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| Number | Title | Issue Date |
| 8186953 | Multiple piece turbine blade A turbine rotor blade with a spar and shell construction, the spar including an internal cooling supply channel extending from an inlet end on a root section and ending near the tip end, and a plurality of external cooling channels formed on both side of the spar, w... | 05/29/2012 |
| 8182225 | Blade for a gas turbine A blade for a gas turbine includes a leading edge running in a longitudinal direction substantially radially to an axis of the turbine; a trailing edge running in the longitudinal direction; a blade body disposed between the leading edge and the trailing edge so as ... | 05/22/2012 |
| 8177506 | Microcircuit cooling with an aspect ratio of unity A turbine engine component having improved cooling is provided. The turbine engine component includes an airfoil portion having a leading edge, a trailing edge, a pressure side, a suction side, a root, and a tip, and at least one cooling circuit in a wall of the air... | 05/15/2012 |
| 8177507 | Triangular serpentine cooling channels A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and cooling channels ex... | 05/15/2012 |
| 8172534 | Turbine blade or vane with improved cooling Disclosed is a turbine blade or vane including a blade or vane body including a leading edge and a trailing edge, a plurality of cooling openings disposed along the trailing edge, a first width of the trailing edge, the first width being disposed across the cooling ... | 05/08/2012 |
| 8172533 | Turbine blade internal cooling configuration A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cool... | 05/08/2012 |
| 8167560 | Turbine airfoil with an internal cooling system having enhanced vortex forming turbulators A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorth... | 05/01/2012 |
| 8167557 | Gas turbine engine assemblies with vortex suppression and cooling film replenishment A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembl... | 05/01/2012 |
| 8157527 | Airfoil with tapered radial cooling passage A turbine engine airfoil includes an airfoil structure having an exterior surface and an end portion. A cooling passage extends a length radially within the structure in a direction toward the end portion. The cooling passage provides a convection surface along the ... | 04/17/2012 |
| 8157526 | Component having a film cooling hole Conventionally coated components with film cooling holes are known, comprising a diffuser, extending through the layers into the substrate. According to the invention, the component is embodied such that the whole diffuser is largely arranged in the layer. ... | 04/17/2012 |
| 8152469 | Annular turbine ring rotor A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which... | 04/10/2012 |
| 8147197 | Turbine blade platform A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent th... | 04/03/2012 |
| 8137068 | Castings, casting cores, and methods The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a plurality of metallic casting cores.... | 03/20/2012 |
| 8137069 | Turbine blades A cast turbine blade is disclosed and includes an internal cooling passage that passes (e.g., zig-zags or meanders) through the blade from an inlet in the blade root to an outlet in the blade tip. The cooling passage can have a zone at a bend that is at a distance w... | 03/20/2012 |
| 8128366 | Counter-vortex film cooling hole design An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall to a first outlet along the exterior surface of the wall for providing film cooling, and first and second rows of vortex-g... | 03/06/2012 |
| 8123481 | Turbine blade with dual serpentine cooling A turbine rotor blade with a low cooling flow serpentine circuit to provides cooling for the airfoil. The circuit includes a three pass aft flowing serpentine circuit that begins at the airfoil mid-chord region and connects to a series of multiple impingement coolin... | 02/28/2012 |
| 8118554 | Turbine vane with endwall cooling A turbine stator vane with an outer endwall and an inner endwall, and with an airfoil extending between the two endwalls. The inner endwall includes an endwall edge with a plurality of slots each separated to form compartment slots. A number of impingement cooling h... | 02/21/2012 |
| 8113780 | Castings, casting cores, and methods A gas turbine engine component has a leading edge and a trailing edge and a pressure side and a suction side. The pressure side and suction side extend between the leading edge and trailing edge. One or more cooling passageways extend through the airfoil and compris... | 02/14/2012 |
| 8109726 | Turbine blade with micro channel cooling system A cooling system for a turbine airfoil of a turbine engine has a multi-pass serpentine flow circuit providing a flow path from a forward cooling flow entry at the root and exhausting towards the trailing edge through a series of chord wise micro channels extending f... | 02/07/2012 |
| 8105032 | Systems and methods for internally cooling a wheel of a steam turbine A system may cool a wheel of a steam turbine, the wheel being associated with a rotor of the steam turbine. The system may include an inlet passage and an outlet passage. The inlet passage may be positioned to communicate steam from an exterior of the rotor, through... | 01/31/2012 |
| 8105033 | Particle resistant in-wall cooling passage inlet A cooling microcircuit for a turbine engine component has a first cooling passage which has at least one inlet oriented in a radially outward direction for preventing particles from entering the cooling passage and for dislodging particles which may become lodged in... | 01/31/2012 |
