|
Match
|
Document |
Document Title |
|
|
7611330 |
Turbine blade with triple pass serpentine flow cooling circuit
A turbine blade used in a gas turbine engine, the blade having a dual triple pass serpentine flow cooling circuit to provide cooling to the blade. A first triple pass serpentine flow circuit...
|
|
|
7607891 |
Turbine component with tip flagged pedestal cooling
A turbine blade for a gas turbine engine is provided with improved cooling at a radially outer portion of the trailing edge. A tip flag path is provided with a first pedestal array to increase the...
|
|
|
7607890 |
Robust microcircuits for turbine airfoils
A cooling microcircuit for use in a turbine engine component, such as a turbine blade, having an airfoil portion is provided. The cooling microcircuit has at least one inlet slot for introducing a...
|
|
|
7607889 |
Turbine blade and gas turbine equipped with a turbine blade
The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane having a platform that extends transversally...
|
|
|
7600973 |
Blades for gas turbine engines
A blade for a gas turbine engine comprises an aerofoil having a root portion, a tip portion located radially outwardly of the root portion, and leading and trailing edges extending between the root...
|
|
|
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,...
|
|
|
7600966 |
Turbine airfoil with improved cooling
A turbine airfoil includes an outer wall and a plurality of cooling passages or minicores formed in the outer wall. A web separates each adjacent pair of the minicores. In order to provide more...
|
|
|
7597540 |
Turbine blade with showerhead film cooling holes
A showerhead cooling arrangement for a turbine airfoil in which the showerhead includes a row of film cooling holes on the stagnation point of the leading edge, a row of pressure side film cooling...
|
|
|
7597539 |
Turbine blade with vortex cooled end tip rail
A turbine blade having a squealer tip includes a trailing edge tip rail formed as an extension of the pressure side tip rail and the suction side tip rail. Positioned along the trailing edge tip...
|
|
|
7597536 |
Turbine airfoil with de-coupled platform
An airfoil used in a gas turbine engine, such as a turbine blade, includes a thin slot formed between a platform section and an airfoil section of the blade, with a metering hole providing for a...
|
|
|
7591070 |
Turbine blade tip squealer and rebuild method
A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls...
|
|
|
7588413 |
Upstream plasma shielded film cooling
An upstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of...
|
|
|
7584538 |
Method of forming a turbine blade with cooling channels
A method of constructing a turbine blade for a gas turbine engine is provided. The method includes casting the blade, forming a plurality of spaced-apart notches in the airfoil proximate the tip on...
|
|
|
7581928 |
Serpentine microcircuits for hot gas migration
A turbine engine component, such as a turbine blade, has an airfoil portion with a pressure side and a suction side. The turbine engine component also has a first cooling circuit within the...
|
|
|
7581920 |
Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor
An air circulation method in a turbomachine compressor includes minimizing an inner flowpath between two adjacent blades by providing labyrinths on an inner casing between the two adjacent blades,...
|
|
|
7578653 |
Ovate band turbine stage
A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer...
|
|
|
7578652 |
Hybrid vapor and film cooled turbine blade
An apparatus for a gas turbine engine includes an airfoil defining a leading edge and a trailing edge, a root located adjacent to the airfoil, a vapor cooling system, and a film cooling system for...
|
|
|
7575414 |
Turbine nozzle with trailing edge convection and film cooling
A hollow cooled airfoil includes an array of radially-spaced apart, longitudinally-extending partitions defining a plurality of cooling channels therebetween. A plurality of aft pins are disposed...
|
|
|
7572103 |
Component comprising a multiplicity of cooling passages
A component comprises a multiplicity of cooling passages arranged in two intersecting arrays to form a multiplicity of cooling passage intersections. Air jet interactions are generated at cooling...
|
|
|
7572102 |
Large tapered air cooled turbine blade
A large tapered air cooled turbine blade having a serpentine flow cooling circuit with a first leg located adjacent to a leading edge of the blade and a third leg at the trailing edge, where the...
|
|
|
7568887 |
Turbine blade with near wall spiral flow serpentine cooling circuit
A turbine blade for a gas turbine engine having a 5-pass serpentine flow cooling circuit with a first pressure side channel forming the first leg and being supplied with cooling air from an...
|
|
|
7568882 |
Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method
A localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shroud.
|
|
|
7563073 |
Turbine blade with film cooling slot
A film cooling slot arrangement for a turbine blade, in which the blade includes a suction side with an impact zone on which hot and heavy particles can strike to block film cooling holes. The...
|
|
|
7556476 |
Turbine airfoil with multiple near wall compartment cooling
The present invention is a turbine airfoil such as a rotor blade with a cooling circuit that provides convective cooling to the airfoil main body, and impingement cooling and film cooling to the...
|
|
|
7553534 |
Film cooled slotted wall and method of making the same
An article includes a substrate having a first surface and a second surface; a slot disposed in the second surface, the slot having a bottom surface substantially parallel to the second surface, a...
|
|
|
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...
|
|
|
7549844 |
Turbine airfoil cooling system with bifurcated and recessed trailing edge exhaust channels
A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel with bifurcated exhaust channels formed by suction and pressure side trailing edge cooling channels...
