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| Number | Title | Issue Date |
| 7571598 | Plasma torch for ignition, flameholding and enhancement of combustion in high speed flows Preheating of fuel and injection into a plasma torch plume fro adjacent the plasma torch plume provides for only ignition with reduced delay but improved fuel-air mixing and fuel atomization as well as combustion reaction enhancement. Heat exchange also reduced eros... | 08/11/2009 |
| 7370478 | Method of controlling a gas combustor of a gas turbine A gas combustor has a peripheral premix burner, and a central diffusion burner whose nozzle defines an eccentric first channel housing an ignition device, an axial second channel, and a third channel interposed radially between the first and second channel; the gas ... | 05/13/2008 |
| 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 |
| 7334409 | Retractable afterburner for jet engine The present invention is a retractable afterburner shroud for use upon a jet engine. The retractable shroud conforms to an outer surface of a jet engine. The afterburner shroud is affixed by a plurality of moveable support arms. The afterburner shroud is retractable... | 02/26/2008 |
| 7299620 | Tornado torch igniter An ignition system having improved reliability for a gas turbine combustor is disclosed. The ignition system comprises an outer housing having at least one fuel passage and an electrode extending therethrough forming a generally annular passage for cooling air to pa... | 11/27/2007 |
| 7111463 | Combustion wave ignition for combustors A system, such as a turbine power production system, including a plurality of combustion chambers. The combustion chamber may be provided with an ignition system that allows for substantially simultaneous ignition of each of the plurality of the combustors. Generall... | 09/26/2006 |
| 7096670 | Method for igniting the combustion chamber of a gas turbine unit and an ignition device for carrying out the method In a method for igniting the combustion chamber of a gas turbine unit, a safely working ignition and a long lifetime of the ignition device (10) is achieved by discharging a compressed gas with a supercritical pressure ratio through a nozzle (21) and h... | 08/29/2006 |
| 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 |
| 7065956 | Two piece jet engine igniter assembly A two-piece jet engine igniter assembly includes a front section and a rear section. When the igniter assembly is installed in an aircraft, either the front section or the rear section is removable for service or replacement. The front section includes a detachable ... | 06/27/2006 |
| 7047722 | Small scale hybrid engine (SSHE) utilizing fossil fuels This invention describes a miniaturized hybrid diesel-electric engine formed by a closed-loop system powered by plasma-aided combustion of JP-8 fuel (or other hydrocarbon fuels) working in tandem with a vapor cycle utilizing miniaturized expanders and condensers. Th... | 05/23/2006 |
| 6964171 | Method and apparatus using jets to initiate detonations This invention pertains to apparatus and method for initiating detonation in a chamber of tubular or other shapes, which can be a combustor for a propulsion engine, such as a pulse detonation engine. This invention is characterized by detonation initiation at high p... | 11/15/2005 |
| 6925810 | Gas turbine engine transition liner assembly and repair A method of repairing a damaged combustion gas transition liner for a gas turbine engine and an improved damage-resistant transition liner that mounts adjacent to the edge of one of the engine's combustion chambers. In a particular embodiment, the gas turbine engine... | 08/09/2005 |
| 6912857 | Torch igniter An improved torch igniter for use in devices such as thrust augmenters, gas turbine engines, ramjets, combined-cycle engines and industrial burners. The torch igniter includes a housing with a combustion chamber. Fuel and oxidizer are delivered into the combustion c... | 07/05/2005 |
| 6821113 | Precombustion chamber for an ic engine and electrode assembly for producing combustion in one part of the precombustion chamber An assembly includes a precombustion chamber and electrode, for producing the ignition and combustion of a fuel while maintaining the flame temperature below a predetermined value, and keeping the flame front (F) in the proximity of an aperture of the precombustion ... | 11/23/2004 |
| 6748735 | Torch igniter An improved torch igniter for use in devices such as thrust augmenters, gas turbine engines, ramjets, combined-cycle engines and industrial burners. The torch igniter includes a housing with a combustion chamber. Fuel and oxidizer are delivered into the combustion c... | 06/15/2004 |
| 6718773 | Method for igniting a thermal turbomachine In a method for igniting a thermal turbomachine, the turbomachine containing a combustion chamber (30), an ignition device (10), a fuel supply (60) and an air supply (70), and the ignition device (10) consisting of an ignition spac... | 04/13/2004 |
| 6668557 | Pilot nozzle of gas turbine combustor A pilot nozzle of a gas turbine combustor comprises a first structure, provided near a main nozzle of a combustor that injects fuel oil, having a flow channel for a fuel gas and an outlet for the fuel gas. The first structure diffusion-injecting the fuel ... | 12/30/2003 |
| 6564542 | Ignition system for combustion chambers of rocket engines An ignition system for combustion chambers of rocket engines has a first fuel tank for a first fuel constituent and a second fuel tank for a second fuel constituent, both of which are separated from the fuel tanks of the rocket engine. Feed pipes (3, 4) f... | 05/20/2003 |
| 6553769 | Method for providing concentricity of pilot fuel assembly in a combustor Concentric installation of a pilot fuel assembly in an opening in a gas turbine combustor casing is achieved by providing a boss having at least two flat surfaces which are perpendicular to each other on the combustor casing surrounding the opening and a ... | 04/29/2003 |
| 6530223 | Multi-stage radial axial gas turbine engine combustor A combustor for a gas turbine engine having a longitudinal axis therethrough, including an outer liner having a forward end and an aft end, an inner liner having a forward end and an aft end, a first dome formed upstream of the outer liner forward end so ... | 03/11/2003 |
