Quotables
"During my service in the United States Congress, I took the initiative in creating the Internet."
Al Gore ; The basis for the later misquote by US Republicans that Gore had "invented" the Internet. Gore was the leading political champion of the modern-day Internet.
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 |
| 8122727 | Compliant metal support for ceramic combustor liner in a gas turbine engine A combustion system for an engine, such as a gas turbine engine is provided. The combustion system has a ceramic component, such as ceramic combustor liner, and at least one metal support component, such as a metal ring or a plurality of metal cones, for providing r... | 02/28/2012 |
| 8104291 | Combustion cap floating collar using E-seal An improved floating collar assembly for gas turbine combustion units consists of a sheet metal collar with a flat flange and an E seal that is pre-compressed within a block of epoxy. The collar fits over a corresponding fuel nozzle burner tube and is retained on a ... | 01/31/2012 |
| 8099963 | Device for mounting an igniter plug in a combustion chamber of a gas turbine engine The present invention relates to a device for mounting an igniter plug in a combustion chamber of a gas turbine engine contained in a casing, in which the combustion chamber has an axis YY, the mounting device comprising a hollow shaft, of axis XX, a floating ignite... | 01/24/2012 |
| 8051664 | Pre-loaded internal fuel manifold support A system for mounting an internal fuel manifold within a gas generator case of a gas turbine engine includes at least one fastener support assembly having a fastener pin and at least one receiving element, respectively engaged to either the internal fuel manifold or... | 11/08/2011 |
| 7966832 | Combustor A combustor includes a first wall, a second wall, an injector grommet, a combustor longitudinal axis, and a connection assembly indirectly connecting the first wall to the second wall. A portion of the injector grommet is disposed within a groove of the connection a... | 06/28/2011 |
| 7958734 | Cover assembly for gas turbine engine rotor A cover assembly disposed about a rotor in a gas turbine engine. The cover assembly comprises a first cover, a second cover, and securing structure. The first cover is disposed about the rotor and comprises a forward end and an opposed aft end. The first cover is as... | 06/14/2011 |
| 7900461 | Combustor liner support and seal assembly The invention is a combination that includes a gas turbine engine extending along an axis. The gas turbine engine includes an annular combustor with a combustor liner. The combination of the invention also includes a plurality of projections extending from the combu... | 03/08/2011 |
| 7797948 | Transition-to-turbine seal apparatus and transition-to-turbine seal junction of a gas turbine engine A transition-to-turbine seal (320) including an upstream portion (322) adapted to engage a flange (416) of a transition (400). The upstream portion (322) may be U-shaped in cross-sectional profile and include a primary wall (324... | 09/21/2010 |
| 7757495 | Turbine engine annular combustion chamber with alternate fixings A turbine engine annular combustion chamber includes inner and outer longitudinal walls connected upstream by a transverse chamber bottom and including a single-piece cowling covering the chamber bottom. Each of the longitudinal walls is inserted between correspondi... | 07/20/2010 |
| 7757494 | Device for feeding fuel to a combustion chamber in a turbomachine A device for feeding fuel to a combustion chamber in a turbomachine, the device comprising both an annular fuel feed rail extending around an outer casing of the combustion chamber, and a plurality of injectors fixed to the casing and opening out into the combustion... | 07/20/2010 |
| 7752851 | Fastening a combustion chamber inside its casing A combustion chamber module includes a combustion chamber attached to a casing. The downstream end of the outer wall of the combustion chamber is secured to an annular connection part having fastener tabs directed in an upstream direction, each tab end being engaged... | 07/13/2010 |
| 7647779 | Compliant metal support for ceramic combustor liner in a gas turbine engine A combustion system for an engine, such as a gas turbine engine is provided. The combustion system has a ceramic component, such as ceramic combustor liner, and at least one metal support component, such as a metal ring or a plurality of metal cones, for providing r... | 01/19/2010 |
| 7617689 | Combustor dome assembly including retaining ring A retaining ring is provided for use in conjunction with a carburetor assembly having a flow passage therethrough for conducting a fuel-air mixture into a combustion chamber, the carburetor assembly comprising an air flow modifier and a fuel injector receiving eleme... | 11/17/2009 |
| 7591136 | Antirotation injection system for turbojet Injection system of a turbojet engine. It comprises a fixed part and a sliding crossmember. The sliding crossmember comprises a flange capable of sliding on the sliding surface of the fixed part. The fixed part comprises antirotation means and the sliding crossmembe... | 09/22/2009 |
| 7584621 | Radially expanding turbine engine exhaust cylinder interface Aspects of the invention are directed to an interface between an exhaust cylinder and an exhaust diffuser in a turbine engine. The interface allows relative radial movement of the exhaust diffuser and the exhaust cylinder. According to aspects of the invention, the ... | 09/08/2009 |
| 7377116 | Gas turbine combustor barrier structures for spring clips A barrier structure (302) blocks exit of spring clip fragments (317) that may break off from a spring clip assembly disposed between a gas turbine engine combustor (300) and a transition piece component (360). The barrier structure (30... | 05/27/2008 |
| 7360988 | Methods and apparatus for assembling turbine engines A method facilitates the assembly of a gas turbine engine. The method comprises providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands, wherein the vane includes a first sidewall and a sec... | 04/22/2008 |
| 7360364 | Method and apparatus for assembling gas turbine engine combustors A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled toge... | 04/22/2008 |
