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US20120070307 TURBINE BLADES, TURBINE ASSEMBLIES, AND METHODS OF MANUFACTURING TURBINE BLADES  
A turbine blade includes a first side wall including a first tip edge, a second side wall opposite the first side wall and including a second tip edge, a tip wall between the first and second side...
US20140165593 GAS TURBINE ENGINE TURBINE BLADE LEADING EDGE TIP TRENCH COOLING  
An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that...
US20130216395 GAS TURBINE BLADE  
A gas turbine blade including a root, an airfoil with a leading edge and a trailing edge, a radial outer tip, and a pressure side and a suction side between the leading edge and the trailing edge,...
US20130142668 COOLED TURBINE BLADE FOR GAS TURBINE ENGINE  
A cooled turbine blade for a gas turbine engine including a pressure surface wall, a suction surface wall and a distal wall connecting the pressure surface wall and the suction surface wall,...
US20150104326 TURBINE ROTOR BLADES WITH IMPROVED TIP PORTION COOLING HOLES  
A turbine rotor blade is provided for a turbine section of an engine. The turbine rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the...
US20150184538 INTERIOR COOLING CIRCUITS IN TURBINE BLADES  
An airfoil of a turbine rotor blade that includes a cooling configuration having a plurality of elongated flow passages for receiving and directing a coolant along a path through the airfoil. The...
US20140093390 COOLED TURBINE BLADE WITH LEADING EDGE FLOW REDIRECTION AND DIFFUSION  
A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning...
US20150104327 TURBINE ROTOR BLADES WITH TIP PORTION PARAPET WALL CAVITIES  
In accordance with an exemplary embodiment, a turbine rotor blade is provided for a turbine section of an engine. The turbine rotor blade includes a platform and an airfoil extending from the...
US20140227103 TURBINE BLADE WITH CONTOURED CHAMFERED SQUEALER TIP  
A squealer tip formed from a pressure side tip wall and a suction side tip wall extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side tip walls may...
US20140093389 COOLED TURBINE AIRFOIL STRUCTURES  
In accordance with an exemplary embodiment, disclosed is an air-cooled turbine blade having an airfoil shape, including a convex suction side wall, a concave pressure side wall, the walls...
US20140093388 COOLED TURBINE BLADE WITH LEADING EDGE FLOW DEFLECTION AND DIVISION  
A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning...
US20150078916 TURBINE BLADES WITH TIP PORTIONS HAVING CONVERGING COOLING HOLES  
A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the...
US20120269650 TURBINE WHEEL FOR A TURBINE ENGINE  
A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the...
US20140083116 GAS TURBINE ENGINE COMPONENTS WITH BLADE TIP COOLING  
A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine...
US20110038710 Application of Dense Vertically Cracked and Porous Thermal Barrier Coating to a Gas Turbine Component  
A configuration for coating a turbine component such as a blade or vane with various forms of thermal barrier coating to provide enhanced temperature capability and increased strain tolerance is...
US20110020137 Spar and shell constructed turbine blade  
A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to...
US20150004001 TURBINE BLADE  
A turbine vane for a rotary turbomachine is described having a turbine blade which is delimited by a concave pressure-side wall and a convex suction-side wall which are connected in the region of...
US20140255208 Gas Turbine Blade  
The gas turbine blade includes a cooling channel formed therein, and a partition disposed on its tip side for isolating the cooling channel from the outside. The partition is integrally formed...
US20110027103 IMPELLER WHICH INCLUDES IMPROVED MEANS OF COOLING  
Impeller for turbine engine which includes a disk provided with blade retention teeth, wherein associated with each tooth there are means for channelling a flow of cooling air which covers the...
US20140047842 SUCTION SIDE TURBINE BLADE TIP COOLING  
An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial...
US20140023517 NOZZLE FOR TURBINE SYSTEM  
A nozzle for a turbine system is disclosed. The nozzle includes an airfoil, an inner sidewall, and an outer sidewall. The airfoil includes exterior surface defining a pressure side and a suction...
US20150082808 GAS TURBINE ENGINES WITH TURBINE AIRFOIL COOLING  
An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a...
US20150125310 Gas Turbine Airfoil  
A gas turbine airfoil is provided that is superior in the cooling performance of an end wall and in the thermal efficiency of a gas turbine. A gas turbine airfoil includes an airfoil portion...
US20140271228 TURBINE BLADE  
A turbine blade has hollowness, and is provided with a back-side wall of which a portion of the inner wall surface is exposed at the rear edge portion, with cooling air flown along the inner wall...
US20130064680 TURBINE ENDWALL WITH GROOVED RECESS CAVITY  
A vane assembly for a gas turbine engine including an endwall and an airfoil extending from the endwall. An inner rail extends radially inwardly of the endwall, and an overhang portion extends...
US20150152734 TURBINE AIRFOIL WITH LOCAL WALL THICKNESS CONTROL  
A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure...
US20130039760 OIL MIST SEPARATION IN GAS TURBINE ENGINES  
A rotor stage is provided which comprises a shank passage for separating liquid from secondary air system (SAS) air. The shank passage is formed between a radially outer surface of a disc post, a...
