Did You Know...
...that Kleenex tissue was originally designed to be a gas mask filter? It was developed at the beginning of World War I to replace cotton, which was then in short supply as a surgical dressing.
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 |
| 8096130 | Fuel conveying member for a gas turbine engine A gas turbine engine fuel conveying member in fluid flow communication with at least one fuel nozzle, the fuel conveying member having at least first and second member portions sealingly engaged to one another, and means for conveying fuel defined at a junction betw... | 01/17/2012 |
| 8096131 | Fuel inlet with crescent shaped passage for gas turbine engines An inlet tube within a gas turbine engine which includes a primary fuel channel and a secondary fuel channel formed in a cylindrical tube body. The secondary channel has a substantially crescent shaped cross-sectional area which is complementary in shape to the prim... | 01/17/2012 |
| 8074452 | Nested channel ducts for nozzle construction and the like A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at ... | 12/13/2011 |
| 8047002 | Annular combustion chamber of a gas turbine engine The present invention relates to an annular combustion chamber of a gas turbine engine comprising a casing with at least one air tapping outlet situated at the chamber inlet, a fuel supply device with a plurality of fuel injectors in the chamber distributed annularl... | 11/01/2011 |
| 8037690 | Fuel manifold for gas turbine engine A fuel manifold for a gas turbine engine comprises manifold adaptors each supporting a nozzle for outputting fuel from a fuel supply. The manifold adaptors have a primary conduit and a secondary conduit extending between connection ends of the manifold adaptor. The ... | 10/18/2011 |
| 8024931 | Combustor for turbine engine A turbine engine includes an annular combustor having a combustion chamber defined between an annular outer wall and an annular inner wall. A diffuser case substantially encloses the annular outer and inner walls. A fuel nozzle extends through the diffuser case to a... | 09/27/2011 |
| 7942002 | Fuel conveying member with side-brazed sealing members A gas turbine engine fuel nozzle system having a fuel conveying member with a channel formed in a surface thereof defined between a pair of facing spaced apart walls, and at least one sealing member disposed within the channel and sealingly fastened to the spaced ap... | 05/17/2011 |
| 7856825 | Redundant mounting system for an internal fuel manifold A mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener enga... | 12/28/2010 |
| 7854120 | Fuel manifold with reduced losses A fuel conveying member of a gas turbine engine fuel system conducting pressurized fluid flow is provided. The fuel conveying member comprises a body defining an L-shaped fuel flow passage therein, the L-shaped passage including an elbow. The elbow portion provides ... | 12/21/2010 |
| 7788927 | Turbine engine fuel nozzles and methods of assembling the same A method for assembling a fuel nozzle for a turbine engine is provided. The method includes coupling a one-piece housing to a one-piece venturi wherein the housing defines an annular fuel nozzle tip and the venturi defines a fuel chamber within the fuel nozzle tip. ... | 09/07/2010 |
| 7775047 | Heat shield with stress relieving feature A heat shield for a fuel member of a gas turbine engine having at least one heat shield segment having a connection edge with at least one joint receiving portion defined therealong for receiving a welded joint attaching the heat shield segment to a fuel member, eac... | 08/17/2010 |
| 7765808 | Optimized internal manifold heat shield attachment A fuel manifold assembly for a gas turbine engine includes an annular fuel manifold having at least one fuel conveying passage and defining at least one slow fuel flowing location. A heat shield at least partly encloses the fuel manifold and a plurality of intermitt... | 08/03/2010 |
| 7743612 | Internal fuel manifold and fuel inlet connection An internal fuel manifold assembly for a gas turbine engine comprises a fuel manifold ring and a fuel inlet assembly fastened thereto. The fuel inlet assembly providing fluid flow communication with the fuel manifold ring and being joined to the fuel manifold ring a... | 06/29/2010 |
| 7721546 | Gas turbine internal manifold mounting arrangement A mounting system for an annular internal fuel manifold of a gas turbine engine includes three supports equally spaced apart about the annular fuel manifold, the three supports having at least two pin supports disposed between the fuel manifold and a surrounding gas... | 05/25/2010 |
| 7654088 | Dual conduit fuel manifold for gas turbine engine Fuel conduit systems for internal installation in a gas turbine engine are provided which are low cost and easy to manufacture. First and second members co-operate to provide a channel to define a discrete fuel carrying conduit. The direction of fuel flow can be ada... | 02/02/2010 |
| 7617683 | Fuel nozzle and manifold assembly connection A fuel supply assembly for a gas turbine engine including a manifold portion with a transfer conduit, a fuel nozzle with an entry conduit and disconnectable means for retaining the transfer and entry conduits in mating engagement with one another. ... | 11/17/2009 |
| 7568344 | Hydrostatic flow barrier for flexible fuel manifold A fuel manifold segment (34) for gas turbine engines comprises a polymer tube (48) surrounded by a metallic braid layer (50). A hydrostatic flow barrier (56) is provided for preventing the polymer material of the tube (48) from flo... | 08/04/2009 |
| 7559201 | Redundant fuel manifold sealing arrangement A fuel manifold of gas turbine engines comprises a tube for fluid communication with a fuel source and for connection with at least one fuel nozzle tip to thereby define a fuel conveying passage. A redundant seal is provided around the tube and covers substantially ... | 07/14/2009 |
| 7533531 | Internal fuel manifold with airblast nozzles A gas turbine engine internal fuel manifold assembly including an annular fuel distribution member defining at least one fuel flow passage therein, and a plurality of fuel nozzles having spray tips mounted to the fuel distribution member. the spray tips are in fuel ... | 05/19/2009 |