| 8105031 | Cooling arrangement for turbine components A turbine component includes an aft cooling circuit that extends between a turbine midsection and a turbine trailing end. The aft cooling circuit includes a trailing end section proximate the trailing end, a first interior section proximate the turbine midsection, a... | 01/31/2012 |
| 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 7 extending along th... | 01/24/2012 |
| 8100654 | Turbine blade with impingement cooling A turbine blade with a spar to support a thin thermal skin for the outer airfoil surface. The spar includes multiple rows of impingement cooling cavities that are each connected in series through curved impingement cooling holes to provide cooling for the airfoil wa... | 01/24/2012 |
| 8096767 | Turbine blade with serpentine cooling circuit formed within the tip shroud A turbine rotor blade with a tip shroud that has a baffle seal with a knife edge to form a seal with a honeycomb seal of the shroud, where the tip shroud includes larger ribs that form separate compartment each with smaller ribs that form serpentine flow cooling cir... | 01/17/2012 |
| 8096770 | Trailing edge cooling for turbine blade airfoil A gas turbine engine hollow turbine airfoil having chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between the leading edge and the trailing edge. A trailing edge rib extends from the t... | 01/17/2012 |
| 8096772 | Turbine vane for a gas turbine engine having serpentine cooling channels within the inner endwall A turbine vane for a gas turbine engine having an internal cooling system in fluid communication with cooling channels positioned in the inner endwall is disclosed. The cooling system in the inner endwall may include cooling channels extending outwardly from the lea... | 01/17/2012 |
| 8096769 | Damper Dampers (56, 76, 96) are utilized with regard to mounting arrangements (50, 70, 90) in gas turbine engines (10) in order to facilitate cooling. It is known to provide slotted upper surface or cottage roof dampers to enhance cooling effect. Howev... | 01/17/2012 |
| 8096768 | Turbine blade with trailing edge impingement cooling A turbine blade for an industrial gas turbine engine, the blade includes a squealer pocket formed by a pressure side tip rail and a suction side tip rail with tip cooling holes opening onto the tip floor in the trailing edge region, a tip corner and two impingement ... | 01/17/2012 |
| 8096771 | Trailing edge cooling slot configuration for a turbine airfoil A gas turbine engine hollow turbine airfoil having pressure and suction sidewalls extending chordwise between leading and the trailing edges. The trailing edge includes a pressure sidewall lip and a suction sidewall lip, and a breakout distance between the pressure ... | 01/17/2012 |
| 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 radially past a floor of the shelf. The sealing portion extends from a blad... | 01/10/2012 |
| 8092178 | Turbine blade for a gas turbine engine The turbine blade comprises an airfoil having opposite pressure and suction sidewalls extending from a platform to a free end tip and in a chordwise direction from a leading edge to a trailing edge. The blade has two winglets extending in a chordwise direction from ... | 01/10/2012 |
| 8087893 | Turbine blade with showerhead film cooling holes A turbine rotor blade with a showerhead arrangement of film cooling air for cooling the leading edge of the airfoil, where the film cooling holes each includes a tear drop shaped opening that extends in a radial direction of the airfoil from the film hole breakout a... | 01/03/2012 |
| 8087892 | Turbine blade with dual serpentine flow circuits A turbine blade for use in a high temperature environment and with low cooling flow. The blade includes a dual serpentine flow cooling circuit with a 5-pass serpentine circuit located along the leading edge and the tip section of the blade. A 3-pass serpentine circu... | 01/03/2012 |
| 8087891 | Turbine blade with tip region cooling A turbine blade with a tip region cooling circuit in which cooling air from a serpentine flow circuit in the main airfoil body passes into the tip cooling circuit and around the suction side and pressure side walls to better cool the airfoil and tip with low cooling... | 01/03/2012 |
| 8083485 | Angled tripped airfoil peanut cavity A turbine airfoil comprises a wall portion, a cooling channel, an impingement rib, impingement rib nozzles, turbulators and leading edge cooling holes. The wall portion comprises a leading edge, a trailing edge, an outer diameter end, and an inner diameter end. The ... | 12/27/2011 |
| 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 airfoil and connected to a row of exit slots, and in which a second leg inc... | 12/27/2011 |
| 8079815 | Turbine blade In a turbine blade in which a tabular rib partitioning the blade into a pressure side and a suction side is provided in substantially the midsection of the blade along a center line connecting a leading edge and a trailing edge, and at least two cavities of which a ... | 12/20/2011 |
| 8079812 | Turbine component A plurality of film cooling holes 13 is formed at regions exposed to a hot gas in a turbine component main body 3, each of the film cooling holes 13 is comprised of a straight hole portion 15 formed at a portion at a side of an inner wall... | 12/20/2011 |
| 8079811 | Turbine blade with multi-impingement cooled squealer tip A turbine blade with a squealer tip having a cooling circuit formed from a number of rows of multiple impingement cavities that extend across the blade tip from the pressure side wall to the suction side wall. One of the impingement cavities (main impingement cavity... | 12/20/2011 |
