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| Number | Title | Issue Date |
| 8137072 | Turbine blade including a seal pocket A turbine blade is disclosed. The turbine blade may have an airfoil extending from a first surface of a turbine platform. The turbine blade may further have a first side pocket of the turbine platform that is configured to substantially entirely house a first moveab... | 03/20/2012 |
| 8137071 | Damper for turbomachine vanes A turbomachine vane damper constructed so as to be housed between the lower face of the platforms of two adjacent turbomachine vanes and the rim of the rotor disk on which the vanes are mounted is disclosed. The damper includes a weight, a bearing plate and a spring... | 03/20/2012 |
| 8113784 | Coolable airfoil attachment section A rotor blade suitable for use in a gas turbine engine includes an attachment section which defines at least one internal cooling passage along a passage axis through the attachment section. ... | 02/14/2012 |
| 8105037 | Endwall with leading-edge hump An example airfoil assembly includes a base having an airfoil projecting radially therefrom. The base extends laterally away from the airfoil. The airfoil extends axially from an airfoil leading edge portion to an airfoil trailing edge portion. The base has a humped... | 01/31/2012 |
| 8100655 | Method of machining airfoil root fillets An airfoil root fillet having a predetermined compound curve profile can be flank milled with a single flank milling cutter having a generally conical flank milling portion and a rounded tip portion defining a compound curve. ... | 01/24/2012 |
| 8066489 | Aerofoil assembly An aerofoil assembly includes a plurality of rotatable blades. A damping member is disposed between at least two of the blades, each of the at least two blades having an aerofoil portion, a stem portion and a root portion. A recess is provided on two cooperating ste... | 11/29/2011 |
| 8061994 | Rotorcraft blade, a rotorcraft rotor provided with said blade, and a method of fabricating said blade A rotorcraft rotor blade (1) has a blade root (1′) and a free end opposite from the blade root (1′), the blade (1) being provided at least with a spar (2) laid flat on a suction-side face (3) and a pressure side-face ( | 11/22/2011 |
| 8021118 | Turbine blade for a turbine with a cooling medium passage A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which extends inside the platform, for guiding a cooling medium, is charact... | 09/20/2011 |
| 7976281 | Turbine rotor blade and method of assembling the same A rotor blade assembly includes a shank, an airfoil that is formed integrally with the shank, and a removable platform coupled between said shank and said airfoil via a friction fit. A method of assembling a gas turbine engine rotor blade assembly that includes a re... | 07/12/2011 |
| 7931442 | Rotor blade assembly with de-coupled composite platform A rotor disk assembly with a platform spacer secured to the rotor disk and un-coupled from the rotor blades. Adjacent rotor blades are secured to the rotor disk slots by conventional means. The rotor disk includes a dovetail extending from the rim and positioned sub... | 04/26/2011 |
| 7922453 | Process for preparing turbine blades or vanes for a subsequent treatment, and associated turbine blade or vane Process for preparing turbine blades or vanes for a subsequent treatment, for example the application of a coating and/or a material-removing operation, wherein the turbine blade or vane has an airfoil, which is delimited at at least one end by an endplate with peri... | 04/12/2011 |
| 7887297 | Airfoil array with an endwall protrusion and components of the array An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28, or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a hu... | 02/15/2011 |
| 7878763 | Turbine rotor blade assembly and method of assembling the same A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and t... | 02/01/2011 |
| 7874804 | Turbine blade with detached platform A turbine blade with a detached platform in which the platform has a central opening in which the blade is inserted and held in place. The blade includes a root portion with a fir tree configuration to fit within a slot of a rotor disc. The platform includes two leg... | 01/25/2011 |
| 7874803 | Gas turbine rotor On a gas turbine rotor with internally cooled airfoils (4) of the turbine rotor blades and a mechanical sealing and damping element arranged between opposite side faces (6) of adjacent blade platforms (7), the gap is additionally aerodynamically... | 01/25/2011 |
| 7862300 | Turbomachinery blade having a platform relief hole A turbomachinery blade having a relief hole in its platform and a method of limiting the formation and/or propagation of cracks in the trailing edge of the blade are provided. The relief hole may be formed in the concave side of the platform proximate the trailing e... | 01/04/2011 |
| 7766621 | Split shank rotor blade A shroudless turbine rotor blade of the type having a platform damper interface, is provided with at least one slot which extends from the aerofoil side of a platform flow boundary to a point in the root. The slot extends between opposing flanks of the blade so as t... | 08/03/2010 |
| 7762780 | Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies A blade assembly 100 (FIG. 5) configuration that includes a means for distributing mechanical stress (e.g., a stress dissipater 54) is provided. The stress dissipater is configured to reduce the concentration of a peak mechanical stress without ... | 07/27/2010 |
| 7762781 | Composite blade and platform assembly A turbine blade and platform assembly in which the platform is a separate piece that is secured to the blade through shear pins that extend along slots formed between opposed abutting parts of the blade and the platform. Because the platform is detached from the bla... | 07/27/2010 |
