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7377746 |
Airfoil cooling circuits and method
An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a...
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7377743 |
Countercooled turbine nozzle
A turbine nozzle includes a mid vane mounted between a pair of end vanes in outer and inner bands. The mid vane includes a first pattern of film cooling holes configured to discharge more cooling...
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7374401 |
Bell-shaped fan cooling holes for turbine airfoil
A turbine airfoil a plurality of cooling holes formed in the external surface of the airfoil in fluid communication with a cooling circuit. The cooling holes have a metering section and a diffuser...
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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...
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7371048 |
Turbine blade trailing edge construction
A turbine blade system for a gas turbine engine includes a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to...
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7364405 |
Microcircuit cooling for vanes
A turbine engine component has an airfoil portion with a suction side. The component includes a cooling microcircuit embedded within a wall structure forming the suction side. The cooling...
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7357623 |
Angled cooling divider wall in blade attachment
A rotor blade of a gas turbine engine includes a blade root defining a cooling airflow entry cavity therein, in fluid communication with internal cooling air passages through the blade. The cavity...
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7351036 |
Turbine airfoil cooling system with elbowed, diffusion film cooling hole
A cooling system for a turbine airfoil of a turbine engine having an elbowed film cooling hole positioned in an outer wall defining the turbine airfoil. The elbowed film cooling hole may include a...
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7351035 |
Hollow rotor blade for the turbine of a gas turbine engine, the blade being fitted with a “bathtub”
A hollow blade has an internal cooling passage, an open cavity situated at the free end of the blade and defined by an end wall extending over the entire end of the blade and by a rim. The blade...
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7347671 |
Turbine blade turbulator cooling design
A turbine blade ( 10 ) includes internal channels ( 16 ) which provide a flow passage for a cooling medium to assist in cooling the blade ( 10 ) when in use, wherein the channels ( 16 ) include a...
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7344354 |
Methods and apparatus for operating gas turbine engines
A method of assembling a gas turbine engine that includes providing a rotor assembly including a rotor shaft, an air duct, and a rotor disk that includes a mounting arm, wherein the mounting arm...
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7341429 |
Methods and apparatuses for cooling gas turbine engine rotor assemblies
A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine...
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7334991 |
Turbine blade tip cooling system
A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one elongated tip cooling chamber for passing cooling fluids in close proximity to an outer...
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7334992 |
Turbine blade cooling system
A turbine blade cooling system for a gas turbine engine includes a turbine blade having a trailing edge, a concave side, and a convex side. The trailing edge defines at least one set of impingement...
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7334993 |
Gas turbine rotor blade, gas turbine using the rotor blade, and power plant using the gas turbine
A gas turbine rotor blade capable of effectively reducing creep damage by forming a cooling through hole to cool a target area in which significant creep damage of a shroud cover is predicted based...
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7326031 |
Access port for dirt removal for gas turbine engine
A gas turbine engine is provided with a dirt separator placed in a path of the radially outer cooling air flow, and includes a radially outer leg that defines a space to capture dirt or other...
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7322795 |
Firm cooling method and hole manufacture
A cooled cast part has an exterior surface. A cooling passageway system extends from at least one inlet port to a plurality of outlet ports. The passageway system includes a first passageway to at...
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7322789 |
Methods and apparatus for channeling steam flow to turbines
Method and apparatus for assembling a double flow steam turbine is provided. The method comprises providing an annular member having a first end, a second end, and a body extending therebetween,...
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7320575 |
Methods and apparatus for aerodynamically self-enhancing rotor blades
An airfoil having a root, a tip, and an outer surface for pressuring air flowable thereover. The outer surface includes one or more slots elongate in a direction selected to preclude or reduce...
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7316539 |
Vane assembly with metal trailing edge segment
Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane...
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7311498 |
Microcircuit cooling for blades
A turbine engine component such as a turbine blade includes an airfoil portion formed by a suction side wall and a pressure side wall, and a cooling microcircuit incorporated in at least one of the...
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7303376 |
Turbine airfoil with outer wall cooling system and inner mid-chord hot gas receiving cavity
A turbine airfoil usable in a turbine engine and having at least one cooling system. The cooling system may be positioned in an outer wall of the turbine airfoil, and the airfoil may include a hot...
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7303375 |
Refractory metal core cooling technologies for curved leading edge slots
A turbine engine component has an airfoil portion with a leading edge portion. The leading edge portion includes a plurality of staggered holes for causing fluid to flow over a surface of the...
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7300251 |
Turbine cooling vane of gas turbine engine
A cooled blade of a small gas turbine engine can enhance cooling performance without increasing the amount of cooling air in a simple configuration. A cooled turbine blade is provided with a...
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7300250 |
Cooled airfoil trailing edge tip exit
A gas turbine engine airfoil comprises first and second opposite sides joined together at spaced-apart leading and trailing edges and extending from a root to a tip. An internal cooling passage is...