| 7350358 | Exit duct of annular reverse flow combustor and method of making the same A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbi... | 04/01/2008 |
| 7308794 | Combustor and method of improving manufacturing accuracy thereof An improved gas turbine engine combustor with a liner and a dome connected to the liner trough small radius transition portions only, the dome having a plurality of fuel nozzles mounted therein and an interior directly exposed to a combustion region of the combustor... | 12/18/2007 |
| 7302802 | Aerodynamic trip for a combustion system A apparatus and method for improving combustion by improving at least one of temperature distribution in the combustor, pressure distribution around the combustor and combustion noise level in the combustor, by redistributing air around the combustor to modify the s... | 12/04/2007 |
| 7290394 | Fuel injector flexible feed with moveable nozzle tip In a fuel injector assembly, for an internal combustion engine, a curved outer housing, fixed at one end, fully encloses a curved flexible fuel feed member, affixed to the housing inlet end and has a nozzle assembly operatively connected to an inner end, wherein the... | 11/06/2007 |
| 7278254 | Cooling system for a transition bracket of a transition in a turbine engine A heat shield for a transition of a turbine engine for coupling a transition component of a turbine engine to a turbine vane assembly to direct combustor exhaust gases from the transition into the turbine vane assembly. The heat shield may be capable of reducing the... | 10/09/2007 |
| 7270175 | Extended impingement cooling device and method An extended impingement cooling structure to cool outside an air supply plenum comprises an inner wall; an impingement sheet; a series of supports to maintain the inner wall in spaced relation to the impingement sheet, and a baffle supported between the inner wall a... | 09/18/2007 |
| 7269957 | Combustion liner having improved cooling and sealing A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness along the aft end of the combustion liner is improved, resulting in extended component life, while utilizing a simpler c... | 09/18/2007 |
| 7269958 | Combustor exit duct A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions. ... | 09/18/2007 |
| 7260936 | Combustor having means for directing air into the combustion chamber in a spiral pattern A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral patter... | 08/28/2007 |
| 7249461 | Turbine fuel ring assembly A turbine fuel ring assembly includes a fuel distribution ring, at least one fuel supply tube attached to the fuel distribution ring and at least one attachment leg connected to the fuel distribution ring. The fuel ring has a hollow interior and a plurality of apert... | 07/31/2007 |
| 7237389 | Attachment system for ceramic combustor liner Aspects of the invention relate to a system for attaching a ceramic liner to a non-ceramic combustor head-end component while accommodating different rates of thermal expansion of these components. One end of the liner can be received within a slot formed by the com... | 07/03/2007 |
| 7216489 | System and method for lightoff detection in turbine engines A system and method is provided for lightoff detection in a turbine engine that provides improved accuracy and consistency. The system and method use engine temperature and engine rotation speed sensor data to determine a first time interval during which the lightof... | 05/15/2007 |
| 7198304 | Fluid line connector with intermediate smooth surface A fluid line connector includes a length of tubing having a plurality of corrugations formed therealong between opposing tubing ends. A non-corrugated section is disposed along the length of tubing between the opposing tubing ends such that a portion of the pluralit... | 04/03/2007 |
| 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 |
| 7185499 | Device for passive control of the thermal expansion of the extension casing of a turbo-jet engine The invention relates to a device for passive control of the thermal expansion of the extension casing of a turbo-jet engine, said extension casing surrounding the casing of the high pressure compressor of the turbo-jet engine, and including a flange for attachment ... | 03/06/2007 |
| 7185498 | Modular gas turbine Method and arrangement for providing a gas turbine (1) having a duct (11) for carrying gas from a gas turbine inlet (9) to a gas turbine outlet (10) and an outer housing (19, 20, 21) arranged radially outside a wall structure (1... | 03/06/2007 |
| 7178340 | Transition duct honeycomb seal A sealing device for use between a gas turbine combustor transition duct aft frame and a turbine inlet having improved durability, reduced wear on the mating turbine vane, and reduced manufacturing costs, is disclosed. The sealing device has a circumferential length... | 02/20/2007 |
| 7163666 | Thermally tolerant support structure for a catalytic combustion catalyst The present invention provides a support structure for a catalyst disposed within an outer containment. Several unique arrangements and connections of supporting struts that form the structure provide a number of significant advantages and improvements. The support ... | 01/16/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7152411 | Rabbet mounted combuster A combustor includes an outer wall and an inner liner joined to an inner shell in turn mounted to an inner casing. The casing includes a first rabbet at an end flange in which is mounted a corresponding flange of the inner shell. The inner shell also includes a seco... | 12/26/2006 |
| 7146815 | Combustor A combustor heat shield panel is secured relative to a combustor shell so as to hold the panel exterior surface spaced apart from and facing the shell interior surface over major area of the panel exterior surface. A gap is formed between the heat shield exterior su... | 12/12/2006 |
| 7140840 | Turboshaft engine comprising two elements connected to each other with the interposition of a seal A turboshaft engine, such as for example a turbine, including a segmented seal between two longitudinally adjacent elements such as, for example, a casing and a ring of sectors of vanes. According to one embodiment, a seal is interposed between a casing and a ring o... | 11/28/2006 |
