Quotables
"The wireless music box has no imaginable commercial value. Who would pay for a message sent to nobody in particular?"
David Sarnoff, American radio pioneer ; 1921
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 8079821 | Turbine airfoil with dual wall formed from inner and outer layers separated by a compliant structure A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration ma... | 12/20/2011 |
| 8047799 | Wind turbine blades with improved bond line and associated method A wind turbine blade includes an upper shell member and a lower shell member with an internal cavity therebetween. The shell members are joined at leading and trailing edges of the blade with a bond paste along a bond line having a designed width. A sleeve is dispos... | 11/01/2011 |
| 8047800 | Wind turbine blades with improved bond line and associated method A wind turbine blade includes an upper shell member and a lower shell member with an internal cavity therebetween. The shell members are joined at leading and trailing edges of the blade with a bond paste along a bond line having a designed width. A barrier is dispo... | 11/01/2011 |
| 7993106 | Core for use in a casting mould A core, for use in a casting mould to form a cavity in a cast component such as a blade or vane of a gas turbine engine. The core has a relatively fragile thin-walled region. A bead is formed along a lateral edge of the thin-walled portion in order to reduce crackin... | 08/09/2011 |
| 7993105 | Hollow fan blade for gas turbine engine A hollow fan blade for a gas turbine engine provides improved resistance to buckling without adding wall thickness. The hollow fan blade includes a pressure side wall and a suction side wall separated and supported by ribs. In the present invention, each wall segmen... | 08/09/2011 |
| 7922456 | Lightweight components A lightweight component in the form of an outlet guide vane for a gas turbine engine and a method of manufacturing such lightweight components are provided. The vane is filled with hollow metal ellipsoid members in a solid metal outer member. The arrangement of holl... | 04/12/2011 |
| 7824158 | Bimaterial turbine blade damper A turbine blade damper includes an outer part for damping vibration of the blade airfoil and a supporting inner part. The two parts are formed of different materials for the different performance required thereof in the blade. ... | 11/02/2010 |
| 7588421 | Methods and apparatus for mechanical retainment of non-metallic fillers in pockets A method for making a turbine blade includes providing a bucket in the turbine blade with a plurality of window pockets passing all the way through a wall of the bucket, positioning the window pockets in regions minimizing or at least reducing stress concentrations ... | 09/15/2009 |
| 7441331 | Turbine engine component manufacture methods A cooled turbine engine component is made by providing first and second pieces respectively having first and second surfaces. At least one circuit is formed in at least one of the first and second surfaces. A first plurality of apertures is provided in the first pie... | 10/28/2008 |
| 7438523 | Blade for a turbine engine and method for production of said blade A blade for a turbine engine is described, having a base body, made from a titanium alloy, with a first and a second component piece, which are connected in the connection region by means of a bonding process. A groove with a groove wall runs through the connection ... | 10/21/2008 |
| 7435057 | Blade for wind turbine A blade for a wind turbine includes a device for causing air at an increased velocity and/or pressure to escape from exit openings in the blade, thereby to apply a force. Pressure and diameter adjustable valves may be provided at each exit opening or orifice to allo... | 10/14/2008 |
| 7435058 | Ceramic matrix composite vane with chordwise stiffener A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that ... | 10/14/2008 |
| 7413409 | Turbine airfoil with weight reduction plenum An airfoil for a gas turbine engine includes: opposed pressure and suction sidewalls extending between spaced-apart leading and trailing edges, a root, and a tip; and a hollow plenum disposed between the sidewalls. The plenum has a chordwise first dimension at a rad... | 08/19/2008 |
| 7393184 | Modular blades and methods for making same A method for making a blade includes stacking a plurality of modular segments having formed conduits, threading and tensioning cables through the conduits of the stacked segments, and clamping the cables to hold the modular segments together. ... | 07/01/2008 |
| 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 |
| 7334333 | Method for making a hollow fan blade with machined internal cavities Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. The floor and opposite interior walls of each cavity are machined simultaneously. The c... | 02/26/2008 |
| 7329102 | Blade With regard to hollow blades for turbine engines, it will be understood there is a problem with respect to percussive impact resulting in excessive distortion of the blade as well as potential failure as a result of blade tip bulging. By provision of ridges 107, ... | 02/12/2008 |
| 7322798 | High structural efficiency blades and devices using same A blade for a rotor has integral stiffeners with at least one of unidirectional caps configured to carry blade bending loads in axial tension or webs to carry transverse shear resulting from blade bending. ... | 01/29/2008 |
| 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 |
| 7300251 | Turbine cooling vane of gas turbine engine A cooled blade of a small gas turbine engine can enhance cooling performance without increasing the amount of cooling air in a simple configuration. A cooled turbine blade is provided with a cooling passageway 12 formed inside thereof, making the cooling air ... | 11/27/2007 |
| 7300256 | Damping arrangement for a blade of an axial turbine A damping arrangement for a blade (20) of an axial turbine, in particular a gas turbine, includes a damping element (17) which is arranged in a recess (16) in the blade aerofoil (10) of the blade (20) and frictionally dampens the v... | 11/27/2007 |
