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6139269 |
Turbine blade with multi-pass cooling and cooling air addition
A convectively cooled turbine blade has two distinct cooling air passage systems. The first system cools the blade leading edge and emits cooling air through outlet passageways in the leading edge...
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6135715 |
Tip insulated airfoil
A turbine airfoil includes a squealer rib extending outwardly from a tip cap to define a tip cavity thereatop. A thermal insulator is disposed in the tip cavity atop the tip cap.
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6132169 |
Turbine airfoil and methods for airfoil cooling
A turbine engine airfoil includes a three-pass serpentine shaped cooling cavity including a leading edge chamber, an oversized intermediate chamber, and a trailing edge chamber in flow...
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6129515 |
Turbine airfoil suction aided film cooling means
Film cooling effectiveness for internally air cooled turbine blades of gas turbine engines is enhanced by including an interconnecting passage to the film cooling hole that is in communication with...
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6126397 |
Trailing edge cooling apparatus for a gas turbine airfoil
A coolable airfoil is disclosed which includes an internal cavity, an external wall, a plurality of first apertures, and a plurality of second apertures. The external wall includes a suction-side...
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6126396 |
AFT flowing serpentine airfoil cooling circuit with side wall impingement cooling chambers
A gas turbine engine hollow airfoil includes an airfoil outer wall having width wise spaced aparted pressure and suction side walls joined together at chordally spaced apart leading and trailing...
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6120244 |
Structure and method for inserting inserts in stationary blade of gas turbine
An insert inserting structure and a method for enabling a stationary blade of a gas turbine to withstand high temperatures of even 1500 C. in order to realize a 150° C. class gas turbine is...
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6120249 |
Gas turbine blade platform cooling concept
A turbine blade with a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Cooling air passages are formed in the blade root platform just below its...
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6116854 |
Gas turbine moving blade
A gas turbine moving blade assembly in which a cooling effect at a leading edge of the blade, which is exposed to a high temperature combustion gas, is enhanced by an arrangement of turbulators in...
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6109867 |
Cooled turbine-nozzle vane
A turbine-nozzle vane fitted with a cooling system including a hollow airfoil (45) inserted between an outer deck and an inner deck (46). Disposed inside the airfoil (45) is a liner (60) which is...
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6099253 |
Gas turbine rotor blade
A gas turbine rotor blade has a plurality of first cooling holes for the flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for...
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6099251 |
Coolable airfoil for a gas turbine engine
A hollow airfoil is provided having a leading edge, a trailing edge, and a wall including a suction side portion and a pressure side portion. The wall, which includes an interior surface and an...
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6099252 |
Axial serpentine cooled airfoil
A gas turbine engine airfoil includes an axial serpentine cooling circuit therein. A plurality of the serpentine circuits are preferably stacked in a radial row along the airfoil trailing edge for...
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6099244 |
Cooled stationary blade for a gas turbine
In the present invention, seal air passes through a tube extending in a stationary blade from an outside shroud to an inside shroud, flows into a cavity to keep the pressure in the cavity high so...
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6089826 |
Turbulator for gas turbine cooling blades
A gas turbine cooled blade has leading edge turbulators. A rounded tip portion of the leading edge portion cooling passage (3) is approximated by a triangular cooling passage (1) having orthogonal...
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6086328 |
Tapered tip turbine blade
A turbine blade includes a hollow airfoil extending from an integral dovetail. The airfoil includes sidewalls extending between leading and trailing edges and longitudinally between a root and a...
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6079946 |
Gas turbine blade
In the cooling system for the gas turbine blade, the apparatus of the present disclosure ensures cooling of the trailing edge part of the blade for which machining is difficult, while aiming at...
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6071075 |
Cooling structure to cool platform for drive blades of gas turbine
A mechanism for cooling the platform for the drive blades of a gas turbine uses a simple configuration which reliably cools the platform. The mechanism includes cooling channels in the interior of...
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6065928 |
Turbine nozzle having purge air circuit
A turbine nozzle includes radially outer and inner bands between which extend a plurality of vanes. The vanes include impingement baffles having impingement holes for impinging cooling air inside...
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6065932 |
Turbine
A turbine (10) for a gas turbine engine includes an annular array of turbine aerofoil blades (12) which are mounted on a disc (19). Each of the aerofoil blades (12) is provided with a radially...
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6065931 |
Gas turbine moving blade
A gas turbine moving blade, which has a blade root section, a wing section, and a platform section, comprises a refrigerant supply port provided in the blade root section, a refrigerant recovery...
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6059530 |
Twin rib turbine blade
A turbine blade includes an airfoil and integral dovetail. The airfoil includes first and second sidewalls joined together at leading and trailing edges, and extending from a root to a tip plate....
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6056507 |
Article with brazed end plate within an open body end
A method for preparing a Ni base superalloy inner wall surface of a body open end, such as an end of a turbomachinery blade, and an end plate, such as a blade tip cap, for brazing together at a rim...
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6050777 |
Apparatus and method 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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6048169 |
Turbine shaft and method for cooling a turbine shaft
A turbine shaft extends along a principal axis and has an outer surface. The turbine shaft is formed by a plurality of cylindrical shaft segments which are disposed axially one behind the other and...
