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| Number | Title | Issue Date |
| 8182224 | Turbine blade having a row of spanwise nearwall serpentine cooling circuits A turbine blade with an array of cells arranged along the pressure side and suction side of the airfoil to provide near wall cooling to a thin thermal skin that forms the airfoil surface of the airfoil. The blade includes a main spar that forms the support for the t... | 05/22/2012 |
| 8167559 | Turbine vane for a gas turbine engine having serpentine cooling channels within the outer wall A turbine vane for a gas turbine engine having an outer wall containing a plurality of serpentine cooling channels. The serpentine cooling channels may be configured to receive cooling fluids from internal cooling fluids supply channels. The serpentine cooling chann... | 05/01/2012 |
| 8167558 | Modular serpentine cooling systems for turbine engine components A cooling system for use in a turbine engine component exposed to high temperatures during engine operation. The system includes a serpentine flow passage and an exhaust region. The serpentine flow passage includes a coolant supply inlet. The passage can be configur... | 05/01/2012 |
| 7717677 | Multi-metering and diffusion transpiration cooled airfoil A turbine airfoil, or a substrate exposed to a high temperature environment, having a plurality of individual cooling circuits in the airfoil wall, each individual cooling circuit having a first metering hole connecting the cooling circuit to a cooling air supply, a... | 05/18/2010 |
| 7585152 | Cooling jets Cooling jets 1 are provided with a longitudinal aspect 2 greater than width 3. Thus, the coolant flow through the jet 1 is less susceptible to deflection by lateral or cross flows presented to that coolant flow such that cooling by imping... | 09/08/2009 |
| 7371049 | Manufacturable and inspectable microcircuit cooling for blades A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first h... | 05/13/2008 |
| 7311497 | Manufacturable and inspectable microcircuits A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first h... | 12/25/2007 |
| 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 shapes with a ceramic matrix composite bonded to at least one external si... | 10/16/2007 |
| 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 and a through thickness direction substantially normal to the in-plane ... | 08/14/2007 |
| 7247002 | Lamellate CMC structure with interlock to metallic support structure A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperat... | 07/24/2007 |
| 7229245 | Vane platform rail configuration for reduced airfoil stress A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their res... | 06/12/2007 |
| 7223072 | Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor An airfoil for a gas turbine engine blade includes a plurality of film cooling holes extending through its outer surface. The film cooling holes are formed by defining at least a first datum structure and a second datum structure, and then forming each film cooling ... | 05/29/2007 |
| 7198860 | Ceramic tile insulation for gas turbine component Ceramic tile (32) insulation for protecting a substrate material (34) in a high temperature environment. A plurality of ceramic tiles (78) may be used in combination with a monolithic layer of ceramic insulation (80) to protect a fillet r... | 04/03/2007 |
| 7185736 | Aerodynamic noise abatement device and method for air-cooled condensing systems The noise abatement device and method described herein makes known an apparatus and method for reducing the aerodynamic resistance presented by a fluid pressure reduction device in a large duct. More specifically, a noise abatement device is disclosed having at leas... | 03/06/2007 |
| 7144220 | Investment casting An article may be manufactured by providing a reticulate core element in a mold shell having a shape at least partially corresponding to a shape of the article. The molten metallic material is introduced to the shell so as to at least partially infiltrate into the r... | 12/05/2006 |
| 7128530 | Coolable component Throughflow openings are provided for a cooling medium in a coolable component. The throughflow opening comprises an insert that reduces the size of the first opening cross-section to a second opening cross-section, and that is released from the first opening if the... | 10/31/2006 |
| 7128532 | Transpiration cooling system A system for cooling a structure or mechanism through transpiration processes. Generally a porous structural material may be used to form a hot wall surface of a high temperature or high heat flux environment component, typically used in combustion type devices. Coo... | 10/31/2006 |
| 7118326 | Cooled gas turbine vane A gas turbine airfoil (e.g. 12) includes a pressure sidewall (14) and a suction sidewall (16) joined along respective leading and trailing edges (18, 20) and extending radially outward from an inner diameter (26) to an outer diamet... | 10/10/2006 |
| 7104756 | Temperature tolerant vane assembly A vane assembly 10 suitable for a turbine engine features a refractory vane 12 with an internal cavity 20 and a pair of flexible metallic baffles 26 extending into the cavity from spanwisely opposite ends of the vane. A rigid fastener ... | 09/12/2006 |
| 7097424 | Micro-circuit platform A gas turbine engine component, such as a high pressure turbine blade, has an airfoil portion, a platform, and micro-circuits within the platform for cooling at least one of a platform edge adjacent the pressure side of the airfoil portion and the trailing edge of t... | 08/29/2006 |
