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US20120275919 |
HIGH EFFICIENCY WIND TURBINE HAVING INCREASED LAMINAR AIRFLOW
A wind turbine is provided with turbine blades mounted for axial rotation about an axis. The blades are surrounded by a shroud to define an axial air passage. A conical ring is attached to the... |
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US20150118062 |
BUCKET ASSEMBLY FOR USE IN A TURBINE ENGINE
An assembly for use in a turbine engine is provided. The assembly includes a first bucket, a second bucket circumferentially adjacent to the first bucket, a shroud extending between the first and... |
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US20130011265 |
CHEVRON PLATFORM TURBINE VANE
Gas turbine vanes of a gas turbine vane assembly have a reconfigured platform shape so as to reduce the ingestion of hot combustion gases into platform gaps between adjacent vane assemblies is... |
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US20080089788 |
Part span shrouded fan blisk
Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the... |
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US20130209258 |
TIP SHROUDED BLADE
A tip shrouded blade includes an airfoil rotatable about an axial centerline. Also included is a tip shroud connected at a radially outer tip of the airfoil, wherein the tip shroud includes at... |
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US20080038116 |
Turbine Blade Tip Shroud
A turbine blade tip shroud. The tip shroud may include a platform, a number of Z-notched positioned within the platform, a number of seal rails positioned on the platform, and a number of cavities... |
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US20130038067 |
Eddy-Type Wind Power Generator
An eddy-type wind power generator includes an inlet tube, an outlet tube and an electricity-generating assembly. The inlet tube has a first end and a second end. The first end has an inlet, an... |
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US20110008170 |
SHROUD AND ROTARY VANE WHEEL OF PROPELLER FAN AND PROPELLER FAN
A shroud includes a body portion 5B, a mount 7 positioned at a center of the body portion 5B and supporting rotary vane wheel driver 6, and multiple support beams 10 radially extending from the... |
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US20120107123 |
Shroud Segment to be Arranged on a Blade
A shroud segment to be arranged on a gas turbine blade is disclosed. The shroud segment includes a shroud segment surface and a stiffening structure that is raised relative to the shroud segment... |
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US20100061856 |
STEAM TURBINE ROTATING BLADE FOR A LOW PRESSURE SECTION OF A STEAM TURBINE ENGINE
A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one... |
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US20080019836 |
Damping Arrangement for Guide Vanes
A damping arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine, is disclosed. Referring to this damping arrangement, the radially external ends of the... |
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US20130045120 |
SEGMENTED FAN ASSEMBLY
Systems and devices for thermodynamically regulating portions of a dynamoelectric machine are disclosed. In one embodiment, a fan assembly element includes: an axially inner shroud segment... |
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US20130266447 |
ANNULUS FILLER
A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an... |
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US20140023506 |
DAMPER SYSTEM AND A TURBINE
A damper system and a turbine are provided. The damper system includes a plurality of CMC blades. Each CMC blade has a first member of a tip shroud, the first member opposite a second member of... |
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US20110268575 |
SPOKE FOR A STATOR COMPONENT, STATOR COMPONENT AND METHOD FOR MANUFACTURING A STATOR COMPONENT
A spoke for a stator component for conducting a gas flow during operation includes at least two wall parts connecting a leading edge and a trailing edge of the spoke, and a middle portion between... |
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US20070122285 |
AXIAL-FLOW FAN
The present invention provides an axial-flow fan capable of entirely cooling an object to be cooled even when the distance between the object to be cooled and an air discharge opening of the... |
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US20150147179 |
BLADE WITH 3D PLATFORM COMPRISING AN INTER-BLADE BULB
A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the... |
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US20130129493 |
TURBINE
A turbine is provided including an annular turbine blade body (50) disposed on a flow path, a diaphragm outer ring (11) installed at a tip side of the blade body via a clearance, and seal fins... |
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US20170183974 |
SHROUDED TURBINE ROTOR BLADES
A rotor blade for a gas turbine that is configured for use within a row of samely configured rotor blades attached to and circumferentially spaced about a rotor disc. The rotor blade may further... |
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US20170183972 |
MIDSPAN SHROUDED TURBINE ROTOR BLADES
A rotor blade for a gas turbine configured for use within a row of samely configured rotor blades. The rotor blade may further include: an airfoil defined between pressure and suction faces; and a... |
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US20170183971 |
TIP SHROUDED TURBINE ROTOR BLADES
A rotor blade for a gas turbine that includes an airfoil and a tip shroud. The tip shroud may have a seal rail that projects radially from an outboard surface and extends circumferentially. The... |
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US20170175533 |
ALLOY, WELDED ARTICLE AND WELDING PROCESS
An alloy is disclosed, including, by weight, about 13% to about 17% chromium, about 16% to about 20% molybdenum, about 1.5% to about 4% silicon, about 0.7% to about 2% boron, about 0.9% to about... |