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6039537 |
Turbine blade which can be subjected to a hot gas flow
A turbine blade which can be subjected to a hot gas flow includes a substrate, at least one interior space and a plurality of bores leading from the interior space out of the substrate. The...
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6036440 |
Gas turbine cooled moving blade
The present invention relates to a gas turbine cooled moving blade in order to cool the gas turbine using steam alone. In the moving blade, two cavities are installed in the lower part of the...
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6036436 |
Gas turbine cooling stationary vane
There is provided a cooled stationary blade of a gas turbine in which the portions which can be cooled sufficiently by air are air-cooled, and the portions which are difficult to cool by air are...
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6036441 |
Series impingement cooled airfoil
A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and extending longitudinally from a root to a tip. The sidewalls are spaced...
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6033181 |
Turbine blade of a gas turbine
According to the invention, turbine blades are provided that have increased functional reliability, which is achieved in that the interior space (8) of the blade body (3) in the region of the...
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6027306 |
Turbine blade tip flow discouragers
A turbine assembly comprises a plurality of rotating blade portions in a spaced relation with a stationery shroud. The rotating blade portions comprise a root section, a tip portion and an airfoil....
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6019579 |
Gas turbine rotating blade
A gas turbine rotating blade comprises a serpentine passage provided in the blade width direction in plural rows in a blade profile portion except the portion near the trailing edge having a small...
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6019573 |
Heat recovery type gas turbine
In a steam cooled type gas turbine, taking the effect of efficiency and power output into consideration, a rear stage is sufficiently cooled by air in place of cooling all of the stages by steam....
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6017189 |
Cooling system for turbine blade platforms
A cooling system is disclosed for cooling the platforms of turbine blades fixed to the periphery of a turbine rotor, each turbine blade having an airfoil portion, a platform with opposite...
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6004095 |
Reduction of turbomachinery noise
In the invention, propagating broad band and tonal acoustic components of noise characteristic of interaction of a turbomachine blade wake, produced by a turbomachine blade as the blade rotates,...
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6004100 |
Trailing edge cooling apparatus for a gas turbine airfoil
A hollow airfoil is provided having a pressure side wall, a suction side wall, a cavity formed between the pressure and suction side walls, a plurality of cooling ports disposed within the pressure...
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6000909 |
Cooling medium path in gas turbine moving blade
A gas turbine moving blade having a cooling medium flow path constructed so that a concave spherical surface (C) is formed on a inside surface of an end portion of the cooling medium path (B)...
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6000908 |
Cooling for double-wall structures
A coolable double walled structure, for use and exposure in a hot gas flow environment, includes a jet issuing wall, a target wall spaced from the jet issuing wall defining at least one cavity...
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5997251 |
Ribbed turbine blade tip
A gas turbine engine turbine blade squealer tip includes an airfoil tip cap having an airfoil shape and pressure and suction sides joined together at chordally spaced apart leading and trailing...
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5997245 |
Cooled shroud of gas turbine stationary blade
The invention relates to a cooled shroud in a gas turbine stationary blade which is able to flow a cooling air in the entire area of an inner shroud for cooling thereof. Three stationary blades are...
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5993156 |
Turbine vane cooling system
A turbine vane-system cooling system uses three internal cooling cavities 1, 12, 13) separated by two radial walls (9, 10). The upstream cavity (11) uses a helical ramp (30) and is fed through an...
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5984637 |
Cooling medium path structure for gas turbine blade
A cooling medium path structure for cooling a gas turbine blade. The structure includes a disk-side cooling medium path, a blade-side cooling medium path formed at the root portion of the blade and...
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5980209 |
Turbine blade with enhanced cooling and profile optimization
A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip...
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5980202 |
Gas turbine stationary blade
A gas turbine stationary blade having a cooling medium passage and outer and inner shrouds in a blade section, comprising a hollow portion in the blade section, the hollow portion including a...
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5975850 |
Turbulated cooling passages for turbine blades
A turbine blade including an airfoil section having contoured surface geometries between the consecutive ribs or turbulators on the leading edge passage walls is described. The contoured surface...
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5975851 |
Turbine blade with trailing edge root section cooling
A convectively cooled turbine blade has two distinct cooling air passage systems. The first system cools the blade leading edge and emits cooling air through outlet passageways in the leading edge...
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5971708 |
Branch cooled turbine airfoil
A turbine airfoil includes a plurality of internal ribs joined to laterally opposite first and second sidewalls to define a pair of serpentine cooling circuits therein. A span rib extends...
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5967755 |
Product with a metallic basic body and method for manufacturing a product
A product and a method for manufacturing the product include a metallic basic body with at least one longitudinal duct disposed therein and with a number of transverse ducts branching off from the...
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5967752 |
Slant-tier turbine airfoil
A turbine airfoil includes a plurality of internal ribs joined to laterally opposite first and second sidewalls to define a serpentine cooling circuit therein. A span rib extends longitudinally...
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5961287 |
Twin-web rotor disk
A rotor disk for a gas turbine engine having an axis of rotation and an axial centerline is provided which includes a rim, forward and aft hubs, and forward and aft webs. The forward web extends...
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