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| Number | Title | Issue Date |
| 8186165 | Turbine fuel nozzle having heat control In one embodiment, a system includes a turbine engine fuel nozzle having an air path, a fuel path, and a surface along the air path. The fuel path may be directed toward the surface. The turbine engine fuel nozzle also may include a heating element configured to hea... | 05/29/2012 |
| 7669420 | Fuel injector having an annular prefilmer A fuel injector for a gas turbine engine has a swirl slot that supplies fuel to a prefilmer. The swirl slot has an upstream lip and a downstream lip that are arranged eccentrically. The slot is thus provided with an area of high static pressure and an area of low st... | 03/02/2010 |
| 7434401 | Fuel/air premixer for gas turbine combustor A fuel/air premixer for use in a gas turbine improves the atomization performance and mixing performance of the fuel by guiding an air so as to flow in an outward radial direction. A flow-deflecting tubular body having an annular cross section is disposed on the ins... | 10/14/2008 |
| 7266945 | Fuel injection apparatus A fuel injection apparatus (10) for a gas turbine engine (110) comprising a prefilmer (26), the prefilmer (26) comprises a body (50), the body (50) defines an axis (51), an annular surface (40) and a downstream... | 09/11/2007 |
| 7174717 | Helical channel fuel distributor and method The present invention includes a fuel distributor for a fuel nozzle in a gas turbine engine comprising an inner tubular body and an outer tubular body respectively having an outer body inner surface and an inner body outer surface adapted to be in sealing contact on... | 02/13/2007 |
| 7140184 | Fuel injection method and apparatus for a combustor A combustor and injector system to inject a selected fuel into a combustor of a gas powered turbine. Generally, the injector is able to inject a selected fuel into a stream of an oxidizer to substantially mix the fuel with the oxidizer stream before any of the fuel ... | 11/28/2006 |
| 7134286 | Gas turbine floating collar arrangement A simplified floating collar mounting arrangement for receiving a fuel nozzle swirler body of a gas turbine engine combustor is provided. The assembly comprises a floating collar mounted between a spaced-apart mounting flange and cap, and slidably trapped therebetwe... | 11/14/2006 |
| 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 |
| 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 |
| 6993916 | Burner tube and method for mixing air and gas in a gas turbine engine A hybrid structure that combines characteristics of the DACRS and Swozzle burners to provide the high mixing ability of an axial flowing counter rotating vane swirler with good dynamic flame stability characteristics of a bluff center body. ... | 02/07/2006 |
| 6968692 | Fuel premixing module for gas turbine engine combustor A fuel-air premixing module is designed to reduce emissions from a gas turbine engine. In one form, the premixing module includes a central pilot premixer module with a main premixer module positioned thereround. Each of the portions of the fuel-air premixing module... | 11/29/2005 |
| 6945053 | Lean premix burner for a gas turbine and operating method for a lean premix burner A lean premix burner for a gas turbine having at least one fuel supply ring 4 fitted with primary fuel nozzles 8 and additional secondary fuel nozzles 9, and a method of operation for this lean premix burner. ... | 09/20/2005 |
| 6925812 | Rotary injector A radially-extending arm is adapted to rotate within a stream of first fluid flowing thereacross. In one embodiment, the arm comprises a plurality of lands located at different radial distances from the axis of rotation, and a port located on each land is operativel... | 08/09/2005 |
| 6820425 | Fuel injection system with multipoint feed A system for injecting an air/fuel mixture into a combustion chamber of a turbomachine, the system having an injector comprising: an axial internal volume opening out at one end via an axial outlet for the air/fuel mixture; a first fuel feed stage having a plurality... | 11/23/2004 |
| 6820424 | Combustor module A combustor module includes a pre-vaporizing chamber defined by an inner wall, and an outer wall, and a heat shield. The heat shield separates the pre-mixing zone from the reaction zone of the combustor. At least one fueling nozzle is disposed in the pre-vaporizing ... | 11/23/2004 |
| 6786430 | Liquid atomizing nozzle This invention provides a liquid atomizing nozzle which utilizes a swirling flow of gas to form a liquid film in as uniform thickness as possible in a circumferential direction, and in which blockages are difficult to develop, and which can facilitate atomization by... | 09/07/2004 |
| 6532728 | Reducing skin friction drag The skin friction drag acting on a surface of an article travelling at high speed such as a vehicle at supersonic or particularly hypersonic speed can be reduced by introducing a fuel into the boundary layer under conditions of the fuel introduction to en... | 03/18/2003 |
| 6418723 | Low pressure gaseous fuel system A low pressure fuel system for a gaseous fuel internal combustion engine in which the source of gaseous fuel is at a pressure lower than the intake manifold pressure of the internal combustion engine. The gaseous fuel is inducted into the interstage duct ... | 07/16/2002 |
| 6401445 | Electrolysis system and method for improving fuel atomization and combustion An atomization system that includes a flow conduit for flowing a fuel/non-fuel mixture to a downstream object of interest. The flow conduit defining a flow chamber, a downstream end, and an upstream end. An electrolysis system is located in the chamber pr... | 06/11/2002 |
| 6244051 | Burner with atomizer nozzle The invention relates to a burner for combustors of gas turbines, the burner having an atomizer nozzle for atomisation of fuel in the combustion air and having a primary and secondary flow channel. In the burners, mostly used in aircraft engines, an exten... | 06/12/2001 |
| 6189314 | Premix combustor for gas turbine engine A premixing section for supplying a fuel-air mixture to a homogeneous combustion chamber includes a first fuel nozzle disposed along an axis, a second fuel nozzle disposed to surround the outer periphery of the first fuel nozzle, and a premixing/pre-evapo... | 02/20/2001 |