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US20170114644 |
ROTATING BLADE
The present invention relates to a rotating blade for a turbomachine, in particular a compressor stage or a turbine stage of a gas turbine, particularly of an aircraft engine, having a blade... |
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US20170096901 |
SHROUDED BLADE FOR A GAS TURBINE ENGINE
A turbine blade for a gas turbine engine comprises a platform, a blade root, an airfoil portion defining pressure and suction sides, and a shroud provided at a tip of the airfoil portion opposite... |
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US20160348525 |
TRAILING EDGE PLATFORM SEALS
A platform trailing edge seal for a turbomachine airfoil (e.g., a blade or vane) assembly includes a body configured to extend into an aft portion of a mateface gap defined between a... |
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US20160312625 |
BLADE WITH TIP SHROUD
A blade includes a leading edge, a trailing edge, a pressure surface, a suction surface, a root end, a tip end, a tip shroud attached to the tip end, the tip shroud comprising a platform and a... |
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US20160298478 |
GAS TURBINE BUCKET SHANKS WITH SEAL PINS
The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a shank assembly may include a component shank with a platform including... |
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US20160290355 |
FAN IMPELLER
A fan impeller includes a plurality of fan blade assembly members, each one of the fan blade assembly members respectively includes a metal ring bracket and a plurality of metal blades, one end of... |
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US20160245107 |
TURBINE BLADE AND GAS TURBINE
A turbine blade with a turbine blade aerofoil, a turbine blade root and a turbine blade platform located between the turbine blade aerofoil and the turbine blade root and having, in its underside,... |
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US20160244175 |
UNDUCTED FAN FOR AN AIRCRAFT TURBINE ENGINE
Unducted fan for an aircraft turbine engine, comprising at least one propeller comprising a hub and an annular array of blades extending substantially radially outwards from said hub, the hub... |
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US20160194973 |
FAN PLATFORM WITH LEADING EDGE TAB
A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a... |
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US20160108749 |
TURBINE BLADE TIP SHROUD
A turbine blade tip shroud (22C, 22D) with a seal rail (32C, 32D) oriented in a circumferential direction of rotation (29) relative to a turbine axis, and extending radially outward from the tip... |
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US20160084103 |
SHROUDED BONDED TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME
Methods are provided for manufacturing a shrouded bonded turbine rotor. A shrouded blade ring is formed. The shrouded blade ring is formed by bonding a unitary shroud ring to an assembled blade... |
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US20160076385 |
TURBOMACHINE BLADE TIP SHROUD
Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and... |
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US20160059364 |
WIDE GAP BRAZE
A method to fill a gap in a component according to one disclosed non-limiting embodiment of the present disclosure includes applying an alloy powder onto the component such that the alloy powder... |
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US20160024939 |
Rotor blade assembly, turbomachine comprising a rotor blade assembly and method of assembling a rotor blade assembly
A rotor blade assembly has aerofoil, root and supplementary components. The aerofoil component includes an aerofoil shaped section and aerofoil connection section for connecting the aerofoil... |
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US20160024933 |
BLADING WITH BRANCHES ON THE SHROUD OF AN AXIAL-FLOW TURBOMACHINE COMPRESSOR
The invention relates to an axial-flow turbomachine blading comprising a semi-circular row of blades extending radially. Each blade comprises a airfoil and lateral branches or lateral legs. Each... |
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US20150377036 |
FAN AIRFOIL SHROUDS WITH AREA RULING IN THE SHROUDS
A shrouded airfoil may have a suction surface and a pressure surface. An at least first suction surface shroud may be disposed on the suction surface and an at least first pressure surface shroud... |
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US20150377035 |
SEGMENTED TURBINE SHROUD WITH SEALS
A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier segment, a blade track segment, and a... |
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US20150369046 |
Low Speed Fan for Gas Turbine Engines
In accordance with one aspect of the disclosure, a fan section for a gas turbine engine is disclosed. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported... |
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US20150315918 |
SHROUDED TURBINE BLADE WITH CUT CORNER
A method includes determining a vibration characteristic of a shrouded turbine blade, which includes an airfoil attacked to a shroud. A corner of the shrouded turbine blade can be removed after... |
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US20150247414 |
PLATFORM FOR CERAMIC MATRIX COMPOSITE TURBINE BLADES
The present disclosure provides for a turbine wheel having a blade platform disposed to compliantly secure ceramic turbine blades to a rotatable disk. The platform includes opposing ends to engage... |
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US20140154082 |
PRE-SINTERED PREFORM REPAIR OF TURBINE BLADES
A process is provided for repairing a damaged portion of a gas turbine blade comprising: providing a preform comprising a low-melt alloy material and a base alloy material; locating the preform on... |