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| Number | Title | Issue Date |
| 8186952 | Blade arrangement With regard to gas turbine engines it will be appreciated that blades are typically cooled in order to ensure that the materials from which the blades are formed remain within acceptable operational parameters. Coolant is judiciously used in order to maintain engine... | 05/29/2012 |
| 8105030 | Cooled airfoils and gas turbine engine systems involving such airfoils Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a trailing edge, a suction side and a pressure side; an interior surface defin... | 01/31/2012 |
| 8092175 | Turbine blade The invention relates to a turbine blade comprising a profiled vane around which working gas flows. The working gas cross-flows a front edge of the vane and flows away on a rear edge of the vane. The vane has a first and a second channel system for guiding two media... | 01/10/2012 |
| 8070440 | Cooling channel formed in a wall A wall element having at least one cooling channel formed therein, the wall element presenting an inside surface and an outside surface, the channel comprising a hole and a diffusion portion, the hole opening out at one end in the inside surface, and at the other en... | 12/06/2011 |
| 8066482 | Shaped cooling holes for reduced stress A gas turbine engine component having shaped cooling holes that further enhances the cooling of a desired region while reducing stress levels in and around the cooling holes is disclosed. The cooling holes are generally elliptically-shaped and diffuse from a cooling... | 11/29/2011 |
| 8047786 | Apparatus for plugging turbine wheel holes A turbine wheel hole plug that includes: 1) an approximate cylindrical body, the cylindrical body sized such that the cylindrical body fits snugly into a turbine wheel hole; 2) a first flange at a first end of the cylindrical body, the first flange being approximate... | 11/01/2011 |
| 8038399 | Turbine rim cavity sealing A rim cavity seal arrangement for a gas turbine engine, where the rim cavity is formed between two rotor disk stages with a stator vane assembly positioned between the rotor disks and extending into the rim cavity. A cover plate secured onto a side of the rotor disk... | 10/18/2011 |
| 8033789 | Apparatus for preventing ice accretion Aerofoils (22) of a gas turbine engine are provided with a coating (34) or filler (44) of viscoelastic material. As ice accretes on the aerofoils (22) during operation, the resulting aerodynamic stability imbalance induces vibration in th... | 10/11/2011 |
| 7896616 | Integrated leading edge for wind turbine blade A wind turbine blade that includes integrated erosion, lightning and icing protection for a leading edge. The leading edge includes a frontal surface with an erosion shield positioned external to the frontal surface. An internal lightning conveyance path is provided... | 03/01/2011 |
| 7717675 | Turbine airfoil with a near wall mini serpentine cooling circuit A stator vane for use in a gas turbine engine, the vane having a plurality of near wall mini serpentine flow cooling modules arranged in an array on the airfoil walls. Each module includes a series of multiple pass serpentine flow cooling channels extending in the a... | 05/18/2010 |
| 7578655 | Composite gas turbine fan blade A composite turbine blade and fan blade assembly for use in a turbo machine such as a gas turbine engine. The turbine blade assembly includes a plurality of metallic turbine blades secured to a rotor disk and forming an outer shroud assembly. A fiber reinforced comp... | 08/25/2009 |
| 7537431 | Turbine blade tip with mini-serpentine cooling circuit A turbine blade having a cooling supply passage formed within the blade, and a blade tip with a squealer tip formed thereon. The blade tip includes a blade top or cap, and includes a plurality of mini-serpentine cooling channels formed within the tip. The mini-serpe... | 05/26/2009 |
| 7429166 | Methods and apparatus for gas turbine engines A method for manufacturing a turbine engine component includes forming a component to include a first side and an opposite second side, positioning at least one capillary adjacent to an external surface of at least one of the first and second sides, and securing the... | 09/30/2008 |
| 7430119 | Impeller and aligned cold plate According to some embodiments, an apparatus may comprise a cold plate comprising a plurality of fins and an impeller comprising a plurality of blades. An output fluid velocity angle defined by the plurality of fins may be aligned to an impeller inlet velocity angle.... | 09/30/2008 |
| 7390167 | Compressor with centripetal air takeoff A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between... | 06/24/2008 |
| 7374400 | Turbine blade arrangement A turbine blade arrangement comprises turbine blades which are secured in adjacent positions to a rotor disc with a cavity defined between root segments and platform segments. A flow deflector within the cavity is provided as an insert such that through a recessed p... | 05/20/2008 |
| 7371044 | Seal plate for turbine rotor assembly between turbine blade and turbine vane This invention relates to a seal plate system adapted to fit between axially adjacent turbine blades and turbine vanes to seal a rim cavity. The seal plate system may be formed from a seal plate supported by a plurality of extended disk lugs extending from a disk. T... | 05/13/2008 |
| 7367190 | Supercharger with electric motor In a supercharger (10) with an electric motor in accordance with the present invention, the electric motor (20) is arranged at a position adjacent to a compressor impeller (6), a center housing (14) has a cooling fluid flow path (34 | 05/06/2008 |
| 7367123 | Coated bucket damper pin and related method A damper pin for a turbine bucket includes an elongated main body portion of substantially uniform cross-sectional shape having opposite ends, one only of said opposite ends coated with a corrosion and oxidation-resistant coating. ... | 05/06/2008 |
| 7367766 | Screw and nut fastening device A device for fastening two parts to each other includes fastening screws extending in aligned passages in the two parts and receiving nuts, and a removable element for preventing the screw heads from moving during tightening or loosening of the nuts on the screws, t... | 05/06/2008 |