| 5918465 | Flow guiding body for a gas turbine combustion chamber A flow-guiding body is designed as a pointed, substantially conical molded shell. The projection of its base surface is formed by a straight line and by a curve that interconnects the ends of the straight line. The curve forms no significant angles. The m... | 07/06/1999 |
| 5857339 | Combustor flame stabilizing structure A combustor structure is described which comprises a cavity defined in the combustor for trapping a vortex of fuel, air and hot combustion products to stabilize the flame, the cavity being formed in any suitable way such as being defined between two or mo... | 01/12/1999 |
| 5609030 | Combustion chamber with temperature graduated combustion flow In the case of a combustion chamber which is respectively arranged upstream of and downstream of a fluid-flow machine and which essentially comprises an inflow duct (5) and a downstream premixing and combustion zone (5a), a fuel (11) is injected into the ... | 03/11/1997 |
| 5575153 | Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer A plurality of turbulence promotors (11) are arranged on a surface of a stabilizer (11) comprising a stabilizer portion (14) contacting combustion gas and support portion (15) for rectifying flow except for a heat receiving surface (13) contacting with co... | 11/19/1996 |
| 5461865 | Tangential entry fuel nozzle A premix liquid fuel nozzle has longitudinal air entrance slots (24) into a cylindrical chamber (20). A centerbody (42) produces an axially increasing flow area toward the chamber outlet (32). Liquid fuel is atomized in a specified location (58) adjacent ... | 10/31/1995 |
| 5437158 | Low-emission combustor having perforated plate for lean direct injection Lean direct injection is used in a gas turbine combustor to reduce NOx emissions. The combustor has a multi-hole perforated plate disposed at the head end of the combustion chamber. The plate has a plurality of independent fuel jets and air jet... | 08/01/1995 |
| 5341645 | Fuel/oxidizer premixing combustion chamber A fuel/oxidizer pre-mixing combustion chamber for a turbojet engine is disclosed in which the pre-mixing device is incorporated into the upstream end wall structure of the combustion chamber. The upstream end portion of the combustion chamber, which is in... | 08/30/1994 |
| 5328355 | Combustor and combustion apparatus In a combustor including a premixing type combustion burner which has an atomizer for ejecting a liquid fuel together with combustion air to atomize the liquid fuel, the atomizer is comprised of an inner shell to an inner peripheral surface of which the l... | 07/12/1994 |
| 5311742 | Gas turbine combustor with nozzle pressure ratio control A gas turbine combustor for a gas turbine power plant comprises a combustion liner connected to a turbine and provided with a main fuel nozzle assembly and a sub-fuel nozzle assembly for jetting fuel to an inside of the combustion liner through nozzle hol... | 05/17/1994 |
| 5307634 | Premix gas nozzle A premix gas nozzle has longitudinal tangential entrance slots to a cylindrical chamber. There is an axially increasing flow area toward the chamber outlet, with pilot fuel centrally introduced near the outlet. A lean mix low NOx fuel nozzle is thereby st... | 05/03/1994 |
| 5277022 | Air blast fuel injecton system In order to enhance fuel injection efficiency, and particularly to atomize low fuel flows at high velocity with low fuel pressure, a fuel injection system 24 for a combustor 22 of a turbine engine 20 has an air blast tube 48 and a fuel supply tube 76. The... | 01/11/1994 |
| 5265425 | Aero-slinger combustor A combustor includes radially spaced apart outer and inner liners joined together at upstream ends through an annular dome disposed coaxially about a longitudinal centerline axis. A plurality of circumferentially spaced apart fuel injectors are disposed a... | 11/30/1993 |
| 5263316 | Turbine engine with airblast injection Improved fuel atomization for turbine engines utilizing high viscosity fuels is accomplished in an engine having an annular combustor (26) by providing an air injector (52) which produces an air stream (50) generally tangentially directed into the combust... | 11/23/1993 |
| 5261239 | Lean premixture combustion-chamber comprising a counterflow enclosure to stabilize the premixture flame A combustion chamber suitable for use in a gas turbine engine includes a first enclosure with a fuel injector for low-power operation and a primary-oxidizer intake, a second enclosure with a fuel injector for full-power operation and a primary-oxidizer in... | 11/16/1993 |
| 5241818 | Fuel injector for a gas turbine engine Difficulties with fuel atomization at low fuel flow rates in gas turbine fuel injection systems may be overcome by use of an impingement injector (52) including a cylindrical orifice (64, 94, 114) that is smooth, straight and uninterrupted by burrs or oth... | 09/07/1993 |
| 5233825 | Tangential air blast impingement fuel injected combustor In order to efficiently atomize a fuel/air mixture to reduce smoke, a fuel injection system (26) for a combustor (12) of a turbine engine (10) includes an air blast tube (16), a fuel supply passage (42), and an impingement surface (30). The air blast tube... | 08/10/1993 |
| 5220794 | Improved fuel injector for a gas turbine engine The high cost of fuel injection nozzles for a gas turbine engine may be reduced by utilizing nozzles (60) formed of simple tubes (63) of capillary cross section having an integral flange (62) formed on one end (86) thereof.... | 06/22/1993 |
| 5167122 | Fuel system for a turbo machine Complexity in a fuel injection system for a gas turbine engine including an annular combustor (26) may be reduced by utilizing a plurality of circumferentially spaced fuel injectors (46) within the annular combustion (26). First and second conduit branche... | 12/01/1992 |
| 5150569 | Integrated propulsion system A propulsion system comprises a gas turbine engine having sructurally integrated support systems that maximize structural efficiency and minimize cost.... | 09/29/1992 |