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7300252 |
Gas turbine airfoil leading edge cooling construction
A gas turbine airfoil with a pressure sidewall ( 6 ) and a suction sidewall ( 7 ) extends from a root ( 2 ) to a tip ( 3 ) and from a leading edge ( 4 ) to a trailing edge ( 5 ). It comprises...
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7296972 |
Turbine airfoil with counter-flow serpentine channels
A turbine airfoil usable in a turbine engine and having at least one cooling system. The cooling system may include a pressure side serpentine cooling channel and a suction side serpentine cooling...
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7296967 |
Counterflow film cooled wall
A turbine wall includes opposite back and front sides. Film cooling holes are inclined longitudinally through the wall. Adjacent holes are spaced laterally apart and are inclined oppositely for...
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7296973 |
Parallel serpentine cooled blade
A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality...
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7293961 |
Zigzag cooled turbine airfoil
A turbine airfoil includes pressure and suction sidewalls spaced apart to define flow channels extending in span and separated by ribs. Side channels are disposed along one sidewall and spaced from...
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7293962 |
Cooled turbine blade or vane
A turbine blade or vane ( 1 ) has a shell ( 2 ), including a first side wall ( 8 ) and a second side wall ( 9 ), which are connected together at a leading edge ( 10 ) and at a trailing edge ( 11 ),...
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7287959 |
Blunt tip turbine blade
A turbine airfoil includes opposite pressure and suction sidewalls, and extends in chord between opposite leading and trailing edges and in span from a root to an outer tip cap. The tip cap bridges...
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7281895 |
Cooling system for a turbine vane
A turbine vane usable in a turbine engine and having at least one cooling system. The cooling system may include at least one convergent flow channel for receiving air from a shroud assembly. The...
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7278828 |
Repair method for plenum cover in a gas turbine engine
A gas turbine engine plenum cover is repaired using a prefabricated repair cover SPAD. The SPAD repair cover has a spoolie boss that is aligned and attached to the body of the repair plenum cover...
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7278827 |
Cooling air evacuation slots of turbine blades
A turbine blade of a turbomachine, having at least a bottom platform connected to the base of the blade by a bottom connection zone, and a cooling circuit consisting of at least one cooling cavity,...
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7278826 |
Airfoil cooling passage trailing edge flow restriction
An internal metering structure permits the exit apertures of a cooled airfoil to be sized to provide for easy manufacturability.
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7273351 |
Component having a film cooling arrangement
A component such as a turbine blade of a gas turbine engine includes a film cooling arrangement which is optimized by a process in which a component is manufactured having a film cooling...
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7273347 |
Blade for a gas turbine
A gas turbine blade ( 1 ) has a shroud ( 3 ) which is cooled by different cooling mechanisms in various regions (A, B, C) according to the different thermal load. In a first region (A), in a fin (...
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7273350 |
Heat transfer arrangement
A heat transfer arrangement comprises a target member ( 28 or 30 ), and an impingement member ( 32 ). The impingement member ( 32 ) defines a fluid path ( 38 or 40 ) there through to direct...
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7270514 |
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...
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7270515 |
Turbine airfoil trailing edge cooling system with segmented impingement ribs
A cooling system for a turbine airfoil of a turbine engine having multiple segmented ribs aligned together spanwise within a trailing edge cooling channel. The segmented ribs may be positioned...
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7264445 |
Cooled blade or vane for a gas turbine
A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as,...
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7264444 |
Aerofoils
An aerofoil has a body, and at least one flow control device, the flow control device including a passage within the body of the aerofoil, and a passage outlet at an upper aerofoil surface of the...
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7255536 |
Turbine airfoil platform cooling circuit
An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit...
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7255534 |
Gas turbine vane with integral cooling system
A turbine vane usable in a turbine engine and having at least one cooling system. The cooling system includes three diffusors in an outer wall of the vane for reducing the velocity of the cooling...
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7255535 |
Cooling systems for stacked laminate CMC vane
Embodiments of the invention relate to various cooling systems for a turbine vane made of stacked ceramic matrix composite (CMC) laminates. Each airfoil-shaped laminate has an in-plane direction...
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7249933 |
Funnel fillet turbine stage
A turbine stage includes a row of airfoils and their platforms spaced laterally apart to define flow passages therebetween. Each airfoil is integrally joined to its platform at a funnel-shaped...
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7249934 |
Pattern cooled turbine airfoil
A hollow turbine airfoil includes pressure and suction sidewalls extending in span between a root and tip and extending in chord between opposite leading and trailing edges. The pressure sidewall...
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7246999 |
Stepped outlet turbine airfoil
A turbine airfoil includes an internal cooling circuit between opposite pressure and suction sidewalls. The pressure sidewall includes a row of outlet slots for the circuit separated by converging...
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7246992 |
High efficiency fan cooling holes for turbine airfoil
A turbine airfoil includes a leading edge and an axially spaced-part trailing edge, the leading edge having an axially-extending external surface curvature. A cooling circuit in the airfoil...
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