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6241466 |
Turbine airfoil breakout cooling
A turbine airfoil includes pressure and suction sides extending between leading and trailing edges and defining an internal cooling air passage. A row of trailing edge holes is disposed in flow...
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6241467 |
Stator vane for a rotary machine
A coolable stator vane 46 having a platform 48, 54 having internal cooling for the platform is disclosed. Various construction details are developed for cooling the interior of the platform in the...
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6241469 |
Turbine blade
Described is a turbine blade with a metal blade body and a protective coating constructed of a porous intermetallic felt, and in the blade body of the turbine blade cooling air channels are...
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6238182 |
Joint for a turbine component
An improved joint for a turbine component including an outer wall member, an inner wall member disposed within the outer wall member, and at least one air channel formed therebetween. The improved...
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6234755 |
Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture
A method is described for improving the cooling effectiveness of a fluid which flows through a row of passage holes in a substrate (e.g., a turbine component), out to a high-temperature surface of...
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6234754 |
Coolable airfoil structure
A coolable airfoil structure having internal heat transfer features through which cooling air is flowed under operative conditions is disclosed. Various construction details and features are...
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6234746 |
Apparatus and methods for cooling rotary components in a turbine
A cooling system for turbomachinery includes a compressor bleed air passageway for supplying bleed cooling air to a plurality of circumferentially spaced, generally axially extending passages in...
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6234753 |
Turbine airfoil with internal cooling
The flow of cooling fluid through core tie holes formed between the internal cooling passageways of turbine airfoils is reduced by disposing flow deflectors on the wall adjacent to the holes. The...
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6231307 |
Impingement cooled airfoil tip
A turbine airfoil includes pressure and suction sidewalls joined together at leading and trailing edges, and extending from root to tip. The tip includes a tip rib extending from a tip cap...
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6227801 |
Turbine engine having improved high pressure turbine cooling
A turbine engine having improved high pressure turbine cooling is disclosed. In the engine, relatively cool intermediate pressure (P2x) air is diverted from a region of a compressor section and...
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6227804 |
Gas turbine blade
A gas turbine blade is provided with a hollow blade effective section and a blade implanted section operatively connected to the blade effective section and the gas turbine blade is formed with: a...
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6224336 |
Triple tip-rib airfoil
A turbine airfoil includes pressure and suction sidewalls extending between leading and trailing edges and from root to tip. The tip includes a floor bounding an internal cooling channel within the...
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6224337 |
Thermal barrier coated squealer tip cavity
A turbine blade squealer tip includes an airfoil shaped tip cap having a squealer tip wall extending radially outwardly from and around the perimeter of the airfoil shaped tip cap to define a...
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6220817 |
AFT flowing multi-tier airfoil cooling circuit
A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits having outer and inner serpentine portions, respectively, in different...
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6213714 |
Cooled airfoil
An actively cooled component having a plurality of film cooling discharge apertures passing through a heat transfer pedestal. In one embodiment the pedestal is elongated so as to provide good...
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6210112 |
Apparatus for cooling an airfoil for a gas turbine engine
A hollow airfoil is provided which includes a body, a trench, and a plurality of cooling apertures disposed within the trench. The body extends chordwise between a leading edge and a trailing edge,...
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6210111 |
Turbine blade with platform cooling
A cooled turbine blade for a gas turbine engine having a platform cooling supply channel that supplies cooling air to a plurality of cooling holes in the surface of the blade platform adjacent the...
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6206638 |
Low cost airfoil cooling circuit with sidewall impingement cooling chambers
A gas turbine engine airfoil includes an airfoil outer wall having widthwise spaced apart pressure and suction sidewall sections extending chordally between leading and trailing edges of the...
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6200087 |
Pressure compensated turbine nozzle
A turbine nozzle includes inner and outer bands having respective air inlets. A plurality of hollow vanes are integrally joined to the bands in flow communication with the inlets. Each vane...
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6200088 |
On-line monitor for detecting excessive temperatures of critical components of a turbine
A monitor for detecting overheating of a critical component in a combustion turbine is provided. The monitor, when used in conjunction with a closed-loop cooling system, comprises a coating...
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6196798 |
Gas turbine cooling blade
A number of air-transpiration holes (4) are provided at a leading edge portion (2) of a cooled blade (1). Cooling air flowing through a cooling air passage (15) formed inside of the blade blows out...
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6196799 |
Gas turbine moving blade platform
A gas turbine moving blade platform having a simplified cooling structure for effecting uniform cooling of the platform. The platform (1) includes cavities (2, 3, 4) and an impingement plate (11)...
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6196791 |
Gas turbine cooling moving blades
In gas turbine cooled moving blade, a cooling air passage is made shortest and temperature elevation and pressure drop of the cooling air are suppressed. The cooling air passage (16) is bored in a...
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6190128 |
Cooled moving blade for gas turbine
A cooled moving blade for a gas turbine which has a blade profile capable of more effectively reducing thermal stress in a blade base portion and, thus, preventing cracks from occurring. A moving...
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6190129 |
Tapered tip-rib turbine blade
A gas turbine engine rotor blade 18 includes a dovetail 22 and integral airfoil 24. The airfoil includes a pair of sidewalls 28,30 extending between leading and trailing edges 32,34, and...
