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Match Document Document Title
8182205 Gas turbine engine with insulated cooling circuit  
A gas turbine engine is provided comprising a compressor with an insulated cooling circuit. The compressor comprises a compressor casing having a compression chamber and at least one stator and at...
8172520 Turbine vane of a gas turbine  
A turbine vane of a gas turbine, especially a gas turbine aircraft engine, is disclosed. The turbine vane includes a vane base body with an outer surface forming a suction side and a pressure side,...
8172507 Gas turbine blade with double impingement cooled single suction side tip rail  
A turbine blade is provided comprising: an airfoil including an airfoil outer wall extending radially outwardly from a blade root, a squealer tip section located at an end of the airfoil distal...
8152436 Blade under platform pocket cooling  
Inlets are provided at a front end of inter-blade cavities for allowing coolant to flow therein to cool down the undersurface of the blade platforms as well as the rim of the disc of a rotor assembly.
8127553 Zero-cross-flow impingement via an array of differing length, extended ports  
A jet impingement array design and method are disclosed for efficiently cooling the liner of a gas turbine combustion chamber, while eliminating almost all effects of coolant gas crossflow. The...
8109724 Recessed metering standoffs for airfoil baffle  
An internally cooled airfoil comprises an airfoil body, a baffle and a plurality of standoffs. The airfoil body is shaped to form leading and trailing edges, and pressure and suction sides...
8109712 Method of producing a turbine or compressor component, and turbine or compressor component  
Disclosed is a turbine or compressor component with an integrated cooling channel, in particular a turbine blade, and a method for producing the same. The cooling channel of the component is...
8105030 Cooled airfoils and gas turbine engine systems involving such airfoils  
Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a...
8100653 Gas-turbine blade featuring a modular design  
A gas-turbine blade has a root 5 and an airfoil 2, with the airfoil 2 including an internal load carrier 6 as well as an airfoil element 8 enclosing the internal load carrier 6 by forming a cavity...
8096751 Turbine engine component with cooling passages  
A component for use in a turbine engine including a first member and a second member associated with the first member. The second member includes a plurality of connecting elements extending...
8092179 Blade tip cooling groove  
An example turbine blade includes a blade having an airfoil profile extending radially toward a blade tip. A shelf is established in the blade tip. A sealing portion of the blade tip extends...
8092175 Turbine blade  
The invention relates to a turbine blade comprising a profiled vane around which working gas flows. The working gas cross-flows a front edge of the vane and flows away on a rear edge of the vane....
8083486 Turbine blade with cooling flow modulation  
A turbine rotor blade with a 3-pass serpentine flow cooling channel having a first leg located at the leading edge of the airfoil and a third leg located adjacent to the trailing edge of the...
8070440 Cooling channel formed in a wall  
A wall element having at least one cooling channel formed therein, the wall element presenting an inside surface and an outside surface, the channel comprising a hole and a diffusion portion, the...
8070436 Cooling airflow modulation  
A gas turbine engine airfoil (22) has a wall (42) provided with a cooling effusion hole (40) therein to facilitate film cooling of the external surface (52) of the wall (42). A member (46) attached...
8066485 Turbine blade with tip section cooling  
A turbine rotor blade with a single tip rail on the suction side of the blade tip, and in which the pressure side tip edge includes a row of trench film slots that each having side walls that are...
8066482 Shaped cooling holes for reduced stress  
A gas turbine engine component having shaped cooling holes that further enhances the cooling of a desired region while reducing stress levels in and around the cooling holes is disclosed. The...
8057182 Metered cooling slots for turbine blades  
A metered cooling slot disposed in a wall comprising an outer surface that is exposed to a hot gas stream and an inner surface that defines an internal coolant chamber through which a coolant...
8047786 Apparatus for plugging turbine wheel holes  
A turbine wheel hole plug that includes: 1) an approximate cylindrical body, the cylindrical body sized such that the cylindrical body fits snugly into a turbine wheel hole; 2) a first flange at a...
8049147 Engine inlet ice protection system with power control by zone  
A system includes a first heater located at the leading edge of a gas turbine structural member, a second heater located aft of the first heater, and a third heater located aft of the second...
8038399 Turbine rim cavity sealing  
A rim cavity seal arrangement for a gas turbine engine, where the rim cavity is formed between two rotor disk stages with a stator vane assembly positioned between the rotor disks and extending...
8033789 Apparatus for preventing ice accretion  
Aerofoils (22) of a gas turbine engine are provided with a coating (34) or filler (44) of viscoelastic material. As ice accretes on the aerofoils (22) during operation, the resulting aerodynamic...
