Matches 301 - 350 out of 997 < 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 >
Match Document Document Title
6773231 Turbine blade core cooling apparatus and method of fabrication  
The present invention provides a cooling apparatus for cooling a turbine blade. The cooling apparatus comprises a pressure side plate comprising a plurality of pressure ribs, a suction side plate...
6773230 Air cooled aerofoil  
An air cooled component with an internal air cooling system comprising an internal cavity which is divided into at least two compartments. The compartments are arranged in flow sequence by...
6769866 Turbine blade and method for producing a turbine blade  
A turbine blade extends along a major axis from a root region via a blade leaf region capable of being acted upon by hot gas to a head region. The turbine blade is formed essentially from...
6769875 Cooling system for a turbine blade  
The invention relates to a blade ( 13; 14 ) for a turbine ( 10 ), comprising at least one channel ( 22 ) which is delimited by walls ( 19, 20, 21 ). An insert ( 25 ) which can be subjected to the...
6769878 Turbine blade airfoil  
A turbine blade including an airfoil having a profile in accordance with Table 1 is disclosed. The turbine blade has a plurality of cooling passages extending radially outward through the airfoil....
6761535 Internal core profile for a turbine bucket  
Second stage turbine buckets have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z...
6761956 Ventilated thermal barrier coating  
A gas turbine engine component includes a perforate metal wall having pores extending therethrough. The wall has a first surface covered by a thermal barrier coating. The pores have first ends...
6761534 Cooling circuit for a gas turbine bucket and tip shroud  
An open cooling circuit for a gas turbine airfoil and associated tip shroud includes a first group of cooling holes internal to the airfoil and extending in a radially outward direction generally...
6758651 Gas turbine  
A gas turbine wherein cooling failure attributable to the occurrence of a horseshoe vortex produced in the vicinity of the stationary blades of the turbine is preventable, the gas turbine including...
6749400 Gas turbine engine disk rim with axially cutback and circumferentially skewed cooling air slots  
A gas turbine engine rotor disk assembly includes a disk having an annular hub circumscribed about a centerline. An annular web extends radially outwardly from the hub to an annular rim. A...
6749395 Device and method for controlling a cooling air flow of a gas turbine  
An apparatus for controlling a cooling air flow, in particular a gas turbine cooling air flow, is for the control, specific to requirement, of a cooling air flow using low-maintenance. A control...
6749396 Failsafe film cooled wall  
A flowpath wall is provided for bounding hot combustion gases in a gas turbine engine. The wall includes opposite outer and inner surfaces and a plurality of cooling holes extending therebetween. A...
6746209 Methods and apparatus for cooling gas turbine engine nozzle assemblies  
A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a...
6733232 Extended tip turbine blade for heavy duty industrial gas turbine  
An improved turbine blade having a tip configured to provide a reduced blade tip clearance between the blade tip and the inside of a turbine casing and to provide an improved flow path for the...
6733229 Insert metering plates for gas turbine nozzles  
The invention comprises a metering plate which is assembled to an impingement insert for use in the nozzle of a gas turbine. The metering plate can have one or more metering holes and is used to...
6726444 Hybrid high temperature articles and method of making  
An article for use in a hot gas path of a gas turbine assembly, a metallic skin for such an article, and a method for making such an article are presented with, for example, the article comprising...
6719529 Gas turbine blade and method for producing a gas turbine blade  
A gas turbine blade includes an inlet edge region of a platform. Eroded into it is a slot which runs parallel to the flow-on edge and into which cooling air is introduced in an impact-cooled manner...
6715988 Turbine airfoil for gas turbine engine  
A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The...
6709230 Ceramic matrix composite gas turbine vane  
A hybrid vane ( 50 ) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member ( 52 ) bonded to a substantially solid core member ( 54 ). The airfoil member and core member...
6709237 Turbine blade or vane and process for producing a turbine blade or vane  
The present invention relates to a turbine blade or vane ( 13; 14 ), in particular for a gas turbine ( 10 ), which has at least one chamber ( 18; 29; 20; 21 ) which can be acted on by a cooling...
6705831 Linked, manufacturable, non-plugging microcircuits  
A linked microcircuit for providing coolant gas flow through an aircraft part, comprising at least one inlet through which a coolant gas may enter, a circuit channel extending from the at least one...
6705836 Gas turbine blade cooling circuits  
A gas turbine blade for an airplane engine, the blade comprising at least a first cooling circuit comprising at least a concave side cavity extending radially beside the concave face of the blade,...
6676370 Shaped part for forming a guide ring  
A shaped part ( 30 ) for forming a guide ring ( 21 ) for a gas turbine ( 1 ) is, on the one hand, to be produced with particularly little outlay and, on the other hand, is to be designed so that it...
6672836 Coolable rotor blade for an industrial gas turbine engine  
A coolable rotor blade having an airfoil having two serpentine passages is disclosed. Various construction details are developed for providing cooling to the leading edge region and the trailing...
6672829 Turbine blade having angled squealer tip  
A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further...