|
|
|
7549843 |
Turbine airfoil cooling system with axial flowing serpentine cooling chambers
A cooling system for a turbine airfoil of a turbine engine having suction and pressure side serpentine cooling channels formed between an internal support core and an outer wall of the turbine...
|
|
|
7547191 |
Turbine airfoil cooling system with perimeter cooling and rim cavity purge channels
A cooling system for a turbine airfoil of a turbine engine having a perimeter cooling channel formed from a portion of a serpentine cooling channel, an airfoil tip cooling channel, and a leading...
|
|
|
7547190 |
Turbine airfoil serpentine flow circuit with a built-in pressure regulator
An airfoil for used in a gas turbine engine, the airfoil having a serpentine cooling flow circuit formed within the airfoil to provide cooling for the leading edge and trailing edge of the airfoil....
|
|
|
7544044 |
Turbine airfoil with pedestal and turbulators cooling
A wall enclosing a hot gas path, the wall including a cooling cavity formed between an inner wall and an outer wall, and a plurality of pins extending between walls with a plurality of turbulators...
|
|
|
7540712 |
Turbine airfoil with showerhead cooling holes
A showerhead cooling arrangement for a turbine airfoil in which the showerhead includes a plurality of rows of diffusion slots arranged in an inverted V across a stagnation point of the airfoil. At...
|
|
|
7540083 |
Method to modify an airfoil internal cooling circuit
Methods are provided for modifying an airfoil internal cooling circuit that include a flow path configured to direct air through the airfoil in a direction and the airfoil having a leading edge, a...
|
|
|
7537431 |
Turbine blade tip with mini-serpentine cooling circuit
A turbine blade having a cooling supply passage formed within the blade, and a blade tip with a squealer tip formed thereon. The blade tip includes a blade top or cap, and includes a plurality of...
|
|
|
7534089 |
Turbine airfoil with near wall multi-serpentine cooling channels
A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may be positioned in an outer wall of the turbine airfoil and be formed...
|
|
|
7534088 |
Fluid injection system
In accordance with the present invention, there is provided a system for injecting a secondary fluid stream into a primary fluid stream with improved aerodynamic efficiency. The secondary fluid...
|
|
|
7534087 |
Turbomachine, in particular a gas turbine
The invention relates to a turbo-machine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbo-machine. The...
|
|
|
7530789 |
Turbine blade with a serpentine flow and impingement cooling circuit
A turbine blade with a film cooling holes arrangement to supply film cooling to hot sections on the pressure side and suction side of the blade. The cooling flow circuit for the blade uses a...
|
|
|
7530788 |
Hollow turbomachine blade
A hollow turbomachine blade including an internal cooling passage, an open cavity situated at the free end of the blade and defined by an end wall and the side wall of at least one rim which...
|
|
|
7527475 |
Turbine blade with a near-wall cooling circuit
An airfoil for a gas turbine engine, the airfoil including a cooling air passage to provide internal cooling for the airfoil. A supply passage is formed in the root of the airfoil to deliver...
|
|
|
7527474 |
Turbine airfoil with mini-serpentine cooling passages
An airfoil used in a gas turbine engine, especially a large rotor blade in an industrial gas turbine engine, the airfoil having at least one cooling air supply cavity formed by an inner wall of the...
|
|
|
7524168 |
Arrangement for the admission of cooling air to a rotating component, in particular for a moving blade in a rotary machine
An arrangement is disclosed for the admission of cooling air to the internal walls of a component rotating about a rotation axis, such as a moving blade in a rotary machine. A component root can be...
|
|
|
7520725 |
Turbine airfoil with near-wall leading edge multi-holes cooling
An air cooled airfoil used in a gas turbine engine includes a showerhead arrangement to cool the leading edge. A cooling supply cavity supplies cooling air to the airfoil, and is metered into an...
|
|
|
7520724 |
Cooled blade for a gas turbine
A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of...
|
|
|
7520723 |
Turbine airfoil cooling system with near wall vortex cooling chambers
A cooling system for a turbine airfoil of a turbine engine having a plurality of vortex cooling chambers positioned in an outer wall defining a suction side of the turbine airfoil. The vortex...
|
|
|
7520719 |
Method and apparatus for the cooling of the outer shrouds of the rotor blades of a gas turbine
Passive shroud cooling of rotor blades ( 5 ) is accomplished by a multitude of cooling-air flows introduced into the hot-gas flow upstream of the rotor blades on the outer circumference, these...
|
|
|
7513744 |
Microcircuit cooling and tip blowing
A turbine engine component has an airfoil portion having a pressure side, a suction side, a leading edge, a trailing edge, and a tip. The component further has a first cooling microcircuit embedded...
|
|
|
7513743 |
Turbine blade with wavy squealer tip rail
A turbine blade ( 10 ) including an airfoil ( 12 ), the airfoil ( 12 ) including an airfoil outer wall ( 16 ) having pressure and suction sidewalls ( 18, 20 ) joined together at chordally spaced...
|
|
|
7513739 |
Cooling circuits for a turbomachine moving blade
A moving blade for a turbomachine, the central portion of the blade including a pressure-side cooling circuit and a suction-side cooling circuit. The pressure-side circuit comprises at least first...
|
|
|
7513737 |
Gas turbine blade cooling circuit having a cavity with a high aspect ratio
A blade for a turbomachine gas turbine, the blade having a cooling circuit comprising at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade,...
|