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7625181 |
Turbine cascade structure
A turbine blade cascade structure includes a plurality of blades arranged in series in a circumferential direction on a wall surface, in which a corner portion defined by the wall surface and a...
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7600972 |
Methods and apparatus for cooling gas turbine engine rotor assemblies
A method and apparatus for a rotor assembly for gas turbine engine are provided. A first rotor blade including an airfoil, a platform, a shank, an internal cavity, and a dovetail is provided,...
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7581930 |
High lift transonic turbine blade
A turbine blade system including a blade airfoil having an airfoil shape with the blade airfoil having a nominal profile substantially in accordance with normalized Cartesian coordinate values Z...
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7581924 |
Turbine vanes with airfoil-proximate cooling seam
Aspects of the invention relate to a turbine vane in which the inner and outer platforms are located substantially entirely on either the pressure side or the suction side of the airfoil. When a...
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7575416 |
Rotor assembly for a rotary machine
A rotor assembly having a seal member in the root section of a rotor blade is disclosed. Various construction details are developed for blocking the flow of gases between adjacent rotor blades. In...
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7553131 |
Integrated platform, tip, and main body microcircuits for turbine blades
A turbine engine component has an airfoil portion with a pressure side and a suction side. The turbine engine component further has a first cooling microcircuit for cooling the suction side of the...
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7549846 |
Turbine blades
A turbine blade is provided for use in a gas turbine engine. The turbine blade has a platform, an airfoil radially extending from the platform, and an attachment portion comprising an asymmetric...
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7534090 |
Enhanced bucket vibration system
An enhanced damping system for a turbine bucket. The damping system includes a damper pocket and a damper pin with an offset center of gravity positioned within the damper pocket.
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7527476 |
Rotor assembly and annulus filler for gas turbine engine compressor
A rotor assembly for a gas turbine engine compressor includes a rotor disc for mounting a plurality of radially extending rotor blades for rotation thereon, an annulus filler for securing to the...
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7497661 |
Gas turbine rotor blade
A rotor blade for a gas turbine, in particular a turbojet, the blade comprising an airfoil, a platform connecting the airfoil to a blade root and having at least one stiffener extending under the...
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7491033 |
Fluid flow machine blade
A fluid flow machine blade ( 1 ) is provided on the outer contour of the airfoil ( 4 ) with a thermal barrier coating ( 41 ). In this context, quite purposefully, only part-regions of the airfoil...
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7488157 |
Turbine vane with removable platform inserts
Aspects of the invention are related to a turbine vane assembly in which at least one of the platforms is equipped with one or more removable platform inserts. The inserts can be used in those...
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7484936 |
Blades for a gas turbine engine with integrated sealing plate and method
A blade for a rotor assembly including a root portion, a platform with an overhang, an airfoil portion and a sealing plate. The sealing plate protrudes from the blade along a circumferential...
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7484935 |
Turbine rotor hub contour
Disclosed herein is a turbine rotor having a contoured hub comprising a cambered surface extending from a leading edge of the rotor hub to a trailing edge of the rotor hub along an axial direction...
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7467924 |
Turbine blade including revised platform
The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The...
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7465155 |
Non-axisymmetric end wall contouring for a turbomachine blade row
A turbomachine blade row is provided having a hub that includes a non-axisymmetric end wall modified by a transformation function. The blade row further includes a circumferential row of a...
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7458779 |
Gas turbine or compressor blade
A gas turbine or compressor blade, includes a convex outer surface or suction side and a concave inner surface or pressure side, these sides being joined at their upstream ends by a leading edge...
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7452184 |
Airfoil platform impingement cooling
A gas turbine engine airfoil has a platform cooling scheme including an impingement hole for directing cooling air against an undersurface of the airfoil platform.
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7445433 |
Fan or compressor blisk
A fan or compressor blisk for a gas turbine engine, lift fan or the like, comprises a disc having a radially outer rim, and a plurality of aerofoil blades circumferentially spaced around and...
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7442007 |
Angled blade firtree retaining system
A blade root retaining system for attachment of a turbine blade to a turbine disc of a gas turbine engine comprises a blade root having at least one projection on each of opposite sides thereof,...
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7431564 |
Turbine blisk
A blisk for use in the turbine section of a gas turbine engine comprises a disk around the circumference of which is disposed a plurality of blades in an annular array. The blades are preferably...
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7416391 |
Bucket platform cooling circuit and method
In a turbine bucket having an airfoil portion and a root portion with a platform at an interface between the airfoil portion and the root portion, a platform cooling arrangement including: a...