6663346 Compressor stator inner diameter platform bleed system  
The present invention relates to a bleed system for use in a gas turbine engine. The bleed system comprises a plurality of blades with each of the blades having an airfoil member and a platform...
6652235 Method and apparatus for reducing turbine blade tip region temperatures  
A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a...
6644921 Cooling passages and methods of fabrication  
A turbine portion, for example a turbine blade, for exposure in a hot fluid flow includes at least one internal cooling passage disposed therein. A cooling fluid is introduced within the cooling...
6644920 Method for providing a curved cooling channel in a gas turbine component as well as coolable blade for a gas turbine component  
A method of forming a curved cooling channel into a gas turbine component such as a turbine blade uses an electrode in the form of a helix. The electrode is driven to rotate around the central...
6641360 Device and method for cooling a platform of a turbine blade  
Described is a device and a method for cooling a platform of a turbine blade comprising a blade root, a vane with a leading and trailing edge, as well as a blade tip with a platform, through which...
6641362 Component that can be subjected to hot gas, especially in a turbine blade  
A component can be subjected to hot gas. At least one duct is provided which can be subjected to a cooling fluid. The duct is bounded by two first walls opposite to one another. The walls include...
6634858 Gas turbine airfoil  
An airfoil includes internal cooling air passages arranged in a serpentine manner with one or more radially outward and radially inward extending passages. The passages are in fluid connection...
6634859 Apparatus and process for impingement cooling of a component exposed to heat in a flow power machine  
An apparatus and a process are provided for impingement cooling of a component exposed to heat in a flow machine. The component includes a wall section on at least one side of which at least one...
6629817 System and method for airfoil film cooling  
An airfoil for a gas turbine engine including an inflection that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The...
6617003 Directly cooled thermal barrier coating system  
An actively cooled TBC bond coat wherein active convection cooling is provided through micro channels inside or adjacent to a bond coat layer applied to a substrate. The micro channels communicate...
6616406 Airfoil trailing edge cooling construction  
An airfoil in a gas turbine comprises an improved cooling construction at its trailing edge providing impingement as well as enhanced film cooling. The airfoil comprises cavities arranged between...
6616405 Cooling structure for a gas turbine  
In a cooling structure for a gas turbine, cooling air diffusion holes are formed from inner surface to outer surface of a platform so as to open from high pressure side blade surface of a moving...
6616407 Gas turbine engine guide vane  
An air cooled guide vane ( 20 ) is provided with a stack of ducts ( 40 ) each of which converges towards its outlet end. Air flow turbulators ( 42 ) are positioned in ducts ( 40 ) and pressure...
6612811 Airfoil for a turbine nozzle of a gas turbine engine and method of making same  
An airfoil for a turbine nozzle assembly of a gas turbine engine includes an outer side wall, an inner side wall, a leading edge extending from the outer side wall to the inner side wall, a...
6609884 Cooling of gas turbine engine aerofoils  
An aerofoil ( 39 ) for a gas turbine engine ( 10 ) includes one or more internal cooling passage ( 74,76 ) for receiving a flow of cooling fluid, and means ( 84,86,88,90 ) for inducing at least two...
6607355 Turbine airfoil with enhanced heat transfer  
A turbine airfoil section having an internal cavity and a plurality of indentations on the inner surface of the internal cavity is described. The indentations provide enhanced heat transfer for...
6607356 Crossover cooled airfoil trailing edge  
A turbine airfoil includes pressure and suction sidewalls having first and second flow channels disposed therebetween and separated by a longitudinally extending bridge. The bridge includes a row...
6602053 Cooling structure and method of manufacturing the same  
A method of forming a cooling feature ( 28 ) on a surface ( 14 ) of a substrate ( 12 ) to protect the substrate from a high temperature environment. The cooling feature is formed by first...
6602052 Airfoil tip squealer cooling construction  
An airfoil for a gas turbine includes a pressure sidewall and a suction sidewall, a tip cap, and a tip squealer. Cooling fluid flows from a hollow space within the airfoil through exit passages...
6599092 Methods and apparatus for cooling gas turbine nozzles  
A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a...
6595748 Trichannel airfoil leading edge cooling  
A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in front of a pair of side channels. The leading edge channel receives coolant from the...
6595749 Turbine airfoil and method for manufacture and repair thereof  
An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip defining a tip shelf, and an integral tip cap between the airfoil...
6595750 Component of a flow machine  
The present invention relates to a component of a flow machine, particularly a turbine blade, which has a cooling channel ( 9, 10 ) through which cooling medium can flow, with at least one...
6582194 Gas-turbine blade and method of manufacturing a gas-turbine blade  
The invention relates to a method of manufacturing a gas-trubine blade and to a turbine blade. First, a hollow, supporting metal blade body is made, in particular by casting, with a multiplicity...
6582584 Method for enhancing heat transfer inside a turbulated cooling passage  
A method of enhancing heat transfer and cooling efficiency in a cooling passage includes forming a plurality of turbulator rings in the passage, the rings projecting inwardly, substantially...
Matches 301 - 350 out of 997 < 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 >