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US20090255116 METHOD OF REPAIRING A FUEL NOZZLE  
A method of repairing a fuel nozzle is disclosed comprising the steps of forming a pilot assembly; installing into a repair bore; inserting a primary adaptor into a repair bore such that the...
US20090255120 METHOD OF ASSEMBLING A FUEL NOZZLE  
A method of assembling a fuel nozzle comprises the steps of forming a pilot assembly; coupling the pilot assembly to a unitary distributor such that the pilot assembly is in flow communication...
US20090255119 METHOD OF MANUFACTURING A UNITARY SWIRLER  
A method for fabricating a unitary swirler is disclosed, the method comprising the steps of determining three-dimensional information of the unitary swirler having a plurality of vanes arranged in...
US20090255118 METHOD OF MANUFACTURING MIXERS  
A method for fabricating a unitary mixer is disclosed, said method comprising the steps of determining three-dimensional information of the unitary mixer having at least one swirler, converting...
US20160138474 LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE  
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan and a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear...
US20150322811 ORC Turbine and Generator, And Method Of Making A Turbine  
A turbine-generator device for use in electricity generation using heat from industrial processes, renewable energy sources and other sources. The generator may be cooled by introducing into the...
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...
US20060260127 Turbine exhaust case and method of making  
A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas...
US20110070072 ROTARY MACHINE TIP CLEARANCE CONTROL MECHANISM  
A tip clearance control mechanism for a rotary machine adapted for reducing leakage flows, and minimizing tip vortex size and penetration into main flow that will improve turbine efficiency. The...
US20080148881 POWER TAKE-OFF SYSTEM AND GAS TURBINE ENGINE ASSEMBLY INCLUDING SAME  
A power take-off system for a gas turbine engine includes a starter coupled to a first spool using a first shaft, and a generator coupled to the second spool using a second shaft, the first shaft...
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....
US20160040547 BLADE OUTER AIR SEAL WITH SECONDARY AIR SEALING  
A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a...
US20120251297 SCALABLE HIGH PRESSURE COMPRESSOR VARIABLE VANE ACUATION ARM  
A variable vane arm has a hook portion comprising a radially inner leg connected to a radially outer leg by an arcuate connection, and an actuation lever extending from the hook portion. The hook...
US20120207608 FINAL-STAGE ROTOR BLADE OF A STEAM TURBINE  
A turbine blade is provided that includes at least certain regions made of fiber reinforced composite material. Also, the turbine blade has at least one anti-erosion component for protecting...
US20090223052 GEARBOX GEAR AND NACELLE ARRANGEMENT  
A gas turbine engine is provided that includes a spool that supports an engine. A gearbox is operatively coupled to the spool through a transmission device configured to transfer rotational drive...
US20120301309 DISSIMILAR METAL WELDS AND ITS MANUFACTURING METHOD OF LARGE WELDED STRUCTURES SUCH AS THE TURBINE ROTOR  
Dissimilar metal welds including a buttering portion with a small variation in strength distribution in a plate thickness direction are formed by welding two parent materials having at least one...
US20140317926 FRONT CENTERBODY SUPPORT FOR A GAS TURBINE ENGINE  
A method for maintaining a gas turbine engine includes providing access from a forward section of a front center body assembly to a flex support mounted to a front center body support. The flex...
US20120260669 FRONT CENTERBODY SUPPORT FOR A GAS TURBINE ENGINE  
A front center body support for a gas turbine engine includes a front center body section, a bearing section and a frustro-conical interface section, the frustro-conical interface section between...
US20080005903 External datum system and film hole positioning using core locating holes  
A turbine engine structure is provided that includes a wall having an exterior surface defining an internal passage. A locating hole extends through the wall from the exterior surface to the...
US20160201606 LOW WEIGHT LARGE FAN GAS TURBINE ENGINE  
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan configured to deliver airflow to a bypass passage, and a core engine configured to rotate...
US20160084104 FAN DRIVE GEAR SYSTEM  
A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. A first fan section support bearing is mounted forward of the speed change mechanism and a...
US20050241149 METHOD FOR MANUFACTURING A STATOR COMPONENT  
Method for manufacturing a stator component that is intended during operation to conduct a gas flow. The component is made up of at least two sections (113) in its circumferential direction, which...
US20160153279 LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE  
A turbine module according to an example of the present disclosure includes, among other things, a fan drive rotor having a plurality of blade rows each including a number of blades. A majority of...
US20160130949 LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE  
A turbine module according to an example of the present disclosure includes, among other things, a fan drive rotor having a plurality of blade rows each including a number of blades. A majority of...
US20150031272 MACHINING TOOL AND METHOD FOR ABRADABLE COATING PATTERN  
A method for forming a pattern in an abradable coating includes the step of machining a groove in the abradable coating with a machining tool. The machining tool is configured to machine a top...
US20090313991 Turbocharger cleaning  
A turbocharger having a cleaning port communicating between an external surface of the turbocharger housing and an internal cavity which communicates with a component of a gas flow control mechanism.
US20160131043 TURBINE ENGINE GEARBOX  
A gas turbine engine comprises a fan, a compressor, a combustor, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction. The gear reduction includes at least...