| 7708528 | Platform mate face contours for turbine airfoils Gas turbine engine components having an airfoil extending outwardly of a platform are mounted in adjacent relationship, and such that cooling air flows outwardly of a gap between mating faces of the platforms. The location of localized hot spots is identified on the... | 05/04/2010 |
| 7625181 | Turbine cascade structure A turbine blade cascade structure includes a plurality of blades arranged in series in a circumferential direction on a wall surface, in which a corner portion defined by the wall surface and a front edge portion of each of blade bodies supported by the wall surface... | 12/01/2009 |
| 7581930 | High lift transonic turbine blade A turbine blade system including a blade airfoil having an airfoil shape with the blade airfoil having a nominal profile substantially in accordance with normalized Cartesian coordinate values Z set forth in a table 1 below and which values are dimensionless values ... | 09/01/2009 |
| 7575416 | Rotor assembly for a rotary machine A rotor assembly having a seal member in the root section of a rotor blade is disclosed. Various construction details are developed for blocking the flow of gases between adjacent rotor blades. In one detailed embodiment, a deformable seal member formed of a high te... | 08/18/2009 |
| 7534090 | Enhanced bucket vibration system An enhanced damping system for a turbine bucket. The damping system includes a damper pocket and a damper pin with an offset center of gravity positioned within the damper pocket. ... | 05/19/2009 |
| 7488157 | Turbine vane with removable platform inserts Aspects of the invention are related to a turbine vane assembly in which at least one of the platforms is equipped with one or more removable platform inserts. The inserts can be used in those areas of the platform where failures or damage has been known to occur, a... | 02/10/2009 |
| 7484935 | Turbine rotor hub contour Disclosed herein is a turbine rotor having a contoured hub comprising a cambered surface extending from a leading edge of the rotor hub to a trailing edge of the rotor hub along an axial direction of the rotor hub. A turbine rotor and a gas turbine engine comprising... | 02/03/2009 |
| 7467924 | Turbine blade including revised platform The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly ... | 12/23/2008 |
| 7445433 | Fan or compressor blisk A fan or compressor blisk for a gas turbine engine, lift fan or the like, comprises a disc having a radially outer rim, and a plurality of aerofoil blades circumferentially spaced around and extending radially outwards from the rim. The rim has a radially inward fac... | 11/04/2008 |
| 7442007 | Angled blade firtree retaining system A blade root retaining system for attachment of a turbine blade to a turbine disc of a gas turbine engine comprises a blade root having at least one projection on each of opposite sides thereof, the projection extending from a leading edge to a trailing edge of the ... | 10/28/2008 |
| 7431564 | Turbine blisk A blisk for use in the turbine section of a gas turbine engine comprises a disk around the circumference of which is disposed a plurality of blades in an annular array. The blades are preferably cast separately and then joined, for example by welding, so that the ro... | 10/07/2008 |
| 7416391 | Bucket platform cooling circuit and method In a turbine bucket having an airfoil portion and a root portion with a platform at an interface between the airfoil portion and the root portion, a platform cooling arrangement including: a cooling passage defined in the platform to extend along at least a portion ... | 08/26/2008 |
| 7399163 | Rotor blade for a compressor or a gas turbine Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, including a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform conn... | 07/15/2008 |
| 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 |
| 7371046 | Turbine airfoil with variable and compound fillet A turbine airfoil may be a rotating blade having a single platform, or a stationary nozzle having a pair of platforms. The airfoil body has pressure and suction sidewalls extending between leading and trailing edges. A compound fillet is disposed between the airfoil... | 05/13/2008 |
| 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 |
| 7354243 | Axial compressor blading An axial compressor has at least one circumferential row of aerofoil members (30a, 30b, 30c) in which at least one of the two end walls (37) between adjacent blades is given a non-axisymmetric profile, defined by circ... | 04/08/2008 |
| 7341533 | CVT housing having wear-resistant bore A continuously variable transmission (CVT) includes an aluminum housing member having a bore formed therein. A rotatable pulley member is supported on a bearing within the bore. The bore includes a layer of thermal spray coating for improved wear resistance so that ... | 03/11/2008 |
| 7334983 | Integrated bladed fluid seal Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extendi... | 02/26/2008 |
| 7334995 | Turbine blade assembly and method of manufacture Aspects of the invention are directed to a turbine blade assembly and an associated method of manufacture. The turbine blade assembly can include: (a) a unitary structure having an airfoil and a primary root portion; (b) a separately-formed platform; and (c) a secon... | 02/26/2008 |
| 7331755 | Method for coating gas turbine engine components A method for assembling a vane sector for a gas turbine engine, the vane sector including an airfoil vane and a platform includes depositing a wear coating material onto a selected area of the platform, positioning the platform adjacent to the airfoil vane, and exec... | 02/19/2008 |
