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6960060 |
Dual coolant turbine blade
A turbine blade includes a hollow airfoil joined to a dovetail and platform. The airfoil includes leading and trailing edge cooling circuits disposed between the opposite pressure and suction...
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6957949 |
Internal cooling circuit for gas turbine bucket
In a gas turbine bucket having a shank portion and an airfoil portion having leading and trailing edges and pressure and suction sides, an internal cooling circuit, the internal cooling circuit...
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6955522 |
Method and apparatus for cooling an airfoil
An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum longitudinally located within the leading edge of the airfoils. Within the...
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6955525 |
Cooling system for an outer wall of a turbine blade
A turbine blade for a turbine engine having a cooling system in at least an outer wall. The cooling system in at least the outer wall formed from at least a first plurality of parallel cavities...
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6951444 |
Turbine and a turbine vane for a turbine
The invention relates to a stationary blade ( 12 ) for a gas turbine ( 1 ) with a hollow sectional element ( 22 ) which extends radially with respect to the rotor ( 3 ) and has a platform ( 23 ) at...
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6945749 |
Turbine blade platform cooling system
Aspects of the invention relate to a cooling system for a blade platform that can provide cooling to and reduce stress on the platform. Aspects of the invention relate to including one or more...
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6945750 |
Turbine blade
A turbine blade for a gas turbine has a hollow airfoil extending from a platform. There is a fillet between the airfoil and the platform, both on the pressure side and on the suction side of the...
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6942450 |
Differential pressure sensing system for airfoils usable in turbine engines
A detection system for identifying airfoils having a cooling systems with orifices that are plugged with contaminants or with showerheads having a portion burned off. The detection system measures...
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6939102 |
Flow guide component with enhanced cooling
A cooled fluid flow component for a combustion engine which directs cooling fluid through complementary guided-flow regions to ensure effective cooling of the component tip end, without producing...
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6939107 |
Spanwisely variable density pedestal array
A turbine engine component, such as a blade or vane, has a system for cooling a trailing edge portion thereof. The system includes a plurality of rows of pedestals which vary in density along a...
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6932572 |
Film cooled article with improved temperature tolerance
The invention is a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface 26 to be film cooled. The hot surface 26 includes a depression 48 featuring a...
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6932570 |
Methods and apparatus for extending gas turbine engine airfoils useful life
A method enables a gas turbine engine blade to be manufactured to include an airfoil, a platform, a shank, and a dovetail. The platform extends between the airfoil and the shank, the shank extends...
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6932571 |
Microcircuit cooling for a turbine blade tip
An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes an embedded microcircuit that traverses a tip between a suction sidewall and a...
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6932577 |
Turbine blade airfoil having improved creep capability
A turbine blade including an airfoil having a profile in accordance with Table 1 is disclosed. The turbine blade has a plurality of cooling passages extending radially outward through the airfoil....
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6932573 |
Turbine blade having a vortex forming cooling system for a trailing edge
A turbine blade for a turbine engine having one or more cavities in a trailing edge of the turbine blade for forming one or more vortices in inner aspects of the trailing edge. In at least one...
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6929445 |
Split flow turbine nozzle
A turbine nozzle includes a hollow vane having opposite pressure and suction sides extending in span between outer and inner bands. The vane includes a forward flow channel behind the leading edge,...
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6926499 |
Thin-walled, lightweight cooled turbine blade
A blade 10 is composed of a front blade portion 10 a , a rear blade portion 10 b and a middle blade portion 10 c . The belly side of the middle blade portion 10 c forms a recess towards the...
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6923623 |
Perimeter-cooled turbine bucket airfoil cooling hole location, style and configuration
A turbine stage one bucket has an airfoil having a plurality of cooling holes passing through the airfoil from 0% span to 100% span whereby cooling air exits the airfoil tip into the hot gas path....
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6918742 |
Combustion turbine with airfoil having multi-section diffusion cooling holes and methods of making same
A combustion turbine 20 includes a housing 22 and a plurality of airfoils 40 radially and rotatably positioned within the housing. At least one interior cooling passageway 50 extends within...
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6916155 |
Cooling circuits for a gas turbine blade
A gas turbine blade for an airplane engine, comprising in its central portion at least a first central cooling circuit comprising at least first and second cavities extending radially on the...
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6910864 |
Turbine bucket airfoil cooling hole location, style and configuration
First, second and third sets of cooling holes are provided in a turbine airfoil. The first set of holes adjacent a leading edge have turbulators commencing at a predetermined distance from the root...
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6908657 |
Coated component with through-hole having improved surface finish
A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is...
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6896487 |
Microcircuit airfoil mainbody
A cooling circuit disposed within a first wall portion and a second wall portion of a wall for use in a gas turbine engine is provided. The cooling circuit includes a plurality of inlet apertures...
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6893209 |
Connecting system for a transition duct in a gas turbine
A system for connecting a low-pressure jet to a transition duct in a gas turbine, in which the said low-pressure jets are arranged in sectors of two or three stator blades and are filled on to the...
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6890154 |
Microcircuit cooling for a turbine blade
A turbine blade is provided comprising an internal cavity into which cooling air is flowable, an external wall and a first, second and third cooling circuits embedded with the wall. The cooling...
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6890153 |
Castellated turbine airfoil
A turbine airfoil includes pressure and suction sidewalls joined together at opposite leading and trailing edges, and at a forward bridge spaced behind the leading edge to define a flow channel....