| 7451599 | Fuel manifold inlet tube An inlet tube supplies fuel to a manifold of a combustor in a gas turbine engine, the manifold defining a manifold plane. The inlet tube comprises a tube body having a channel providing fluid flow communication between first and second ends of the tube body. At leas... | 11/18/2008 |
| 7434404 | Method for operating a gas turbine combustion chamber including a plurality of burners arranged in groups A method for operating a combustion chamber (1) for a gas turbine. The combustion chamber (1) has a combustion space (2) and a plurality of burners (3), which are each arranged at an inlet (13) of the combustion space (2). T... | 10/14/2008 |
| 7320212 | Side-fed shielded internal fuel manifold inlet tube In a gas turbine engine, a fuel inlet tube comprising a body, a channel defined in the body and in fluid communication with a manifold, and a side inlet in fluid communication with the channel, such that fuel entering the side inlet is delivered to the manifold thro... | 01/22/2008 |
| 7305830 | Fuel manifold inlet tube In a gas turbine engine, a fuel inlet tube comprising a body, a channel defined in the body and in fluid communication with a manifold, and a side inlet in fluid communication with the channel, the side inlet being sealingly isolated by at least two annular sealing ... | 12/11/2007 |
| 7287382 | Gas turbine combustor end cover An end cover for a gas turbine combustor that eliminates the use of braze joints within the plate portion of the end cover is disclosed. The end cover comprises a plate and a plurality of fluid inlets with the fluid inlets directing fluids to first and second manifo... | 10/30/2007 |
| 7277801 | Method for testing catalytic converter durability The present application relates in general to methods for testing the performance of an automotive catalytic converter under conditions simulating those which occur in motor vehicles over extended driving conditions. ... | 10/02/2007 |
| 7269939 | Method and apparatus for automatically actuating fuel trim valves in a gas A gas turbine combustion system having: a plurality of combustion chambers; a plurality of fuel nozzles for each of combustion chamber; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion chambers; each of the manifolds ... | 09/18/2007 |
| 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 |
| 7197879 | Multiple electric fuel metering systems for gas turbine applications The present invention provides a multiple manifold fuel metering system with a separate motor, pump, and shut-off/purge valve for each manifold. The present invention may be used for metering fuel to any engine, especially a gas turbine engine. The fuel metering sys... | 04/03/2007 |
| 7188465 | Method and apparatus for actuating fuel trim valves in a gas turbine The gas turbines of the present invention have multiple combustion chambers, and within each chamber are multiple fuel nozzles. Each nozzle has its own fuel control valve to control the fuel flowing to the nozzles. To minimize the pressure drop through the fuel cont... | 03/13/2007 |
| 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 |
| 7137256 | Method of operating a combustion system for increased turndown capability A method of operating a gas turbine engine combustion system at lower load conditions while maintaining required emissions levels is disclosed. The present invention includes multiple embodiments of axial, radial, and circumferential fuel staging within a can-type c... | 11/21/2006 |
| 7124588 | Combustion chamber of gas turbine with starter film cooling A combustion chamber of a gas turbine includes starter film cooling of a combustion chamber wall 4 and several circularly arranged burners 7 with local maxima and minima in the intensity of the starter film 3 being provided around the circumfere... | 10/24/2006 |
| 7107771 | Method for introducing fuel into a premix burner A method and a device for the introduction of fuel into a premixing burner, with a pilot gas feed and a premix gas feed for the operation of a gas turbine in the entire load range, in which the pilot gas feed is carried out via a burner lance provided in the premixi... | 09/19/2006 |
| 7107772 | Multi-point staging strategy for low emission and stable combustion The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further ha... | 09/19/2006 |
| 7093419 | Methods and apparatus for operating gas turbine engine combustors A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combus... | 08/22/2006 |
| 7065972 | Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions A fuel-air mixer for use in a combustion chamber of a gas turbine engine is provided. The fuel air mixing apparatus comprises an annular fuel injector having a plurality of discrete plain jet orifices, a first swirler wherein the first swirler is located upstream fr... | 06/27/2006 |
| 7028484 | Nested channel ducts for nozzle construction and the like A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel is formed in a surface of a gas turbine engine component, and the channel is adapted for conveying a fluid flow from... | 04/18/2006 |
| 7024862 | System and method for controlling combustion in gas turbine with annular combustor A gas turbine system composed of a gas turbine engine and a controller. The gas turbine engine includes an annular combustor, and a turbine driven by combustion gas from the annular combustor to rotate on a longitudinal centerline axis of the gas turbine engine. The... | 04/11/2006 |
| 7007476 | Gas turbine fuel system staging valves In a fuel injector circuit for a gas turbine engine, a fuel staging valve assembly for distributing fuel into multiple zones in the combustor, the staging valve assembly, including a pilot valve operatively interconnected with at least one main valve, having high pr... | 03/07/2006 |
| 7003939 | Method for the adaption of the operation of a staged combustion chamber for gas turbines This invention relates to a fuel injection system for a staged combustion chamber (1) of a gas turbine aero-engine, in which a certain quantity of fuel is permanently supplied to the pilot burner(s) (3) and in which fuel is apportioned to the main burn... | 02/28/2006 |
