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| Number | Title | Issue Date |
| 8186939 | Turbine disc and retaining nut arrangement A turbine rotor for a gas turbine engine including a disc having a hub defining a central bore for receiving an engine shaft. A nut retains the disc on the shaft. The disc retaining nut has at least one cooling passage defined therein and disposed for directing a fl... | 05/29/2012 |
| 8186938 | Turbine apparatus A gas turbine engine comprising a rotor and a stator which define first, second and third cavities; the rotor and stator define a seal therebetween and which is located for sealing between the second and third cavities, the rotor comprises an aperture through which ... | 05/29/2012 |
| 8182204 | Deflector for a gas turbine strut and vane assembly A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially ... | 05/22/2012 |
| 8182202 | Coupling device for a turbine upstream guide vane, a turbine comprising same, and aircraft engine fitted therewith A coupling device for coupling a turbine upstream guide vane which is coupled to a supporting part which itself attached to a stabilizing part is disclosed. The coupling device includes a interlocking device for interlocking a supporting end of the supporting part w... | 05/22/2012 |
| 8182203 | Turbine blade and gas turbine A turbine blade and a gas turbine are provided in which the velocity of cooling fluid at the inlet of a pin fin region is improved so that the cooling performance at the trailing edge of the turbine blade can be improved. It includes an airfoil; a supply channel ext... | 05/22/2012 |
| 8172505 | Cooling structure In this cooling structure, a cooling flow path, which is meandering around a flow direction of a high temperature combustion gas, is provided in a structural body. The cooling flow path has an inflow path for a cooling air formed inside of the structural body; at le... | 05/08/2012 |
| 8172507 | Gas turbine blade with double impingement cooled single suction side tip rail A turbine blade is provided comprising: an airfoil including an airfoil outer wall extending radially outwardly from a blade root, a squealer tip section located at an end of the airfoil distal from the root, and cooling structure. The squealer tip section comprises... | 05/08/2012 |
| 8172506 | Method and system for cooling engine components A method and system for a rotatable member of a turbine engine are provided. The rotatable member includes a substantially cylindrical shaft rotatable about a longitudinal axis, and a hub coupled to the cylindrical shaft through a conical shaft portion wherein the c... | 05/08/2012 |
| 8172504 | Hybrid impingement cooled airfoil A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity po... | 05/08/2012 |
| 8172508 | Multiple airfoil vanes A vane for a turbine assembly of a turbocharger includes a first airfoil that includes a length between a leading edge and a trailing edge, a second airfoil that includes a length between a leading edge and a trailing edge where the length of the first airfoil optio... | 05/08/2012 |
| 8167535 | System and method for providing supercritical cooling steam into a wheelspace of a turbine A system for cooling a high pressure section of a turbomachine includes a conduit configured to carry cooling steam from a boiler to a space upstream of a first stage nozzle of the turbomachine. The conduit extends through a housing of the turbomachine and a nozzle ... | 05/01/2012 |
| 8167537 | Air cooled turbine airfoil with sequential impingement cooling An air cooled turbine airfoil such as a stator vane in which the airfoil is hollowed out and an insert is secured within the hollowed out section that produces sequential impingement cooling of the airfoil. The insert is formed from a plurality of plates bonded toge... | 05/01/2012 |
| 8167536 | Turbine blade leading edge tip cooling system A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one leading edge cooling chamber for cooling the leading edge and for exhausting cooling fluids through a tip exhaust outlet. The leading edge cooling channel may ... | 05/01/2012 |
| 8162593 | Inter-turbine casing with cooling circuit, and turbofan comprising it An inter-turbine casing for a turbofan is disclosed. The casing includes an outer ring, an inner ring, and an intermediate ring between the inner ring and the outer ring. The inner and intermediate rings have respective openings for the passage of cooling air. The c... | 04/24/2012 |
| 8162594 | Cooled blade for a turbomachine A cooled blade forming an upstream guide vane element for a turbomachine is disclosed. The airfoil includes a longitudinal cavity with a first opening at one end and a second opening at the other end, a tubular sleeve being housed in the cavity with a first end in t... | 04/24/2012 |
| 8157504 | Rotor blades for turbine engines A blade tip of a turbine rotor blade for a gas turbine engine, the turbine rotor blade including an airfoil and a root portion for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, a pressure sidewall and a suction sidewall that j... | 04/17/2012 |
| 8157505 | Turbine blade with single tip rail with a mid-positioned deflector portion A turbine blade is provided comprising: an airfoil including an airfoil outer wall extending radially outwardly from a blade root, a squealer tip section located at an end of the airfoil distal from the root, and cooling structure. The squealer tip section comprises... | 04/17/2012 |
| 8152451 | Split fairing for a gas turbine engine A fairing for a structural strut in a gas turbine engine includes: (a) an inner band; (b) an outer band; (c) a hollow, airfoil-shaped vane extending between the inner and outer bands; (d) wherein the fairing is split along a generally transverse plane passing throug... | 04/10/2012 |
| 8142138 | Turbine engine having cooling pin In one embodiment, a turbine system may include a turbine casing, a shroud block coupled to the turbine casing, a fluid passage in the shroud block; and a pin configured to interface with the fluid passage. The pin may include a hollow shaft; a rod inserted into the... | 03/27/2012 |
| 8142137 | Cooled gas turbine vane assembly A gas turbine vane to improve vane performance by addressing known failure mechanisms. A cooling circuit to the trailing edge of a vane airfoil is fed from the outer diameter platform, which prevents failure due to an oxidized and eroded airfoil trailing edge. The g... | 03/27/2012 |
