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US20130224027 SCALLOPED SURFACE TURBINE STAGE WITH PURGE TROUGH  
A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord...
US20130017091 RADIAL TURBINE BACKFACE CURVATURE STRESS REDUCTION  
A turbine wheel is disposed about an axis and has a back having a separator disposed thereon, an inner undercut disposed between the separator and the axis, and an outer undercut disposed between...
US20110110780 ANNULUS FILLER FOR A GAS TURBINE ENGINE  
An annulus filler is provided for mounting to a rotor disc of a gas turbine engine. The filler comprises a lid for bridging the gap between two adjacent blades attached to the rotor disc. The...
US20150050150 ANNULUS FILLER  
An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a...
US20130004315 MATEFACE GAP CONFIGURATION FOR GAS TURBINE ENGINE  
In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending...
US20140169973 Ni-Based Heat Resistant Alloy, Gas Turbine Component and Gas Turbine  
A Ni-based heat resistant alloy has a composition of, by mass percent, carbon: 0.001 to 0.1%, chromium: 16 to 22%, aluminum: 0.5 to 1.5%, molybdenum: 0.1 to 2.0%, tungsten: 0.1 to 6.0%, niobium:...
US20140356172 TURBINE WHEEL IN A TURBINE ENGINE  
The invention relates to a turbine wheel (104) comprising a plurality of blades having roots engaged axially and held radially in slots (34) in a disk (22) alternating between teeth (36) of the...
US20150125305 LOW PROFILE FAN PLATFORM ATTACHMENT  
A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a...
US20070177979 Vane comprising a transition zone  
A vane of a guide vane or impeller blade of a turbo machine, particularly a gas turbine. The profile of the vane includes at least one thickening that is advantageous for flow purposes in a...
US20130004331 TURBINE BLADE OR VANE WITH SEPARATE ENDWALL  
A turbine engine airfoil structure including an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine. The airfoil structure further includes a...
US20090004006 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...
US20070140854 Vane arrangement and a method of making vane arrangement  
Within gas turbine engines 10 it is necessary to provide fixed vanes which comprise an aerofoil in the gas flow through the gas turbine engine 10. These vanes are subject to significant stressing....
US20120263596 ANNULUS FILLER SYSTEM  
An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends...
US20080085190 Turbine airfoil with submerged endwall cooling channel  
A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may be positioned in an endwall attached to the turbine airfoil. The...
US20070014667 Method for loading and locking tangential rotor blades and blade design  
A method of loading and locking a plurality of tangential rotor blades is provided. The method includes the steps of providing a disk having a slot and a pair of rails adjacent the slot,...
US20080044284 Segmented fluid seal assembly  
A rotor assembly for a turbine engine includes a rotor disk having rotor blades mounted about the circumference and rotatable about a central longitudinal axis. A fluid seal extends about the...
US20080263863 Dimensional restoration of turbine blade knife edge seals  
A turbine blade assembly comprising a knife edge seal having at least one seal member. The at least one seal member comprising a restored portion fused to a stub portion, where the restored...
US20140356173 TURBINE ENGINE WHEEL, IN PARTICULAR FOR A LOW PRESSURE TURBINE  
The invention relates to a turbine engine wheel (2), in particular for a low pressure turbine (1), the wheel having blades (4), each comprising an airfoil (5) connected by a platform (6) to a...
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...
US20070258817 Blade or vane with a laterally enlarged base  
A blade or vane includes a platform 130 and an airfoil 132 extending from the platform. The airfoil has a pressure surface offset in a first direction D1 from a part span mean camber line 148, a...
US20140271206 TURBINE BLADE WITH A PIN SEAL SLOT  
A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure...
US20140003949 INTERBLADE PLATFORM FOR A FAN, ROTOR OF A FAN AND ASSOCIATED MANUFACTURING METHOD  
The invention concerns an interblade platform (3) of a turbomachine fan, characterized in that it is produced: in an aluminum alloy belonging to the 7xxx series that has undergone full-temper heat...
US20100143140 FLUID FLOW MACHINE WITH SIDEWALL BOUNDARY LAYER BARRIER  
A fluid flow machine has a main flow path in which at least one row of blades (2) is arranged, with at least one blade end of a blade row (2) being firmly connected to the main flow path...
US20060029500 Turbine blade flared buttress  
A turbine blade construction having a flared buttress is disclosed. The turbine blade is of the type adapted for use within a gas turbine engine and includes a buttress so as to fortify the area...
US20100221113 INTERNALLY-DAMPED AIRFOIL AND METHOD THEREFOR  
An airfoil component and method for producing the component. The component has root and airfoil portions, the latter having an airfoil tip and oppositely-disposed concave and convex surfaces that...
US20070231144 Axial-flow compressor for a gas turbine engine  
An axial-flow compressor for a gas turbine engine has a rotor drum (2) in thermally lower loaded first compressor stages (3 to 6) which includes a one-piece ring, or rotor rings (7 to 10) attached...
