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US20130108438 TURBINE BUCKET FOR USE IN GAS TURBINE ENGINES AND METHODS FOR FABRICATING THE SAME  
A turbine bucket for use with a turbine engine. The turbine bucket includes an airfoil that extends between a root end and a tip end. The airfoil includes an outer wall that defines a cavity that...
US20130039760 OIL MIST SEPARATION IN GAS TURBINE ENGINES  
A rotor stage is provided which comprises a shank passage for separating liquid from secondary air system (SAS) air. The shank passage is formed between a radially outer surface of a disc post, a...
US20080181768 Axial rotor section for a rotor of a turbine  
Disclosed is an axial rotor section for a rotor of a turbine, on which a sealing element, which is provided on an end side surface, is secured by means of a bolt against movement in the...
US20130315738 AIRFOIL AND PLATFORM ASSEMBLY FOR SUPERSONIC FLOW  
An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of...
US20130315739 AIRFOIL AND PLATFORM ASSEMBLY FOR SUBSONIC FLOW  
An assembly including an airfoil for a bladed wheel together with a platform, the airfoils in association with such platforms forming a bladed wheel. The platform surface presents a...
US20110064580 TURBOFAN FLOW PATH TRENCHES  
An integrally bladed disk includes a rim and blades. The blades are circumferentially spaced and extend integrally outward from the rim to define a flow path therebetween. The periphery of the rim...
US20090081044 POLYGON ROTOR ATTACHMENT DEVICE  
A rotor and shaft assembly for turbomachinery has a polygon shaped drive collar interposed between corresponding polygonal mating surfaces of a drive shaft and a rotor hub. The mating surfaces of...
US20130164137 TURBOFAN FLOW PATH TRENCHES  
An integrally bladed disk includes a rotor disk and circumferentially spaced first and second blades. The rotor disk has a rim the periphery of which forms a flow surface. The first and second...
US20090180885 METHODS AND APPARATUS TO REPAIR A ROTOR DISK FOR A GAS TURBINE  
Embodiments of the invention can provide methods and apparatus to repair a rotor disk for a gas turbine. In one embodiment, a method to repair a rotor disk for a gas turbine is provided, wherein...
US20130259700 NEAR-FLOW-PATH SEAL ISOLATION DOVETAIL  
A turbine bucket includes an airfoil portion; a platform at radially inner end of the airfoil portion; a shank portion extending radially-inwardly of the platform; and a mounting portion extending...
US20110016875 GUIDE VANE HAVING HOOKED FASTENER FOR A GAS TURBINE  
A stator vane for a gas turbine includes a vane airfoil which extends in the longitudinal direction of the vane and which is delimited by a leading edge and a trailing edge, and also an outer...
US20080267766 ROTOR SUPPORTS AND SYSTEMS  
A rotor support includes a first ring disposed around a first axis, a second ring disposed around the first axis downstream from the first ring, and a plurality of beams extending between the...
US20130045104 COMPOSITE RINGS FOR IMPELLER-SHAFT FITTING  
Systems and methods for attaching one or more impellers to a shaft and attaching composite rings to a back and front lip on each impeller to secure the impellers for high angular velocity...
US20090311103 ROTOR FOR STEAM TURBINE AND METHOD OF MANUFACTURING THE SAME  
A steam turbine rotor shaft and a method of manufacturing the same are provided wherein the sliding characteristics of a journal are improved, and the journal is free from welding cracks and does...
US20090214348 METHOD FOR MANUFACTURING THE ROTOR ASSEMBLY OF A ROTATING VACUUM PUMP  
A rotor assembly for rotary vacuum pumps has improved mechanical characteristics and low manufacturing cost due to a one-step thermal coupling of a rotor having a male axial projection and its...
US20080050245 TURBOMACHINE ROTOR BLADE  
A turbomachine rotor blade comprising a root (14) mounted in a channel of the periphery of a disk and held by an annular flange (18) which presses on the root (14) of the blade (12), this root...
US20110061394 METHOD OF HEAT TREATING A NI-BASED SUPERALLOY ARTICLE AND ARTICLE MADE THEREBY  
A method of heat treating an Ni-base superalloy article is disclosed. The method includes hot-working an article comprising an NiCrMoNbTi superalloy comprising, in weight percent, at least about...