| 8137055 | Turbine blade with an impingement cooling insert A turbine blade, particularly a guide blade for a gas turbine, is provided. The turbine blade includes a blade leg, a platform area and a hollow blade for receiving a metal plate-type impact cooling insert which consists of at least two sections which overlap in an ... | 03/20/2012 |
| 8133008 | Axial flow fluid apparatus and blade An axial flow fluid apparatus axially provided with a plurality of blade rows having a plurality of blades arranged around a shaft is provided. A fluid passage for jetting a fluid to a downstream velocity defect region resulting from a blade is formed in at least on... | 03/13/2012 |
| 8123464 | Coating optimization process using a coupon and component comprising a coupon A method for optimizing the coating of a component using a coupon by introducing the coupon into a depression of the component, in which the geometry of the component is not altered as compared to a component without a coupon, is provided. A component having a depre... | 02/28/2012 |
| 8123465 | Mounting tubes for pressurizing an internal enclosure in a turbomachine A turbomachine comprising high- and low-pressure compressor shafts guided in bearings isolated from an internal enclosure by a sealing end plate, and radial pressurization tubes connecting the enclosure to an air passage passing through the intermediate casing, the ... | 02/28/2012 |
| 8123463 | Method and system for manufacturing a blade A method of manufacturing a blade is provided. The method includes providing a plurality of first plies, each of the first plies sized to extend substantially the length of a span of the blade and providing a plurality of second plies, each of the second plies sized... | 02/28/2012 |
| 8118538 | Offshore vertical-axis wind turbine and associated systems and methods An offshore wind turbine has a vertical-axis wind turbine (VAWT) mounted on a platform. The VAWT has a vertical rotor and curved blades coupled to a gearbox and an electric generator. The VAWT can fixedly extend from the platform or may be capable of reclining on th... | 02/21/2012 |
| 8109712 | Method of producing a turbine or compressor component, and turbine or compressor component Disclosed is a turbine or compressor component with an integrated cooling channel, in particular a turbine blade, and a method for producing the same. The cooling channel of the component is subjected to internal pressure during a pressure impingement phase, the int... | 02/07/2012 |
| 8100634 | Vane and a vane assembly for a gas turbine engine A fan outlet guide vane for a gas turbine engine comprises a generally radially-extending internal structural member and at least one surface member securable in use to the internal structural member so as to define an aerofoil. The gas turbine engine includes an an... | 01/24/2012 |
| 8100633 | Cooling air manifold splash plates and gas turbines engine systems involving such splash plates Cooling air manifold splash plates and gas turbine engine systems involving such splash plates are provided. In this regard, a representative cooling air manifold splash plates includes: a base having an aperture; and an air deflector supported by the base, the air ... | 01/24/2012 |
| 8100635 | Control of clearance at blade tips in a high-pressure turbine of a turbine engine A turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring held by a casing of the turbine, and an annular thermal protection sheet mounted between the casing and the sealing ring is disclosed. The annular thermal protection sh... | 01/24/2012 |
| 8096751 | Turbine engine component with cooling passages A component for use in a turbine engine including a first member and a second member associated with the first member. The second member includes a plurality of connecting elements extending therefrom. The connecting elements include securing portions at ends thereo... | 01/17/2012 |
| 8096752 | Method and apparatus for cooling a transition piece Disclosed is a compressor discharge can including a transition piece and a flow redirector located about the transition piece, defining an airflow space therebetween, the flow redirector configured to reduce recirculation of flow in the airflow space. ... | 01/17/2012 |
| 8092152 | Device for cooling slots of a turbomachine rotor disk The invention relates to a device for cooling the slots of a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange that extends upstream from a radially upstream face of the disk. The device also comprises a retaining a... | 01/10/2012 |
| 8092153 | Bypass air scoop for gas turbine engine A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a... | 01/10/2012 |
| 8087879 | Device for cooling the slots of a rotor disk in a turbomachine having two air feeds The invention relates to a device for cooling slots in a turbomachine rotor disk, comprising a rotor disk having a plurality of slots and a flange. The device also comprises blades, each having its root mounted in a respective slot, a retaining annulus having one en... | 01/03/2012 |
| 8079802 | Gas turbine A gas turbine includes a shaft directional passage provided to a rotating member that rotates along a central axis of a rotor, which is a rotating axis of the rotating member, about the central axis, or a rotating axis of the rotating member, and in which cooling ai... | 12/20/2011 |
| 8079804 | Cooling structure for outer surface of a gas turbine case A gas turbine case is provided including an outer case surface, and a channel portion formed as a recessed area extending radially inwardly into the outer case surface. The channel portion extends about a circumference of the case. An outer flow jacket is attached t... | 12/20/2011 |
| 8079803 | Gas turbine and cooling air supply structure thereof The present invention includes an introducing passage that is provided within a turbine stationary blade fixed within a turbine casing and that communicates an interior of the turbine casing with an exterior thereof; a nozzle that is provided in an inner circumferen... | 12/20/2011 |
| 8079805 | Rotary separator and shaft coupler for compressors A separator is for a turbomachine, preferably a compressor including a casing, a primary compressor shaft with an impeller disposed within the casing, and a drive shaft connectable with the compressor shaft. The separator includes a coupler having a central axis and... | 12/20/2011 |
| 8070422 | Turbine stator vane and rotor blade arrangement A turbine rotor blade and stator vane assembly in which the rotor blades include a cooling air discharge slot formed within the blade platform to discharge cooling air toward a surface of the adjacent vane to prevent formation of a vortex flow over the region of the... | 12/06/2011 |