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7399163 |
Rotor blade for a compressor or a gas turbine
Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, including a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at...
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7374400 |
Turbine blade arrangement
A turbine blade arrangement comprises turbine blades which are secured in adjacent positions to a rotor disc with a cavity defined between root segments and platform segments. A flow deflector...
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7371046 |
Turbine airfoil with variable and compound fillet
A turbine airfoil may be a rotating blade having a single platform, or a stationary nozzle having a pair of platforms. The airfoil body has pressure and suction sidewalls extending between leading...
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7354243 |
Axial compressor blading
An axial compressor has at least one circumferential row of aerofoil members ( 30 a , 30 b , 30 c ) in which at least one of the two end walls ( 37 ) between adjacent blades is given a...
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7334995 |
Turbine blade assembly and method of manufacture
Aspects of the invention are directed to a turbine blade assembly and an associated method of manufacture. The turbine blade assembly can include: (a) a unitary structure having an airfoil and a...
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7334983 |
Integrated bladed fluid seal
Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a...
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7322797 |
Damper cooled turbine blade
A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A...
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7322796 |
Turbine vane construction
A method for forming a component for use in a gas turbine engine, such as a turbine vane construction is provided. The method broadly comprises the steps of: forming a first aerodynamic structure...
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7309212 |
Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge
In a turbine bucket having an airfoil portion and a root portion with a substantially planar platform at an interface between the airfoil portion and the root portion, a platform cooling...
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7300253 |
Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring
The invention relates to a gas turbine blade or vane ring having a supporting structure and gas turbine blades or vanes secured to it. The gas turbine blades or vanes have a blade or vane root,...
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7284958 |
Separable blade platform
A gas turbine engine blade platform including a par of platform retention members. The pair of platform retention members are configured to be located on opposite sides of a disk lug. The retention...
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7264447 |
Sealing arrangement for an axial turbine wheel
In an axial turbine wheel including a rotor disk and a plurality of turbine blades each having a base end retained by the rotor disk via a joint and extending radially from the rotor disk, a seal...
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7255536 |
Turbine airfoil platform cooling circuit
An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit...
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7252477 |
Rotating blade body
A rotating blade body is provided that can restrain vibrations of rotating blades effectively. The rotating blade body comprises a rotor disc, a plurality of rotating blades being assembled so as...
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7249933 |
Funnel fillet turbine stage
A turbine stage includes a row of airfoils and their platforms spaced laterally apart to define flow passages therebetween. Each airfoil is integrally joined to its platform at a funnel-shaped...
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7249928 |
Turbine nozzle with purge cavity blend
A turbine nozzle for a gas turbine engine includes a nozzle segment having an airfoil-shaped vane with a root, a tip, a leading edge, a trailing edge and opposed curved pressure and suction sides....
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7244104 |
Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
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7220103 |
Impingement cooling of large fillet of an airfoil
A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which, together with an impingement rib, defines a...
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7220100 |
Crescentic ramp turbine stage
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...
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7217094 |
Airfoil with large fillet and micro-circuit cooling
A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which partially defines a fillet cavity therebehind,...
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RE39630 |
Turbine blisk rim friction finger damper
A damper for reducing vibrations in an integrally bladed turbine disk is provided. The damper includes an annular member and a plurality of fingers. The annular member is configured so that it is...
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7214034 |
Control of leak zone under blade platform
A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities...
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7207776 |
Cooling arrangement
A cooling arrangement comprises a support ( 20 ) for a plurality of blades ( 22 ). The support ( 20 ) comprises a plurality of blade mounting members ( 28 ) provided between adjacent blades ( 22 )....
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7198467 |
Method and apparatus for cooling gas turbine engine rotor blades
A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined...
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7189063 |
Methods and apparatus for cooling gas turbine engine rotor assemblies
A method for assembling a rotor assembly for gas turbine engine is provided. The method includes providing a first rotor blade that includes an airfoil, a platform, a shank, and a dovetail. The...
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7189056 |
Blade and disk radial pre-swirlers
A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
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7186089 |
Cooling system for a platform of a turbine blade
A turbine blade for a turbine engine having a platform cooling system formed from one or more platform cooling channels extending from an inner cooling cavity in a root of a turbine blade to an...
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7179049 |
Gas turbine gas path contour
Gas flow is redirected by a feature disposed on a trailing edge of at least one segment of a peripheral gas path defining surface to improve alignment with a downstream portion of the gas path.
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