7993102 Rotor cooling circuit  
A cooling circuit serves to provide cooling air in a rotor having a compressor rotor and a turbine rotor. The cooling circuit includes a first cooling path through the compressor rotor in series...
7926763 Ice management system for rotary-wing aircraft  
An ice management system is configured for an aircraft having at least one rotor (11), each rotor having a plurality of blades. The system has an alternating current (AC) electrical power supply...
7896616 Integrated leading edge for wind turbine blade  
A wind turbine blade that includes integrated erosion, lightning and icing protection for a leading edge. The leading edge includes a frontal surface with an erosion shield positioned external to...
7828514 Rotor for an engine  
A rotor (10) for a power plant, in particular an aero engine or a gas turbine, whereby the rotor (10) includes at least two bonded rotor discs (12, 14). The rotor (10) has an inlet opening (30) for...
7789620 Heater assembly for deicing and/or anti-icing a component  
A heater assembly for deicing and/or anti-icing a component includes a metallic heating element adjacent to a densely woven fabric layer impregnated with a resin that is capable of withstanding...
7758309 Vane wheel of turbine comprising a vane and at least one cooling channel  
There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the...
7748211 Vapor cooling of detonation engines  
An engine cooling system includes a combustion chamber assembly configured to generate detonation waves and a first vapor cooling assembly. The combustion chamber assembly defines a flowpath...
7748946 Cooling system and method for wind turbine components  
A cooling system and method is provided for a wind turbine. The cooling system is used to cool at least one component in the wind turbine, and includes a filter system having at least one primary...
7717675 Turbine airfoil with a near wall mini serpentine cooling circuit  
A stator vane for use in a gas turbine engine, the vane having a plurality of near wall mini serpentine flow cooling modules arranged in an array on the airfoil walls. Each module includes a series...
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,...
7581927 Serpentine microcircuit cooling with pressure side features  
In accordance with the present invention, there is provided a turbine engine component having an airfoil portion with a pressure side and a suction side, a first microcircuit embedded in a wall...
7578655 Composite gas turbine fan blade  
A composite turbine blade and fan blade assembly for use in a turbo machine such as a gas turbine engine. The turbine blade assembly includes a plurality of metallic turbine blades secured to a...
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...
7549845 Gas turbine having a sealing structure  
In a gas turbine, annular overhang portions are formed on adjacent surfaces of a plurality of rotor discs so as to face each other, surrounding the rotor axis, groove portions are provided...
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...
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...
7476078 Rotor with core surrounded by shielding rings  
A rotor of a thermally loaded turbomachine, in particular of a compressor or a gas turbine, is mounted such that it can rotate about a rotor axis and is concentrically surrounded by a hot-gas duct...
7429166 Methods and apparatus for gas turbine engines  
A method for manufacturing a turbine engine component includes forming a component to include a first side and an opposite second side, positioning at least one capillary adjacent to an external...
7430119 Impeller and aligned cold plate  
According to some embodiments, an apparatus may comprise a cold plate comprising a plurality of fins and an impeller comprising a plurality of blades. An output fluid velocity angle defined by the...
7390167 Compressor with centripetal air takeoff  
A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the...
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...
7334412 Cooling air and injected liquid system for gas turbine blades  
The invention relates to a turbine 1, in particular a gas turbine, which along a swivel-mounted rotationally symmetrical rotor 2 has a compressor 3, a combustion chamber 5 and a turbine section 7...
7282274 Integral composite structural material  
The present invention is an integral composite structural (ICS) material comprising an open metal structure having at least one external side and internal surfaces defining a plurality of open...
7258526 Eddy current heating for reducing transient thermal stresses in a rotor of a gas turbine engine  
The device and method are used for heating a central section of a rotor mounted for rotation in a gas turbine engine.
7217091 Methods and apparatus for deicing airfoils or rotor blades  
A method for deicing a rotor blade having a blade root, a blade tip, and a leading edge in which the rotor blade is operably coupled to a hub of a turbine includes circulating heated air through an...
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). The...
RE39479 Durable turbine nozzle  
A turbine nozzle includes a plurality of vanes joined at opposite ends to outer and inner bands. The inner band has a forward hook which is segmented to reduce thermal mismatch. And, in additional...
RE39320 Thermal barrier coating wrap for turbine airfoil  
An airfoil having extended life due to reduction in stresses. The stresses are reduced by extending the thermal barrier coating below the radius between the outer band perimeter and the inner flow...
Matches 1 - 50 out of 436 1 2 3 4 5 6 7 8 9 >