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.
US20080170958 ROTOR ASSEMBLY AND METHOD OF FORMING  
A rotor assembly for a supercharger is provided having a first rotor section and at least one other rotor section affixed to the first rotor section. The first rotor section and the at least one...
US20090139821 Hydrodynamic torque converter and method for producing the same  
In a hydrodynamic torque converter having a turbine shell and a torsion damper spring carrier jointly mounted to a carrier part by way of rivets extending through aligned openings in the turbine...
US20060096091 Method for manufacturing aircraft engine cases with bosses  
A method of manufacturing turbine engine casings having at least one boss includes, in one exemplary embodiment, forming an engine casing having an outer wall, machining a tapered opening through...
US20140119887 FLUID-COOLED SEAL ARRANGEMENT FOR A GAS TURBINE ENGINE  
A rotational component for a gas turbine engine includes at least one passage with a semi-spherical end.
US20110314833 ADDITIVE INJECTION SYSTEM FOR USE WITH A TURBINE ENGINE AND METHODS OF ASSEMBLING SAME  
A method for assembling an additive injection system for use with a turbine engine includes coupling an atomizing air connection to a fuel nozzle assembly and coupling an additive source to the...
US20110020126 MODULAR ROTOR BLADE FOR A POWER-GENERATING TURBINE AND A METHOD FOR ASSEMBLING A POWER-GENERATING TURBINE WITH MODULAR ROTOR BLADES  
A modular rotor blade for a power generating turbine allows simple replacement of individual rotor blade sections in case of damage to or malfunction of a section. The modular rotor blade includes...
US20160186614 TURBINE EXHAUST CASE ASSEMBLY  
A turbine exhaust case assembly includes a frame which includes an outer ring, an inner ring, a plurality of struts that connect the inner ring and the outer ring and a monolithic fairing assembly...
US20110052412 HIGH-PRESSURE TURBINE ROTOR, AND METHOD FOR THE PRODUCTION THEREOF  
A method for producing a high-pressure turbine rotor, as well as a turbine rotor, is disclosed. The turbine rotor is designed as a blisk (i.e., bladed disk) and forms a radially inward disk and...
US20070163114 Methods for fabricating components  
A method for fabricating an assembly having an airfoil extending radially outwardly from a member includes determining three-dimensional information of the airfoil, converting the...
US20100132377 FABRICATED ITD-STRUT AND VANE RING FOR GAS TURBINE ENGINE  
A gas turbine engine mid turbine frame having an annular interturbine duct and vane ring assembly includes a duct having outer and inner duct walls of sheet metal interconnected by radial hollow...
US20160047268 GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE  
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a spool along an engine axis which drives a gear train, the spool including a low...
US20140248146 ATTACHMENT APPARATUS FOR CERAMIC MATRIX COMPOSITE MATERIALS  
A first ceramic matrix composite structure having a first flange with a first aperture, and a second structure having a second flange with a second aperture are clamped together by a fastener and...
US20080118357 TURBOFAN AND MANUFACTURING METHOD THEREOF  
A turbofan integrally formed with a shroud and a method of manufacturing the same. The turbofan includes a rotating plate rotated by a driving motor, a plurality of blades having first ends...
US20090068016 SHROUDED SINGLE CRYSTAL DUAL ALLOY TURBINE DISK  
A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is...
US20070163115 Turbine platform repair using laser clad  
A method of restoring a gas turbine engine component includes removing a defect section of a turbine engine component according to a template. The template has a standardized shape and is used in...
US20130224004 Radial Diffuser Vane for Centrifugal Compressors  
A turbo machine comprising a rotor assembly comprising at least one impeller, a bearing connected to the rotor assembly, wherein the bearing is configured to rotatably support the rotor assembly,...
US20110255959 TURBINE ALIGNMENT CONTROL SYSTEM AND METHOD  
A turbine that includes a rotor, an inner turbine shell, an outer turbine shell, and a sliding engagement between the inner turbine shell and the outer turbine shell. The inner turbine shell is a...
US20160362983 LOW NOISE TURBINE FOR GEARED TURBOFAN ENGINE  
A method of designing a gas turbine engine comprises the steps of including a fan section with a fan. A turbine section is included having a first turbine and a second turbine. A gear reduction is...
US20150016977 ASSEMBLY OF A TURBOMACHINE  
A turbomachine and a method for the assembly of the turbomachine with a housing and with a rotor, in which at least one cover of the housing is fastened to the rotor, and the combination is placed...
US20140230247 ONE-PIECE MANUFACTURING PROCESS  
A method of making a turbomachine part, wherein the method can include machining a blank into a base having blades extending therefrom, the blades defining a channel therebetween. The method can...
US20100192587 COMBUSTOR ASSEMBLY FOR USE IN A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING SAME  
A combustor assembly for use in a gas turbine engine and method of assembly is described. The combustor assembly includes a combustor liner having a slot that at least partially circumscribes the...
US20090208339 BLADE ROOT STRESS RELIEF  
In a gas turbine engine, a stress relief is formed along a blade root and disk slot junction. An exemplary relief is a chamfer along the pressure side of the blade root extending forward from the...

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