| 7364404 | Turbomachine with fluid removal A turbomachine includes at least one rotor (6), at least one stator (7), and a casing (1), with the rotor (6) comprising several rotor blades (8) attached to a rotating shaft, and with the stator (7) being provided with stat... | 04/29/2008 |
| 7362574 | Jet orifice plate with projecting jet orifice structures for direct impingement cooling apparatus A cooling apparatus and a direct cooling impingement module are provided, along with a method of fabrication thereof. The cooling apparatus and direct impingement cooling module include a manifold structure and a jet orifice plate for injecting coolant onto a surfac... | 04/22/2008 |
| 7354241 | Rotor assembly with cooling air deflectors and method A rotor assembly for a gas turbine engine, the rotor assembly comprises a plurality of cooling air deflectors made integral with the rotor disk to redirect air to a manifold at a bottom side of a corresponding blade retention slot on the periphery of the rotor disk.... | 04/08/2008 |
| 7347672 | Rotor disk balancing device, disk fitted with such a device and rotor with such a disk A rotor disc includes a rim and a balancing device, which includes housings formed in the rim, and balancing masses housed in at least some of the housings. ... | 03/25/2008 |
| 7334412 | Cooling air and injected liquid system for gas turbine blades The invention relates to a turbine 1, in particular a gas turbine, which along a swivel-mounted rotationally symmetrical rotor 2 has a compressor 3, a combustion chamber 5 and a turbine section 7 formed of a plurality of turbine st... | 02/26/2008 |
| 7334999 | Turbomachine rotor including at least one disk reinforced by a composite ring A turbomachine rotor including at least one disk having a ring constituted, for example, by a winding of metal-coated silicon carbide or alumina yarn. According to the invention, the composite ring is received in a closed annular cavity, e.g. defining by machining a... | 02/26/2008 |
| 7329086 | Rotor shaft, in particular for a gas turbine A rotor shaft, particularly for a gas turbine, includes a cooling air supply disposed inside the rotor shaft and a plurality of cooling air ducts connected to the cooling air supply and extending essentially radially outward toward an outside of the shaft, wherein e... | 02/12/2008 |
| 7303376 | Turbine airfoil with outer wall cooling system and inner mid-chord hot gas receiving cavity A turbine airfoil usable in a turbine engine and having at least one cooling system. The cooling system may be positioned in an outer wall of the turbine airfoil, and the airfoil may include a hot gas receiving cavity positioned in a mid-chord region of the airfoil.... | 12/04/2007 |
| 7287961 | Retaining arrangement A retaining arrangement for joining together two components such as a rim coverplate 10 and a rotor disc 12 in a gas turbine engine. The arrangement comprising a channel 54 formed by respective formations 26, 52 on the disc 12 and ... | 10/30/2007 |
| 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 |
| 7264447 | Sealing arrangement for an axial turbine wheel In an axial turbine wheel including a rotor disk and a plurality of turbine blades each having a base end retained by the rotor disk via a joint and extending radially from the rotor disk, a seal plate is received in outer and annular slots formed in the base ends o... | 09/04/2007 |
| 7258526 | Eddy current heating for reducing transient thermal stresses in a rotor of a gas turbine engine The device and method are used for heating a central section of a rotor mounted for rotation in a gas turbine engine. ... | 08/21/2007 |
| 7249935 | Lightning protection means for a wind turbine A lightning protection device which is capable of avoiding electrical current, which is being induced in the blades of wind turbine, from being passed to parts of the wind turbine that may be damaged or destroyed by the electrical current. The electrical current is ... | 07/31/2007 |
| 7241117 | Motor shaft assembly and method A method for assembling a motor shaft with a bearing, a motor housing, and an impeller is disclosed. A motor shaft extension is used to retain the impeller axially on the motor shaft and allows the motor shaft to drive an additional component, such as an impeller, l... | 07/10/2007 |
| 7241109 | Seal system A seal system comprises a rotor and a stator. First and second cavities are defined between the rotor and the stator. A plurality of seals for inhibiting a flow of gas through the cavities are provided. Relative motion between the rotor and the stator can cause a fl... | 07/10/2007 |
| 7229254 | Turbine blade with a reduced mass The invention relates to a turbine comprising at least four stages and to the use of a rotor blade with a reduced mass. In prior art, rotor blades in the fourth stage of a gas turbine, which exceed 50 cm in length, cause problems relating to mechanical strength, as ... | 06/12/2007 |
| 7217091 | Methods and apparatus for deicing airfoils or rotor blades A method for deicing a rotor blade having a blade root, a blade tip, and a leading edge in which the rotor blade is operably coupled to a hub of a turbine includes circulating heated air through an outflow channel from the blade root towards the blade tip, recircula... | 05/15/2007 |
| 7214034 | Control of leak zone under blade platform A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the... | 05/08/2007 |
| 7207776 | Cooling arrangement A cooling arrangement comprises a support (20) for a plurality of blades (22). The support (20) comprises a plurality of blade mounting members (28) provided between adjacent blades (22). The blades (22) are mounted upon the... | 04/24/2007 |
| 7207775 | Turbine bucket with optimized cooling circuit A turbine bucket includes a cooling circuit through a dovetail section, a shank section and an airfoil section. The cooling circuit is configured to maximize cooling ability and maximize a useful life at base load operation at firing temperatures of up to 2084° F. ... | 04/24/2007 |