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6190120 |
Partially turbulated trailing edge cooling passages for gas turbine nozzles
A plurality of passages are spaced one from the other along the length of a trailing edge of a nozzle vane in a gas turbine. The passages lie in communication with a cavity in the vane for flowing...
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6186741 |
Airfoil component having internal cooling and method of cooling
The flow of cooling fluid through a core tie hole formed between a pair of internal cooling passageways of an airfoil component is reduced by providing a restriction that meters coolant flow...
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6186740 |
Gas turbine cooling blade
In a gas turbine cooling blade, cooling passages are defined by ribs formed therein. The cooling blade comprises an insert fitted in one of the cooling passages at the front edge of the blade, a...
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6183198 |
Airfoil isolated leading edge cooling
A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and spaced apart from each other therebetween to define a leading edge...
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6183194 |
Cooling circuits for trailing edge cavities in airfoils
An airfoil having a trailing edge cavity formed by a leading wall and a trailing edge connected by a pair of side walls which converge at the trailing edge to define a cooling passage of...
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6183199 |
Cooling-air bore
A cooling wall comprises an outer surface, which is exposed to a hot-gas flow, an inner surface, and at least one film-cooling hole within the wall, which film-cooling hole has a diffuser section...
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6179556 |
Turbine blade tip with offset squealer
An industrial turbine assembly comprises a plurality of rotating blade portions in a spaced relation with a stationary shroud. The rotating blade includes a root section, an airfoil having a...
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6179565 |
Coolable airfoil structure
A coolable airfoil structure having internal heat transfer features through which cooling air is flowed under operative conditions is disclosed. Various construction details and features are...
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6176678 |
Apparatus and methods for turbine blade cooling
A turbine blade includes a platform and an airfoil having a plurality of trailing edge slots separated by land areas larger than the slots. The slots have an exit diffusion half angle of about two...
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6176676 |
Cooling system for a main body used in a gas stream
Structure with elements includes a main body of the element used in gas stream and a plurality of fluid passage. Each outlet of the fluid passage is opened on surface of the main body. Coolant...
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6174134 |
Multiple impingement airfoil cooling
A turbine airfoil includes first and second sidewalls joined together at leading and trailing edges, and spaced apart to define first and second cavities separated by a septum therebetween. An aft...
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6174133 |
Coolable airfoil
Apparatus and method including a coolable airfoil for exposure in a hot fluid flow of a machine portion. The airfoil is configured to be connectable with the machine portion and includes a...
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6174135 |
Turbine blade trailing edge cooling openings and slots
A turbine blade including an airfoil having a plurality of trailing edge slots and a plurality of trailing edge openings for use in a turbine engine is described. The trailing edge slots extend...
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6168381 |
Airfoil isolated leading edge cooling
A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in flow communication with an isolation flow channel disposed therebehind. The isolation...
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6164912 |
Hollow airfoil for a gas turbine engine
A hollow airfoil is provided which includes a body having an external wall and an internal cavity. The external wall includes a suction side portion and a pressure side portion. The portions extend...
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6164913 |
Dust resistant airfoil cooling
A turbine airfoil includes first and second sidewalls joined together at leading and trailing edges, and extending longitudinally from root to tip. An internal cooling circuit is disposed between...
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6164914 |
Cool tip blade
A turbine blade includes a hollow airfoil having a squealer tip rib extending outboard from a tip cap enclosing the airfoil. An impingement baffle is spaced inboard from the tip cap to define a tip...
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6158955 |
Welding method and assembly therefor
An assembly and method for welding an article, such as an air-cooled superalloy airfoil of a gas turbine engine nozzle. The method entails inserting a fixture into a cooling passage of the airfoil....
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6155778 |
Recessed turbine shroud
A turbine shroud includes a panel having inner and outer surfaces extending between forward and aft opposite ends. The panel includes forward and aft hooks for supporting the panel radially atop a...
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6153889 |
Method and an apparatus for inspecting articles
An apparatus (42) for inspecting an as cast turbine blade (40), with impingement cooling passages (36) (see FIG. 2 ), comprises a vacuum pump (52) arranged to evacuate the interior of the turbine...
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6152695 |
Gas turbine moving blade
In a gas turbine moving blade 1, the convection of cooling air is promoted to enhance the heat transfer rate, the cooling effect of a shroud 2 is enhanced and the entire cooling effect of the blade...
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6151881 |
Air separator for gas turbines
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6152694 |
Tip shroud for moving blades of gas turbine
A tip shroud (11) for a moving blade to be used at a downstream stage of a gas turbine. The tip shroud is extended in its creep lifetime by feeding it effectively with cooling air. In the tip...
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6146098 |
Tip shroud for cooled blade of gas turbine
A tip shroud for a moving blade that is made thin and light for use at a gas turbine downstream stage. Cooling air holes (13 to 16) having a slot shape, are formed in a tip shroud (11) of the...
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6142734 |
Internally grooved turbine wall
A turbine wall includes an outer surface for facing combustion gases, and an opposite inner surface for being impingement air cooled. A plurality of adjoining ridges and grooves are disposed in the...
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