Did You Know...
...that the inventor of the electric motor was a blacksmith named Thomas Davenport? Described as "a brilliantly unsuccessful inventor", Davenport invented the first rotary electric motor. In 1836 he headed out -- on foot -- from his Vermont home to file a patent application at the Patent Office in Washington, D.C. By the time he got there, he had squandered away his money and couldn't afford the $30 filing fee so he turned around and went home. When he later mailed in his application with money he'd raised, the Patent office was destroyed in a fire. He did finally get credit for his invention on Feb. 5, 1837.
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| Number | Title | Issue Date |
| 8172522 | Method and system for supporting stator components A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static s... | 05/08/2012 |
| 8092163 | Turbine stator mount A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart ... | 01/10/2012 |
| 8033786 | Axial loading element for turbine vane A vane assembly for a gas turbine engine comprising an axial loading element disposed between a mounting element of the vane ring and a cooperating portion of the supporting structure, such as to generate a load force therebetween in an axial direction. The axial lo... | 10/11/2011 |
| 7854588 | Stamped torque converter stator blades and a torque converter stator with stamped blades The present invention broadly comprises a blade for a torque converter stator including a body, a first end, and a second end; a stator blade assembly; and a stator for a torque converter including a plurality of blades, a housing, and a core ring. The first end is ... | 12/21/2010 |
| 7704042 | Turbomachine, especially a gas turbine A turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (2... | 04/27/2010 |
| 7419352 | Methods and apparatus for assembling turbine engines A method for assembling a gas turbine engine is provided. The method includes providing a turbine nozzle including an outer band and an inner band, wherein each band includes a leading edge, a trailing edge, and a body extending therebetween. At least one of the out... | 09/02/2008 |
| 7413400 | Vane assembly with grommet A vane assembly for a gas turbine engine including a shroud ring with openings and isolating arrangement isolating a vane extremity within each opening, the isolating arrangement cooperating to form a continuous gas path surface completely covering at least an axial... | 08/19/2008 |
| 7374398 | Automotive compressor An automotive compressor is provided having a casing defining an intake section for fluid for compression, and a delivery section for delivering the compressed fluid. An impeller is movable angularly inside the casing to increase the pressure of the fluid. A distrib... | 05/20/2008 |
| 7374397 | Mounting device for fans A mounting device, for mounting a plurality of fans (50) to a server chassis (70), includes a tray (20), a plurality of brackets (30), and a plurality of fasteners (40). The tray includes a plurality of pairs of mounting sections e... | 05/20/2008 |
| 7341427 | Gas turbine nozzle segment and process therefor A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle... | 03/11/2008 |
| 7311495 | Vane support in a gas turbine engine A fluid flow machine comprises an array of vanes (2) which are supported at their ends by inner and outer support structures 4, 6. The ends of the vanes are received in slots 8, 10, with resilient material 12 disposed between the vane ... | 12/25/2007 |
| 7305905 | Rotatable member with an annular groove for dynamic balancing during rotation A rotatable member is adapted for dynamic balancing by the addition of balancing weights in the form of high speed projectiles fired at the member during rotation in timed relationship with the rotation of the member so as to impact the member at specific circumaxia... | 12/11/2007 |
| 7303371 | Gas turbine having a sealing element between the vane ring and a vane carrier of the turbine The invention relates to a gas turbine. The aim of the invention is to provide an axial sealing between a vane ring and a moving blade ring, which has an excellent sealing effect, is easy to install and inexpensive to produce. For this purpose, a sealing element is ... | 12/04/2007 |
| 7303372 | Methods and apparatus for cooling combustion turbine engine components A turbine nozzle cooling sub-system is provided. The sub-system includes at least one turbine nozzle segment. The segment includes an arcuate, radially outermost endwall, an arcuate, radially innermost endwall, and at least one airfoil vane. The endwalls each includ... | 12/04/2007 |
| 7300237 | Self-locking bolted fastener A bolted fastener for joining components, such as a bracket fastened to a crosspiece, includes a bolt, a nut and an eccentric. A square neck of a bolt fits into an oblong hole in a component and prevents the bolt from turning. The diameter of the eccentric that serv... | 11/27/2007 |
| 7300246 | Integrated turbine vane support A unitary component for retaining a vane ring in a gas turbine engine comprises a retaining plate portion to restrain axial vane movement, a retaining ring portion to restrain circumferential vane movement, and a baffle portion to split a cooling air flow between th... | 11/27/2007 |
| 7290982 | Arrangement for the attachment of distributor sectors supporting vanes around an arc of a circle The distributor sectors (25) of a turbomachine are secured adjacent to a casing (31) with sealing sectors (32) alternating with them in the axial direction. The distributor sectors (25) are provided with force resistant faces (37; 39 | 11/06/2007 |
| 7290983 | Turbine, fixing device for blades and working method for dismantling the blades of a turbine A turbine and a method for dismantling a blade of a turbine. A turbine includes a rotor that extends in an axial direction and an accessible combustion chamber, which communicates with an annular hot-gas conduit, in which a plurality of blades that form a blade row ... | 11/06/2007 |
| 7278821 | Methods and apparatus for assembling gas turbine engines A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within ea... | 10/09/2007 |