US20090263249 Welded Low-Pressure Turbine Shaft  
Turbo-engine which has a low-pressure area, containing at least one shaft, wherein the low-pressure area has an inflow area, the shaft having, at least on its inflow part arranged in the inflow...
US20100251713 Steam turbine power plant  
An intermediate-pressure turbine is divided into a high-temperature, high-pressure side high-temperature, intermediate-pressure turbine section 11a and a low-temperature, low-pressure side...
US20140369840 CONNECTOR  
A connector for connecting an impeller to a shaft is provided. The connector is formed as a unitary body. The connector has a sleeve portion which is frictionally connected on a radially outer...
US20080253894 Co-forged steel rotor component for steam and gas turbine engines  
A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an outer ring formed from a first steel material, and a disk formed from a second...
US20080292465 Rotating apparatus disk  
A method (20) of fabricating a large component such as a gas turbine or compressor disk (32) from segregation-prone materials such as Alloy 706 or Alloy 718 when the size of the ingot required is...
US20120269637 METHODS FOR CONTROLLING FRICTION BETWEEN HETEROGENEOUS CONTACT SURFACES  
A method of conditioning a first, heterogeneous contact surface for operational engagement with a second contact surface, the method comprising: performing a smoothing operation on part or all of...
US20080025843 Mounting disc  
Mounting discs (20, 30, 40, 50) are used in gas turbine engines to present turbine or compressor blades. These discs (20, 30, 40, 50) incorporate a bore or cob end 31, 41, 51 which in turn...
US20100111673 TURBINE WITH INTERRUPTED PURGE FLOW  
A blade attachment apparatus for a turbine is provided and includes a member, which rotates about an axis of the turbine, including fore and aft disk posts that retain corresponding fore and aft...
US20130224028 COMPONENT BLENDING TOOL ASSEMBLY  
A component blending tool assembly, includes a material removing surface that is moved to provide a blended area in a component, the material removing surface having a spherical contour mimicking...
US20100054944 Rotor assembly for an exhaust gas turbocharger  
In a rotor assembly for an exhaust gas turbocharger including a turbine wheel and a compressor wheel mounted on a common shaft for joint rotation wherein the turbine wheel consist of a metal...
US20080267780 MIXING AND/OR EVAPORATION DEVICE AND RESPECTIVE MANUFACTURING METHOD  
The invention relates to a mixing and/or evaporation device for an exhaust system, an internal combustion engine, having a tubular body on whose one axial end are arranged several blades adjacent...
US20070258820 Torque converter blade with self-locking blade tab  
The present invention broadly comprises a blade for a torque converter including an outer edge arranged to conform to an inner surface of a shell in the torque converter and a first tab extending...
US20130115088 COMPRESSOR WHEEL SHAFT WITH RECESSED PORTION  
A turbocharger assembly includes a compressor wheel with a base surface, a nose surface, a z-plane disposed between the base surface and the nose surface and a bore extending from the base surface...
US20090214347 SPLIT RING FOR A ROTARY PART OF A TURBOMACHINE  
A split ring for mounting with elastic prestress in an annular groove of a rotary part of a turbomachine and having, in the free state, a diameter that is greater than the diameter of the groove,...
US20090041584 Kinetic hydro power triangular blade hub  
A rotor hub mounting arrangement for removably mounting a plurality of turbine rotor blades to the rotor hub in a compact and secure manner. The rotor hub includes an internal mounting assembly,...
US20130121834 FAN HUB DESIGN  
A fan rotor has a fan web and a plurality of circumferentially spaced-apart fan blades extending radially outwardly from an outer rim of the fan web. The outer rim is integrally connected to an...
US20140133989 TURBINE ENGINE PART FORMING A COMPRESSOR STATOR OR A TURBINE NOZZLE, AND METHOD FOR FABRICATING SAME  
A turbine engine part forming a compressor stator or a turbine nozzle and including an inner shroud, an outer shroud, and vanes extending substantially radially between the inner and outer shrouds...