US20150167493 TURBINE BUCKET AND METHOD FOR COOLING A TURBINE BUCKET OF A GAS TURBINE ENGINE  
The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include a platform, an airfoil extending radially outward from the...
US20130142666 TURBINE BLADE INCORPORATING TRAILING EDGE COOLING DESIGN  
A turbine blade (10) including an airfoil (12) having multiple interior wall portions (70) each separating at least one chamber from another one of multiple chambers (46, 48, 50, 58, 60). In one...
US20150167475 AIRFOIL OF GAS TURBINE ENGINE  
An airfoil of gas turbine engine is provided, which can improve cooling efficiency at a leading edge of the airfoil even when a location of combustion gas stagnation changes, without having to...
US20120328450 COOLING SYSTEM FOR TURBINE AIRFOIL INCLUDING ICE-CREAM-CONE-SHAPED PEDESTALS  
A turbine airfoil comprises a wall portion, a cooling channel, a plurality of trip strips and a plurality of pedestals. The wall portion comprises a leading edge, a trailing edge, a pressure side...
US20130302176 TURBINE AIRFOIL TRAILING EDGE COOLING SLOT  
A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in pressure sidewall end at a trailing edge...
US20130230407 Turbine Bucket with a Core Cavity Having a Contoured Turn  
The present application thus provides a turbine bucket. The turbine bucket may include a platform, an airfoil extending from the platform at an intersection thereof, and a core cavity extending...
US20120020787 COOLED BLADE FOR A GAS TURBINE  
A cooled blade for a gas turbine includes a blade airfoil extending between leading and trailing edges in a flow direction and on suction and pressure sides is delimited by a wall, which include...
US20140037459 AIRFOIL DESIGN HAVING LOCALIZED SUCTION SIDE CURVATURES  
An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side...
US20120114480 SYSTEM AND METHOD FOR COOLING A TURBINE BUCKET  
A turbine bucket includes an airfoil, a platform adjacent to the airfoil, and a shank adjacent to the platform. The shank defines a shank cavity, and a divider in the shank cavity creates a...
US20120014808 NEAR-WALL SERPENTINE COOLED TURBINE AIRFOIL  
A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters...
US20120014810 TURBINE VANE WITH DUSTING HOLE AT THE BASE OF THE BLADE  
A cooled turbine vane for a turbine engine, that includes a blade mounted on a platform carried by a base, the blade including one or more cavities formed therein for cooling air circulation, the...
US20140286790 Dust Mitigation for Turbine Blade Tip Turns  
A dust mitigation system for airfoils includes a plurality of contoured tip turns which curve about at least two axes. This inhibits recirculation areas common within airfoils and further inhibits...
US20140186190 TIP LEAKAGE FLOW DIRECTIONALITY CONTROL  
An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil...
US20140056717 GAS TURBINE ENGINE AIRFOIL INTERNAL COOLING FEATURES  
An airfoil for a gas turbine engine includes spaced apart pressure and suction walls joined at leading and trailing edges to provide an airfoil. Intermediate walls interconnect the pressure and...
US20150044059 AIRFOIL FOR A TURBINE SYSTEM  
An airfoil includes a main portion formed of a base material. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising at...
US20130156603 AEROFOIL BLADE OR VANE  
An aerofoil blade or vane for the turbine of a gas turbine engine is provided. The blade or vane includes an aerofoil portion which, in use, extends radially across a working gas annulus of the...
US20110164960 HEAT TRANSFER ENHANCEMENT IN INTERNAL CAVITIES OF TURBINE ENGINE AIRFOILS  
An airfoil includes a leading edge, a trailing edge, a suction side and a pressure side; a plurality of internal cooling cavities extending radially within the airfoil, one of the plurality of...
US20130302179 TURBINE AIRFOIL TRAILING EDGE COOLING HOLE PLUG AND SLOT  
A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes disposed in pressure sidewall. All or a...
US20090202357 COOLED PUSHER PROPELLER SYSTEM  
A propulsion system and method includes an annular exhaust nozzle about an axis radially outboard of the annular cooling flow nozzle and ejecting an exhaust flow through an annular exhaust nozzle...
US20120269648 SERPENTINE COOLING CIRCUIT WITH T-SHAPED PARTITIONS IN A TURBINE AIRFOIL  
A serpentine cooling circuit (AFT) in a turbine airfoil (34A) starting from a radial feed channel (C1), and progressing axially (65) in alternating tangential directions through interconnected...
US20130302177 TURBINE AIRFOIL TRAILING EDGE BIFURCATED COOLING HOLES  
A gas turbine engine turbine airfoil having pressure and suction sidewalls extending outwardly along a span and chordwise between opposite leading and trailing edges. A spanwise row of spaced...
US20140093391 COOLED TURBINE BLADE WITH TRAILING EDGE FLOW METERING  
A cooled turbine blade having a base and an airfoil, the base including cooling air inlet and an internal cooling air passageway, and the airfoil including an internal heat exchange path beginning...
US20120163994 GAS TURBINE ENGINE AND AIRFOIL  
One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique turbine engine airfoil. Other embodiments include apparatuses, systems, devices, hardware,...