APPARATUS FOR DISTRIBUTING FLUID INTO A TURBOMACHINE  
An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within...
US20130189079 ROTOR WITH INLET PERIMETERS  
A device for use in a molten metal pump helps alleviate jams between rotating rotor blades and a stationary pump base. The device includes inlet perimeters that partially define one or more...
US20160146019 COOLING CHANNEL FOR AIRFOIL WITH TAPERED POCKET  
The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various...
US20100034640 NESTED CORE GAS TURBINE ENGINE  
A fan for creating lift or thrust having a fan hub and fan blades depending from the fan hub. The fan blades have slots formed therein with openings facing substantially aft, relative to a...
US20110097191 METHOD AND STRUCTURE FOR COOLING AIRFOIL SURFACES USING ASYMMETRIC CHEVRON FILM HOLES  
A film-cooled turbine structure is configured with one or more asymmetric chevron film cooling holes for improving film cooling for a variety of airfoil surfaces or airfoil regions, particularly...
US20110097188 STRUCTURE AND METHOD FOR IMPROVING FILM COOLING USING SHALLOW TRENCH WITH HOLES ORIENTED ALONG LENGTH OF TRENCH  
A turbine airfoil includes a plurality of shallow trenches. Each trench includes a plurality of film holes disposed within and located along the lengthwise direction of the trench and angled...
US20100124485 Aerofoil cooling arrangement  
Within aerofoils (50, 150, 250, 350), and in particular nozzle guide vane aerofoils in gas turbine engines problems can occur with regard to coolant flows (56, 57; 156, 157; 256, 257; 356, 357)...
US20080061559 Use of Air Internal Energy and Devices  
A method of converting air internal energy into useful kinetic energy is based on air flowing through substantially convergent nozzle, which accelerates the air as the cross section of the nozzle...
US20140030065 Steam Turbine, and Steam Turbine Stationary Blade  
The present invention is a steam turbine comprising a turbine stage having a stationary blade and a moving blade provided on the downstream side of the stationary blade in a working fluid flow...
US20100175380 TRAVERSING FUEL NOZZLES IN CAP-LESS COMBUSTOR ASSEMBLY  
A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud,...
US20080124210 ROTARY ASSEMBLY COMPONENTS AND METHODS OF FABRICATING SUCH COMPONENTS  
A rotor assembly for a turbine is provided. The rotor assembly includes a first portion of a rotor component forged from a first material. The first material is processed using a first process....
US20080003096 High coverage cooling hole shape  
A cooling hole for a gas turbine engine component has a bi-lobed shape to improve cooling effectiveness. The gas turbine engine component has a first outer surface and a second outer surface...
US20160090843 TURBINE COMPONENTS WITH STEPPED APERTURES  
Turbine components include at least one fluid flow passage at least one aperture disposed on a surface of the turbine component and fluidly connected to the at least one fluid flow passage. The at...
US20140301820 TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH NOZZLE INJECTION FOR A GAS TURBINE ENGINE  
A turbine engine shutdown temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine blade assembly during shutdown of a gas...
US20160201474 GAS TURBINE ENGINE COMPONENT WITH FILM COOLING HOLE FEATURE  
A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly...
US20160178199 COMBUSTOR DILUTION HOLE ACTIVE HEAT TRANSFER CONTROL APPARATUS AND SYSTEM  
Systems and methods are described herein whereby an air jet is configured to manipulate local aerodynamics and/or boundary layer flows associated with a dilution hole. A gas turbine component...
US20160169004 COOLING PASSAGES FOR GAS TURBINE ENGINE COMPONENT  
A gas turbine engine component includes a wall having an inner surface and an outer surface. At least one non-rectangular slot extends through the outer wall surface and is in communication with a...
US20160047549 CERAMIC MATRIX COMPOSITE COMPONENTS WITH INSERTS  
A gas turbine engine is disclosed that includes a compressor, a combustor, and a turbine. The turbine includes a turbine shroud having a blade track formed from a ceramic matrix composite...
US20110250053 FLUID TURBINES  
Shrouded fluid turbines of various configurations are disclosed. The shrouded fluid turbines include an impeller, a turbine shroud surrounding the impeller, and an ejector shroud around the...
US20110135446 Castings, Casting Cores, and Methods  
If a refractory metal core (RMC) is punched, the punching asymmetry may be reflected in an asymmetry of the cast article features cast by the punched features. The punched features may have a...
US20110083444 LOW BTU FUEL INJECTION SYSTEM  
A system includes a gas turbine compressor including multiple radial protrusions disposed about a circumference of the gas turbine compressor. Each radial protrusion includes multiple gaseous fuel...
US20150219119 BLOWER  
A blower 10 includes: a housing 11 having an intake port 16 and a flow passage 22 that communicates with a discharge port 17; an impeller 13 disposed in the housing 11 so that the front surface...
US20170101871 BLADE FOR FLUID FLOW MACHINE, TURBO FAN ENGINE AND METHOD FOR MANUFACTURING A BLADE  
A blade/vane for a turbomachine that has a blade/vane outer skin and a blade/vane internal structure is provided. The blade/vane internal structure has a plurality of elongated support elements...
US20120301275 INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR MODULE FOR A GAS TURBINE ENGINE  
A rotor module for a gas turbine engine includes a multiple of CMC airfoil rows which extend from a common CMC drum.
US20110052373 HIGH-TURNING DIFFUSER STRUT WITH FLOW CROSS-OVER SLOTS  
A turning strut for use in a diffuser of a turbine engine has a leading edge with first and second opposing surfaces depending therefrom that terminate at a trailing edge. Slots extend through the...