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6887033 |
Cooling system for nozzle segment platform edges
The cooling system for the nozzle edges includes a chamber containing a cooling medium. First and second elongated plenums are disposed along opposite side edges of each platform. Inlet passages...
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6884029 |
Heat-tolerated vortex-disrupting fluid guide component
A vortex-reducing fluid guide component is disclosed. The fluid guide component includes a base portion and an upstanding body portion. An internally-cooled blending element extends between the...
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6884036 |
Complementary cooled turbine nozzle
A turbine nozzle includes outer and inner bands integrally joined to a vane having a three-pass serpentine flow circuit between opposite pressure and suction sidewalls. The outer band includes an...
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6874992 |
Gas turbine engine aerofoil
An aerofoil blade or vane for a gas turbine engine comprises a body member having an inner end for mounting the blade on a shaft and an outer or tip end. A plurality of cooling passages are formed...
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6874988 |
Gas turbine blade
A gas turbine blade includes a combined convective cooling effected by a meandering cooling channel and an impact cooling channel and an impact cooling effected via an impact cooling insert. The...
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6874987 |
Cooled turbine blade
A gas turbine engine turbine blade ( 20 ) has cooling air holes ( 38 ) arranged in groups, the holes ( 38 ) in one group and which span that part of the leading edge ( 34 ) that spans the hottest...
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6869270 |
Turbine blade cover cooling apparatus and method of fabrication
A blade cover cooling apparatus comprises a blade cover top plate, comprising a plurality of upper ribs, a blade cover bottom plate, comprising a plurality of lower ribs. The blade cover top plate...
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6869268 |
Combustion turbine with airfoil having enhanced leading edge diffusion holes and related methods
A combustion turbine 20 includes a housing 22 and a plurality of airfoils 40 within the housing. Each airfoil 40 has a leading edge surface 42 and at least one interior cooling passageway...
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6851924 |
Crack-resistance vane segment member
A crack-resistant vane segment assembly member for an industrial turbine engine is disclosed. The vane segment includes at least one internally-cooled body portion and inner and outer shroud...
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6840737 |
Gas turbine cooling system
A stage of guide vanes ( 20 ) are cooled by compressor air delivered via piping ( 36,38 ) and by leakage air in the space volume ( 28 ) bounded by the combustion apparatus ( 14 ) and turbine...
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6837687 |
Foil formed structure for turbine airfoil
An airfoil body having a first wall including a plurality of ribs. An outer wall formed of a high temperature foil is attached to the ribs so as to form a plurality of channels. The first wall is...
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6837676 |
Gas turbine
A sealing air bypass flow path is provided in a gas turbine for supplying sealing air to a sealing air supply flow path by bypassing the flow path between each tangential on board injection (TOBI)...
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6835046 |
Configuration of a coolable turbine blade
A turbine blade through which cooling liquid flows, comprises several flow channels that are adjacently arranged in the flowing-off direction of the working fluid. The flow channels extend between...
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6832889 |
Integrated bridge turbine blade
A turbine blade includes a hollow airfoil integrally joined to a dovetail. The airfoil includes a perforate first bridge defining a flow channel behind the airfoil leading edge. A second bridge is...
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6830431 |
High-temperature behavior of the trailing edge of a high pressure turbine blade
A moving blade for a high pressure turbine of a turbomachine. The blade has at least one cooling circuit including at least one cavity extending radially between a tip and a root of the blade, at...
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6830432 |
Cooling of combustion turbine airfoil fillets
A turbine fluid guide member ( 10 ) including an airfoil portion ( 12 ), a platform portion ( 14 ) and fillet ( 16 ) joining the airfoil portion to the platform portion. Fillet cooling holes ( 18 a...
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6824360 |
Turbulated cooling holes
A component for use in a flow path of a gas turbine engine. The component includes a body having an exterior surface mountable in the gas turbine engine so the exterior surface is exposed to gases...
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6817190 |
Blade cooling in a gas turbine engine
A gas turbine engine rotor has a body and blades, which are attached to the rotor by a root portion, for receiving a hot fluid flow and a compressed fluid from a compressor. Each blade has a base...
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6817833 |
Turbine blade of a gas turbine with at least one cooling excavation
The invention relates to a turbine blade of a gas turbine with at least one cooling excavation 2 which connects an interior 3 and the surface 4 of the turbine blade 1, characterized in that...
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6811378 |
Insulated cooling passageway for cooling a shroud of a turbine blade
A turbine blade is disclosed having a tip shroud that includes internal passages through which cooling air is flowed to minimize creep. The cooling air is provided to the shroud through dedicated...
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6808367 |
Cooling system for a turbine blade having a double outer wall
A turbine blade for a turbine engine having a double wall having one or more cavities forming a cooling system. The cavity may include a plurality of pedestals and protrusions configured to create...
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6805533 |
Tolerant internally-cooled fluid guide component
A cooled fluid flow component for a combustion engine which employs internal impingement and exterior surface film cooling is disclosed. The fluid flow component has improved tolerance to assembly...
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6805534 |
Curved bucket aft shank walls for stress reduction
A turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank...
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6790005 |
Compound tip notched blade
A gas turbine engine blade includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The pressure sidewall includes an inclined tip rib offset...
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