US20110223025 GAS TURBINE ENGINE ROTOR SECTIONS HELD TOGETHER BY TIE SHAFT, AND WITH BLADE RIM UNDERCUT  
An integrally bladed rotor is utilized in at least a stage of one of a compressor and turbine section. Airfoils extend radially outwardly from a platform, and there is an undercut inward from the...
US20140271205 TURBINE BLADE PIN SEAL  
A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure...
US20070160476 Turbine component trailing edge and platform restoration by laser cladding  
A method of restoring a gas turbine engine component includes depositing a filler material onto a sulphidation section of an underside of a turbine engine platform and laser consolidating the...
US20140193265 ROTOR DISK INCLUDING A PLURALITY OF HOOKS  
A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors. At least one of the...
US20070269313 TURBOMACHINERY BLADE HAVING A PLATFORM RELIEF HOLE  
A turbomachinery blade having a relief hole in its platform and a method of limiting the formation and/or propagation of cracks in the trailing edge of the blade are provided. The relief hole may...
US20090148295 Gas Turbine Engine Systems Involving Rotor Bayonet Coverplates and Tools for Installing Such Coverplates  
Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine...
US20090123286 ASSEMBLY OF A FAN BLADE AND OF ITS DAMPER, FAN BLADE DAMPER AND METHOD FOR CALIBRATING THE DAMPER  
The invention relates to a fan blade assembly of a turbojet with fan and a fan blade damper, the fan blade comprising a root and a platform, the fan blade damper being suitable for being attached...
US20080101935 Variable compressor stator vane having extended fillet  
An example variable stator vane assembly includes at least one button, a vane airfoil adjacent to the button, and a fillet defined between the button and the airfoil. In one example, the fillet...
US20050220622 INTEGRAL COVERED NOZZLE WITH ATTACHED OVERCOVER  
A method and system of constructing equivalent integral covered blading for a turbine having multiple blades supported by a stator include multiple blade foils; multiple respective cover portions...
US20070031260 Turbine airfoil platform platypus for low buttress stress  
A blade is provided for use in a gas turbine engine. The blade has a platform, an airfoil portion extending radially from a first side of the platform, and an attachment portion extending from a...
US20070258819 Airfoil array with an endwall protrusion and components of the array  
An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28, or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of...
US20080193293 Bladed disk assembly method and impact device  
A bladed disk assembly device includes a horizontal arm and a fixed vertical pivot bar that is perpendicularly attached to a first end of the horizontal rotating arm via a sliding coupling...
US20080159866 Fan blade for a gas turbine engine  
An injection-moulded thermoplastic mini-platform (42) is adhesively bonded, in use, to the aerofoil surfaces of a fan blade (312) in a gas turbine engine. The mini-platform (42) is divided into a...
US20110243742 STATOR STAGE FOR TURBOMACHINE COMPRESSOR  
A turbomachine stator stage comprising two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the...
US20070048140 Methods and apparatus for assembling gas turbine engines  
A method for assembling a gas turbine engine compressor having a plurality of stages and a plurality of blades coupled to each respective stage includes depositing a silicone oxime sealant onto at...
US20100040479 Gas Turbine Engine Systems Involving Baffle Assemblies  
Gas turbine engine systems involving baffle assemblies are provided. In this regard, a representative baffle assembly for a gas turbine engine includes: a cooling plenum defining a cooling air...
US20090004012 COVER PLATE FOR TURBINE ROTOR HAVING ENCLOSED PUMP FOR COOLING AIR  
A cover plate for use with a rotor disk in a gas turbine engine includes an enclosed chamber associated with a web on the rotor disk. The enclosed chamber ensures that adequate cooling air is...
US20140212292 Airfoil Member and Composite Platform Having Contoured Endwall  
An airfoil member and platform assembly for a gas turbine engine is provided. The platform to which the airfoil member is anchored is made of a composite material and includes an endwall defining...
US20070258818 Airfoil array with an endwall depression and components of the array  
An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28 or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of...
US20140056711 AIRCRAFT ENGINE ANNULAR SHROUD COMPRISING AN OPENING FOR THE INSERTION OF BLADES  
An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into...
US20080286106 TURBINE ROTOR BLADE ASSEMBLY AND METHOD OF FABRICATING THE SAME  
A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to...
US20080095614 FAN PLATFORM FIN  
The invention relates to a fan platform of a bypass turbomachine having a primary stream and a secondary stream. The platform defines a portion of the surface of the nose around which the primary...
US20100054942 BLADE ASSEMBLY  
Blade assemblies are provided in a number of forms. These blade assemblies may have blades secured to disks (blisk), rings (bling) and drums (blum). The blades and/or the rotor elements formed by...
US20060110254 Thermal barrier coating for turbine bucket platform side faces and methods of application  
Grooves are formed along portions of the side edges of a turbine bucket platform and open through the side edges of the surface of the platform exposed to the hot gas path of the turbine. A bond...

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