US20120034084 PROCESS FOR PRODUCING A TURBINE WHEEL FOR AN EXHAUST GAS TURBOCHARGER  
The invention relates to a process for producing a turbine wheel for an exhaust gas turbocharger by metal powder injection molding, which comprises the following steps: (a) provision of a...
US20120263597 TURBOMACHINE ROTOR WITH ANTI-WEAR SHIM BETWEEN A DISK AND AN ANNULUS  
The present invention relates to a turbomachine rotor comprising a disk with a rim and axial cavities machined into the rim to individually house blades, an annulus pierced with stress-relief...
US20120244001 RETAINING RING ASSEMBLY AND SUPPORTING FLANGE FOR SAID RING  
A retaining ring assembly for at least one blade of a rotor disk of a turbine engine and a supporting flange for the ring. The flange and the ring are rotating parts having an axis X, the flange...
US20130323063 SYSTEM FOR ATTACHING A TURBOJET ENGINE SPINNER  
According to the invention, the upstream rotor of a turbomachine, of longitudinal axis L-L, comprising a spinner (2) coaxial with the axis L-L and which is attached removably to the upstream end...
US20110255978 Locking Assembly For Circumferential Attachments  
A locking spacer assembly is provided for use with a rotor blade assembly. The locking spacer assembly includes a first end portion, a second end portion, at least one securing device, and a...
US20110116931 METHOD FOR INCREASING THE COEFFICIENT OF ADHESION BETWEEN TWO PARTS ROTATING AS ONE WITH A ROTOR  
A method for increasing the coefficient of adhesion between two parts that rotate as one with a rotor, for example a turbomachine rotor, those parts pressing against one another via pressing...
US20110255979 IMPELLER FOR TURBINE  
An impeller for a turbine includes an impeller body formed by alternately stacking and fixing two or more types of disk blades, a base plate, and a rotating shaft. A plurality of pressed vane...
US20130323052 RETAINING RING  
A retaining ring assembly for a gas turbine engine. The retaining ring assembly may include a discontinuous ring member having first and second portions of reduced cross-sectional area. The second...
US20150167471 SYSTEM AND METHOD FOR SECURING AXIALLY INSERTED BUCKETS TO A ROTOR ASSEMBLY  
A rotor wheel assembly includes a rotor wheel having a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. The rotor wheel also has a plurality of...
US20110176921 METHOD OF REPAIRING OR REWORKING A TURBOMACHINE DISK AND REPAIRED OR REWORKED TURBOMACHINE DISK  
The invention relates to a method of repairing or of reworking a turbomachine disk comprising, on it's rim, at least one external radial tab with an axial bore to accept an axial pin comprising a...
US20120051919 POWDER COMPACT ROTOR FORGING PREFORM AND FORGED POWDER COMPACT TURBINE ROTOR AND METHODS OF MAKING THE SAME  
A forging preform for a turbine rotor disk is disclosed. The preform includes a body of a superalloy material having a mass of about 5000 lbs or more, the superalloy material having a...
US20140056712 TURBINE BUCKET INCLUDING AN INTEGRAL ROTATION CONTROLLING FEATURE  
A turbine bucket including an integral rotation controlling feature is disclosed. In one embodiment, a turbine bucket includes: a blade section having an inner radial end and an outer radial end;...
US20110243744 SEAL FOR A PLATFORM IN THE ROTOR OF A TURBINE ENGINE  
A seal for an intermediate platform provided between two adjacent blades in the rotor of a turbine engine, the seal having an elongate shape with an upstream end and a downstream end, and...
US20120076657 GAS TURBINE ENGINE AND MAIN ENGINE ROTOR ASSEMBLY AND DISASSEMBLY  
One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine main engine rotor. Still another embodiment is a unique method for...
US20110206519 FASTENER APERTURE HAVING AN ELONGATED GEOMETRY  
An apparatus includes a substrate having one or more fastener apertures that extend therethrough. Each fastener aperture has a centerline and includes first and second circular segmented regions...
US20140109548 HIGH PRESSURE ROTOR DISK  
A rotor disk for a gas turbine engine is disclosed and formed to enable operation at high rotational speeds in a high temperature environment. The rotor disk is formed to include a bore, a live...

Matches 1 - 50 out of 133 1 2 3 >