| 6244041 | Liquid-propellant rocket engine chamber and its casing The invention relates to rocket engine manufacturing, and may also be used in aircraft engine manufacturing. A chamber comprises a casing, ignition means and a mixing head. The mixing head consists of an internal injector face, a middle bottom, an externa... | 06/12/2001 |
| 6182436 | Porus material torch igniter The igniter for the combustor in a gas turbine engine includes a tubular member extending beyond the igniter tip, wherein the tubular member is a porous ceramic or high temperature nickel alloy. Fuel is fed to the bore of the tubular member by capillary a... | 02/06/2001 |
| 6148603 | Method of operating a gas-turbine-powered generating set using low-calorific-value fuel In a method of operating a gas turbine group with low calorific value fuel, the gas turbine group essentially comprises a compressor, a combustion chamber, a turbine and a generator. The low calorific value fuel is compressed by means of a fuel compressor... | 11/21/2000 |
| 6082098 | Ignition system for rocket engines An ignition system for a rocket engine which improves the reliability of engine re-ignition by supplying additional oxygen to the ignitor directly from the rocket engines main fuel/oxygen injector elements, thereby eliminating the need for a supplemental ... | 07/04/2000 |
| 5901555 | Gas turbine combustor having multiple burner groups and independently operable pilot fuel injection systems In a gas turbine combustor of the present invention, a pilot fuel nozzle is composed of at least two systems with different hole diameters, and the fuel flow rate of each system can be controlled independently. Also, even if the operation of main burners ... | 05/11/1999 |
| 5735115 | Gas turbine combustor with means for removing swirl The invention relates to a combustion chamber (6) for a gas turbine (6, 18, 19) through which a flow (2) of compressed air is allowed to pass, flowing along an axis (3) from a compressor part (18) to a turbine part (19), said flow (2) having a swirl relat... | 04/07/1998 |
| 5640841 | Plasma torch ignition for low NOx combustion turbine combustor with monitoring means and plasma generation control means A low NOx combustion turbine combustor which utilizes an electric are plasma torch to heat natural gas or another fuel to a sufficiently high temperature to create a plasma which is injected into a combustor causing the auto-ignition and sustai... | 06/24/1997 |
| 5636511 | Torch assembly The conventional gas turbine combustor is improved by mounting a pilot flame producing torch in a wall of the combustor to project a flame into the combustor as a means of ignition. The torch preferably is a catalytic igniter which will operate over a wid... | 06/10/1997 |
| 5628180 | Ignition methods and apparatus for combustors Apparatus for igniting fuel in a combustor includes an injector having an electrostatic fuel atomization nozzle and an igniter. The injector produces an initial combustion process that ignites the main fuel supply from a fuel nozzle. Alternatively, a main... | 05/13/1997 |
| 5590517 | Ignition methods and apparatus for combustors Apparatus for igniting fuel in a combustor includes an injector having an electrostatic fuel atomization nozzle and an igniter. The injector produces an initial combustion process that ignites the main fuel supply from a fuel nozzle. Alternatively, a main... | 01/07/1997 |
| 5588299 | Electrostatic fuel injector body with igniter electrodes formed in the housing Apparatus for igniting fuel in a combustor includes an injector having an electrostatic fuel atomization nozzle and an igniter. The injector produces an initial combustion process that ignites the main fuel supply from a fuel nozzle. Alternatively, a main... | 12/31/1996 |
| 5385015 | Augmentor burner The fuel spray bars and a compressor air bar is disposed in the cavities of the extended vanes of the turbine exhaust case to flow a fuel/air mixture perpendicular to the gas path and the pilot burner encased in the tail cone ejects a hot stream of combus... | 01/31/1995 |
| 5263325 | Low NOx combustion A burner for a gas turbine combustor has a perforated plate facing the combustor and a plurality of gaseous fuel premixing tubes conveying a lean premixed fuel through the plate. A gas pilot extending through the plate projects jets of fuel parallel to th... | 11/23/1993 |
| 5127229 | Gas turbine combustor A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired,... | 07/07/1992 |
| 5081844 | Combustion chamber of a gas turbine In an annular combustion chamber (A), a row of premixed burners (B, C) are located in the peripheral direction at the inlet end. The large premixed burners (B), which are the main burners of the annular combustion chamber (A), and the small premixed burne... | 01/21/1992 |
| 5027603 | Turbine engine with start injector Improved fuel atomization for turbine engines operating at low fuel flows and at high altitudes is accomplished in an engine having an annular combustor 26 by utilizing start fuel injectors 46 provided with discharge orifices 56 and planar impingement sur... | 07/02/1991 |
| 4967563 | Turbine engine with high efficiency fuel atomization Excellent fuel atomization in a turbine engine may be obtained with fuel injectors 46 including elongated, laminar discharge orifices 72 and impingement surfaces 76 disposed in the path of fuel 78 being discharged through the discharge orifices 72. Prefer... | 11/06/1990 |
| 4946384 | Gas pilot-igniter for burners A gas pilot-igniter is used for igniting combustible gases in a burner, particularly high velocity gas streams. The gas pilot-igniter includes an air inlet manifold for supplying air under pressure to a mixing venturi, a fuel gas manifold for directing fu... | 08/07/1990 |
| 4944153 | Burner for hard-to-ignite mixtures A burner for hard-to-ignite mixtures, such as with exhaust gases of an internal combustion engine, in which an ignitable mixture is prepared in a locally limited area for producing an ignition flame that is then used for igniting the hard-to-ignite mixtur... | 07/31/1990 |
| 4860533 | Torch igniter for a combustor having U.V. flame detection A gas turbine combustor is ignited by a torch igniter. The ignition chamber of the torch igniter receives a swirled stream of air into which is injected atomized fuel. The mixture of fuel and air is ignited by a spark plug in the ignition chamber. The com... | 08/29/1989 |