| 7238003 | Vane attachment arrangement A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing. ... | 07/03/2007 |
| 7229245 | Vane platform rail configuration for reduced airfoil stress A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their res... | 06/12/2007 |
| 7195453 | Compressor stator floating tip shroud and related method A stator blade segment for a compressor includes an inner ring segment and an outer ring segment and a plurality of stator blades extending radially between the inner and outer ring segments, the stator blade secured to the outer ring at a shank portion of the blade... | 03/27/2007 |
| 7172388 | Multi-point seal A spring seal for sealing a gap defined between first and second gas turbine engine components. The spring seal has a grasping portion for graspingly receiving a portion of the first component, and a spring loading portion adapted to extend between the first and sec... | 02/06/2007 |
| 7160078 | Mechanical solution for rail retention of turbine nozzles A mechanical arrangement for protection against catastrophic nozzle failures includes a turbine nozzle segment including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with the rail on one side, an inner retainer segment se... | 01/09/2007 |
| 7147434 | Nozzle ring with adhesive bonded blading for aircraft engine compressor Blades (3) extending radially from the inner shroud (1) to the outer shroud (2) are attached to the inner shroud by means of a sealing cement containing an organic polyimide-based polymer adhesive. ... | 12/12/2006 |
| 7144218 | Anti-rotation lock An anti-rotation lock for preventing circumferential movement of a stator segment in relation to a split case to which it is mounted is disclosed. A racetrack shaped pocket, disposed within the case and proximate the stator segment, is suitably sized to receive a lu... | 12/05/2006 |
| 7140835 | Corner cooled turbine nozzle A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore... | 11/28/2006 |
| 7140832 | Method and system for rotating a turbine stator ring A method for distributing effects of a circumferential hot streak condition in a turbine includes communicating a control signal to a rotator moving a stator ring with the rotator in response to the control signal. ... | 11/28/2006 |
| 7114920 | Shroud and vane segments having edge notches Random air flow leakage between a shroud assembly and a stator vane assembly into the gas path of a gas turbine engine due to manufacturing tolerance stack-up is reduced by providing notches to inhibit interference caused by misalignment and/or mismatch of adjacent ... | 10/03/2006 |
| 7112042 | Turbine nozzle support structure A turbine nozzle support structure supports a ceramic turbine nozzle provided with a flange and disposed at the inlet of a turbine on a nozzle support. Force-multiplying mechanism presses the flange of the turbine nozzle against a nozzle support to support the turbi... | 09/26/2006 |
| 7101147 | Sealing arrangement A sealing arrangement that can be employed to maintain a seal in any suitable pressure vessel including but not limited to a gas turbine engine. The sealing arrangement is forg sealing a leakage gap between at least two relatively moveable parts that are adjacent to... | 09/05/2006 |
| 7101150 | Fastened vane assembly A vane assembly for a gas turbine is described wherein the vane assembly comprises a first vane and a second vane connected together by a plurality of flanges, at least one fastener, and at least one spring plate. The fastener and hole diameters in the respective fl... | 09/05/2006 |
| 7094026 | System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor Arcuate seal layers conforming with one another are disposed between inner retainer segments and inner rails of nozzle segments of a gas turbine. The layers are secured to the aft axial face of the segments and project radially outwardly to seal against the forward ... | 08/22/2006 |
| 7094025 | Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction Nozzle segments are secured to a retention ring against circumferential rotation by anti-rotation pins extending generally axially between the outer bands of the nozzle segments and the retention ring. Retention plate segments overlie the ends of the pins, preventin... | 08/22/2006 |
| 7086830 | Tube-type vortex reducer with retaining ring A tube-type vortex reducer conducts cooling air in a compressor (1) of a gas turbine. Radial secondary air tubes (2) are arranged in a disk interspace (5) and attached to a compressor disk (3) with their radial outward end sections. The e... | 08/08/2006 |
| 7070387 | Gas turbine stator housing A housing including an outer casing provided with bearer hooks for stator rings and sealing rings. The hooks are discontinuous angularly and joined to a casing by tenon and mortise assemblies. The hooks and the casing may therefore be made in different materials, th... | 07/04/2006 |
| 7063505 | Gas turbine engine frame having struts connected to rings with morse pins A gas turbine engine strut segment includes a strut, which may be hollow, extending radially between co-annular radially inner and outer platforms, axially spaced apart inner platform flanges extending radially inwardly from the inner platform, and axially spaced ap... | 06/20/2006 |
| 7052235 | Turbine engine shroud segment, hanger and assembly A turbine engine shroud segment comprises a body including an outer surface from and along which a segment projection extends away from and in an axial direction. The segment projection includes circumferentially spaced apart segment support surfaces. A shroud hange... | 05/30/2006 |
| 7052237 | Turbine blade and turbine The pressure distribution curve of the blade suction-side surface excluding the leading edge portion and the trailing edge portion drops in two stages in the area from the leading edge to the minimum pressure point. ... | 05/30/2006 |
| 7048504 | Machine stator and mounting and dismounting methods A machine stator and assembly and disassembly methods. The elements of a casing portion are formed of consecutive shells in line with grooves configured to house roots of guide vane stages that are fixed in place by springs and pins for stopping rotation. The elemen... | 05/23/2006 |