| 7086829 | Film cooling for the trailing edge of a steam cooled nozzle A nozzle assembly (10) for a turbine engine includes an inner band (16) and an outer band (14) spaced apart from each other. An airfoil (12) installed between the bands has a leading edge (18) and a trailing edge (20). The a... | 08/08/2006 |
| 7052233 | Base material with cooling air hole A base material (2) with a cooling air hole (1) is disclosed, means being present which prevent particles (5), which are located in the cooling air (4) which flows through the cooling air hole (1) during the operation of the coolin... | 05/30/2006 |
| 6984100 | Component and turbine assembly with film cooling A component includes a wall with a cold and a hot surface. At least one film-cooling hole extends through the wall for flowing a coolant from the cold to the hot surface. The film-cooling hole defines an exit site in the hot surface. At least one flow modifier is fo... | 01/10/2006 |
| 6908657 | Coated component with through-hole having improved surface finish A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of... | 06/21/2005 |
| 6905301 | Turbine blade/vane A turbine blade/vane, having a blade/vane aerofoil which extends along a blade/vane axis and through which cooling medium flows, mainly in the longitudinal direction of the turbine blade/vane, is configured comparatively simply for reliable and effective closed cool... | 06/14/2005 |
| 6869270 | Turbine blade cover cooling apparatus and method of fabrication A blade cover cooling apparatus comprises a blade cover top plate, comprising a plurality of upper ribs, a blade cover bottom plate, comprising a plurality of lower ribs. The blade cover top plate is disposed over the blade cover bottom plate. The upper ribs are dis... | 03/22/2005 |
| 6832889 | Integrated bridge turbine blade A turbine blade includes a hollow airfoil integrally joined to a dovetail. The airfoil includes a perforate first bridge defining a flow channel behind the airfoil leading edge. A second bridge is spaced behind the first bridge and extends from a pressure sidewall o... | 12/21/2004 |
| 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 which are covered by the thermal barrier coating, and the pores are venti... | 07/13/2004 |
| 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 are cooled by a cooling fluid (58) passing throug... | 03/23/2004 |
| 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 rotational axis of the helix and axially along the central rot... | 11/11/2003 |
| 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 directly with at least one cooling fluid supply contained ... | 09/09/2003 |
| 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 suction side and a pressure side connected at a leading edg... | 07/29/2003 |
| 6551061 | Process for forming micro cooling channels inside a thermal barrier coating system without masking material The present invention provides a process for forming active convection cooling micro channels within or adjacent to a bond coat layer applied to a turbine high pressure turbine airfoil. When placed adjacent or within a porous TBC, the micro channels addit... | 04/22/2003 |
| 6383602 | Method for improving the cooling effectiveness of a gaseous coolant stream which flows through a substrate, and related articles of manufacture A method for improving the cooling effectiveness of a gaseous coolant stream which flows through at least one passage hole in a substrate to an exit site on a high-temperature surface of the substrate is disclosed. The method comprises disrupting the cool... | 05/07/2002 |
| 6368060 | Shaped cooling hole for an airfoil A cooling hole configuration for an air-cooled component, such as a gas turbine engine airfoil. The cooling hole is configured to have cross-sectional variations and a noncircular-shaped diffuser-type opening that significantly improve the cooling film di... | 04/09/2002 |
| 6276597 | Tip cap hole brazing and oxidation resistant alloy therefor A tip cap hole is loaded with a first composition comprising particles of a first alloy having a solidus temperature above the brazing temperature. The first composition is covered with a second composition comprising particles of a second alloy having a ... | 08/21/2001 |
| 6241469 | Turbine blade Described is a turbine blade with a metal blade body and a protective coating constructed of a porous intermetallic felt, and in the blade body of the turbine blade cooling air channels are constructed that end at the intermetallic felt in order to supply... | 06/05/2001 |
| 6210111 | Turbine blade with platform cooling A cooled turbine blade for a gas turbine engine having a platform cooling supply channel that supplies cooling air to a plurality of cooling holes in the surface of the blade platform adjacent the trailing edge of the blade.... | 04/03/2001 |
| 6187450 | Tip cap hole brazing and oxidation resistant alloy therefor A tip cap hole is loaded with a first composition comprising particles of a first alloy having a solidus temperature above the brazing temperature. The first composition is covered with a second composition comprising particles of a second alloy having a ... | 02/13/2001 |
| 6102658 | Trailing edge cooling apparatus for a gas turbine airfoil A coolable airfoil is provided which includes an internal cavity, an external wall, a plurality of first cooling apertures, and a plurality of second cooling apertures. The external wall includes a suction side portion and a pressure side portion. The wal... | 08/15/2000 |