US20110044796 FLUIDFOIL TIP VORTEX DISRUPTION  
A fluidfoil tip vortex disruption arrangement. There is a fluid inlet on a pressure side of the fluidfoil; and a fluid outlet in a low pressure region at or near the tip of the fluidfoil. Fluid...
US20170051614 TURBINE COMPONENT COOLING HOLE WITHIN A MICROSURFACE FEATURE THAT PROTECTS ADJOINING THERMAL BARRIER COATING  
Cooling holes in a turbine component, such as a blade, vane or combustor transition, are formed in and surrounded by a micro surface feature (MSF) that protects the adjoining thermal barrier...
US20160201476 AIRFOIL FOR A TURBINE ENGINE  
An airfoil for a turbine engine includes a cooling cavity and a cooling fluid supply cavity which supplies cooling fluid to the cooling cavity through a passage. The cooling cavity can be provided...
US20140030056 PROCESS GAS FLOW GUIDES FOR LARGE AREA PLASMA ENHANCED CHEMICAL VAPOR DEPOSITION SYSTEMS AND METHODS  
The present invention provides methods and apparatus for a gas diffusion assembly in a deposition processing chamber. The invention includes a backing plate having an inlet for providing a process...
US20110044797 ELECTRICAL CONDUCTOR PATHS  
A component, for example an aerofoil vane or other gas path structure in a gas turbine machine such as a gas turbine engine, in which an insulated electrical conductor path (2) is embedded...
US20140255145 Systems and Methods for Providing a Flow of Purge Air and an Adjustable Flow of Cooling Air in a Gas Turbine Application  
Embodiments of the disclosure include systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity or a stator cavity. According to one...
US20160010466 GAS TURBINE ENGINE COMPONENT WITH TWISTED INTERNAL CHANNEL  
A gas turbine engine component includes a component body that defines an internal micro-channel that extends in a lengthwise direction along a reference line. The internal micro-channel extends...
US20100008759 METHODS AND APPARATUSES FOR PROVIDING FILM COOLING TO TURBINE COMPONENTS  
Methods and apparatuses for film cooling of one or more turbine components are provided. A cooling gas flow passage provides a cooling gas to an turbine component with the hot gas path of a...
US20130223987 Turbine Nozzle Insert  
A turbine nozzle insert of a gas turbine engine is disclosed. The insert may comprise an elongated hollow body portion, a flange portion formed at a first end of the elongated body portion, and a...
US20120257954 METHOD FOR COOLING TURBINE STATORS AND COOLING SYSTEM FOR IMPLEMENTING SAID METHOD  
A method and system for cooling turbine engine turbines, the system includes: at least one pair of parts to be cooled, the pair including a stator upstream from the rotor valve, and a sealing ring...
US20160298464 COOLING HOLE PATTERNED AIRFOIL  
An airfoil having a cooling hole pattern is disclosed. The cooling hole pattern may be an offset herringbone pattern. For instance, the airfoil may have rows of cooling holes arranged in filmrows,...
US20100178157 HEAT EXCHANGE ELEMENT, MANUFACTURING METHOD THEREOF, AND HEAT EXCHANGE VENTILATOR  
A heat exchange element according to the present invention has a stacked-layer structure in which sheet-like partition members and spacing members are stacked alternately, while the spacing...
US20090169361 COOLED TURBINE NOZZLE SEGMENT  
A turbine nozzle segment may have a band having a flange extending radially from a non-flowpath side and an aft end. A plurality of airfoils may extend radially from a flowpath side of the band...
US20050135923 Cooled vane cluster  
A cast vane cluster with enhanced cooling contains an inner and an outer platform and at least two airfoils for directing a primary fluid stream axially rearward. A duct is bounded by inner, an...
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...
US20090016871 Systems and Methods Involving Variable Vanes  
Systems and methods involving vanes are provided. In this regard, a representative method for modifying the throat area between vanes of a gas turbine engine includes: directing a gas flow path of...
US20090060714 Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component  
A multi-part cast component for a turbine engine includes a first component section having a main body portion including at least one cooling flow passage section, and a second component section...
US20160245097 AIRFOIL AND METHOD FOR MANUFACTURING AN AIRFOIL  
An airfoil includes a pressure side, a suction side opposed to the pressure side, a cavity inside the airfoil between the pressure and suction sides, and a trailing edge downstream from the cavity...
US20130149106 STEAM TURBINE, BLADE, AND METHOD  
A stator blade ring comprising a plurality of stator blade modules defining an annular chamber is provided. The plurality of stator blade modules comprises an elongated blade portion comprising a...
US20100266382 WIND TURBINE WITH BOUNDARY LAYER CONTROL  
The invention relates to a wind turbine comprising a rotor with a hub and turbine blades, and further comprising a boundary layer control system for the turbine blades. A plurality of pressure...
US20070048122 Debris-filtering technique for gas turbine engine component air cooling system  
Air cooling passages for a gas turbine engine component, and in particular, a blade outer air seal, are provided with a filtering technique to filter impurities before they can reach a metering...
US20130136579 EXHAUST-GAS TURBOCHARGER  
An exhaust-gas turbocharger (1), having a shaft (2) on which are arranged a compressor wheel (3) and a turbine wheel (4), a bearing housing (5) in which are arranged a compressor-side bearing...
US20070065273 Methods and apparatus for double flow turbine first stage cooling  
Method and apparatus for cooling a double flow steam turbine are provided. In one embodiment, the method includes supplying steam to the turbine to form a main inlet steam flow, allowing steam to...
US20160201908 VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR  
A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly...
US20160237853 TURBINE EXHAUST CASE WITH COATED COOLING HOLES  
An effusion-cooled component includes a base portion defining at least one oversized cooling hole preform. A coating is disposed on the base portion and at least partially covers the oversized...

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