| 7284958 | Separable blade platform A gas turbine engine blade platform including a par of platform retention members. The pair of platform retention members are configured to be located on opposite sides of a disk lug. The retention members interact with the disk lug to restrain radial movement of th... | 10/23/2007 |
| 7258530 | CMC component and method of fabrication An airfoil (44) formed of a plurality of pre-fired structural CMC panels (46, 48, 50, 52). Each panel is formed to have an open shape having opposed ends (54) that are free to move during the drying, curing and/or firing of the CMC material in o... | 08/21/2007 |
| 7252480 | Methods for generation of dual thickness internal pack coatings and objects produced thereby A method for generating an internal pack coating having different, controlled thicknesses includes partially filling a root opening of a turbine blade having a cavity therein with a first powder and a second powder having different formulations so that the first pow... | 08/07/2007 |
| 7251888 | Hollow fan blade for aircraft engines and method for its manufacture A hollow fan blade for the fan of an aircraft engine includes a blade base section (2) and a blade tip section (5) which are assembled at opposing faying surfaces (6, 6′) by a joining process. Starting from the respective faying surface, cavit... | 08/07/2007 |
| 7204153 | Apparatus and a method for testing attachment features of components An apparatus (10) for testing attachment features (26,28,30,32) of components (12,14) comprises a first member (16) having a first end (18), a second end (20), a first edge (22) and a second edge (24). The firs... | 04/17/2007 |
| 7189064 | Friction stir welded hollow airfoils and method therefor A hollow component for gas turbine engine, for example an outlet guide vane, is assembled from a body having at recessed pocket formed therein, and an aerodynamic cover bonded over the pocket. Both the cover and the body are constructed from materials which are not ... | 03/13/2007 |
| 7153090 | System and method for passive load attenuation in a wind turbine In accordance with certain embodiments, a wind turbine blade includes an outer skin and an internal support structure. The skin has a closed airfoil shape and includes an outer surface, an inner surface, and opposite sides along a length of the blade. The internal s... | 12/26/2006 |
| 7118346 | Compressor blade A compressor blade (26) comprises an aerofoil (36) and a root (38). The aerofoil (36) comprises a concave wall (40) extending from a leading edge (44) to a trailing edge (46) and a convex wall (42) extending fr... | 10/10/2006 |
| 7112044 | Blades Percussive impacts due to bird strikes upon the hollow fan blades 20 are a well known problem. These percussive impacts not only deform previous fan blades but also reduce their stiffness. In accordance with the present invention, hollow fan blades 20 ... | 09/26/2006 |
| 7104762 | Reduced weight control stage for a high temperature steam turbine The control stage buckets for a steam turbine have airfoils which are hollowed out to form an interior cavity within the airfoil. The cavity opens through the radial inner platform of the bucket and terminates short of the tip of the bucket. The buckets are therefor... | 09/12/2006 |
| 7094445 | Dimensionally controlled pack aluminiding of internal surfaces of a hollow article An article such as a hollow gas turbine blade has an internal cavity therein with an inlet and outlet. The outlet has an outlet minimum transverse dimension of from about 0.009 inch to about 0.012 inch. An aluminiding source powder has a minimum particle size of gre... | 08/22/2006 |
| 7070390 | Component with internal damping A component such as a blade for use in a gas turbine engine comprises a body 2 formed from outer panels 8, 10 defining an internal cavity 12. A damping element 14 is provided in the cavity 12 and is secured at one end between the p... | 07/04/2006 |
| 7033131 | Fan blade for a gas-turbine engine For material reduction, a fan blade made of solid material for a gas-turbine engine is provided in the area of the blade tip with at least one cavity (5) extending from the face of the blade tip. Thus, apart from the aspect of weight saving, the vibration amp... | 04/25/2006 |
| 7029235 | Cooling system for a tip of a turbine blade A turbine blade for a turbine engine having at least one secondary flow deflector proximate to a blade tip for reducing the effective flow path between the blade tip and an adjacent outer seal. The turbine blade may be a superblade having a central opening forming a... | 04/18/2006 |
| 7021899 | Lightened turbomachine blade and its manufacturing process A turbomachine blade includes a metal alloy airfoil having a cavity closed off by a cover on a hollowed side, the cover providing aerodynamic continuity of the hollowed side and being bonded via an edge thereof to the rest of the airfoil by a weld bead. The weld bea... | 04/04/2006 |
| 7001150 | Hollow turbine blade stiffening An apparatus and method for at least one of stiffening a rotor blade of a gas turbine engine and raising a natural vibration frequency of the blade. The blade has a recess extending radially and inwardly into the blade. A reinforcing element is provided in the reces... | 02/21/2006 |
| 6997682 | Cool air circulation type axial flow fan for refrigerator Disclosed herein is a cool air circulation type axial flow fan for a refrigerator. The fan comprises a plurality of spaced blades mounted on the outer circumference of a hub for blowing cool air to a freezing chamber and a chilling chamber of the refrigerator. Sever... | 02/14/2006 |
| 6979173 | Turbine blade or vane A turbine blade or vane includes an inner contour profile which is matched to the contour profile of the outer transition region, so that a substantially uniform blade or vane wall thickness is achieved. ... | 12/27/2005 |
| 6979180 | Hollow component with internal damping A component, for example a fan blade for a gas turbine engine, comprises panels 2 and 4 which define between them a cavity containing a warren girder structure 6. Internal surfaces of the panels 2 and 4 are provided with a damping ... | 12/27/2005 |
