| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060739000 | With fuel supply manifold for separate injectors | 42 |
| 20090107148 | 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 annularly of which at least one is situated close to said tapping outlet. | 04-30-2009 |
| 20090126368 | FUEL INJECTION SYSTEM FOR A GAS TURBINE ENGINE - A fuel injection system comprises a fuel conveying member and a nozzle tip assembly threadably engaged thereto. A pair of sealing elements is engaged in a fuel passage between the fuel conveying member and the nozzle tip for sealing the junction therebetween. The pair of sealing elements includes a first and a second sealing element located proximate each other and having different cross-sectional shape. | 05-21-2009 |
| 20090178411 | FUEL NOZZLE ENCLOSURE - An enclosure assembly for enclosing a portion of a fuel delivery system of an engine, such as a portion of a fuel nozzle body that extends away from the engine, is disclosed herein. The enclosure assembly includes a nozzle body cover portion operable to enclose a fuel nozzle body. The enclosure assembly also includes a fuel line cover portion unitary with the nozzle body cover portion and operable to enclose a portion of a fuel supply line connected to the fuel nozzle body. Both the nozzle body cover portion and the fuel line cover portion are defined by a first and second half-shells operable to cooperate together in a clam shell arrangement. | 07-16-2009 |
| 20090199562 | INTERNALLY MOUNTED FUEL MANIFOLD WITH SUPPORT PINS - An apparatus for internally mounting a fuel manifold within a surrounding casing in a gas turbine engine which includes a fuel manifold and support pins which are displaceable relative to mounting portions on the fuel manifold between a retracted position, wherein the fuel manifold is able to be inserted within a casing of the engine, and an extended position, wherein the support pins project outwardly from the fuel manifold for engagement with the casing. | 08-13-2009 |
| 20090211256 | Feed arm for a multiple circuit fuel injector - A feed arm for a multiple circuit fuel injector of a gas turbine engine. The feed arm includes an elongated tubular sleeve having a central bore with an interior wall defining an inner diameter, and an elongated fuel tube positioned within the bore of the tubular sleeve. The fuel tube includes a tubular wall defining an outer diameter, which is substantially equal to the inner diameter of the central bore. A primary fuel flow passage is formed within the tubular wall of the fuel tube and bounded by the interior wall of the tubular sleeve, and the primary fuel flow passage circumferentially extends around the fuel tube at least once along the axial length of the fuel tube. A secondary fuel flow passage extends through a central portion of the fuel tube, and the fuel tube is configured to facilitate heat transfer by conduction and/or convection. | 08-27-2009 |
| 20100050645 | Fuel distribution manifold system for gas turbine engines - A fuel distribution manifold system for a gas turbine engine is disclosed that includes a plurality of interconnected manifold segments, each manifold segment extending between a pair of fittings, each manifold segment including at least one fuel transfer tube and a sealing tube that surrounds the at least one fuel transfer tube, wherein opposed end portions of the at least one fuel transfer tube are dynamically connected to the fittings and opposed end portions of the sealing tube are statically connected to the fittings. | 03-04-2010 |
| 20100058764 | LOW BTU FUEL FLOW RATIO DUCT BURNER FOR HEATING AND HEAT RECOVERY SYSTEMS - Duct burner systems configured to utilize low BTU fuel sources are provided in the disclosed embodiments. In certain embodiments, the systems may include a primary duct configured to receive a primary flow stream of exhaust gases from an exhaust duct and a secondary duct configured to receive a secondary flow stream of exhaust gases from the exhaust duct. Primary and secondary variable geometry diverters may be configured to allow and restrict the primary and secondary flow streams, respectively. A combustion system may receive the secondary flow stream, combine it with at least one low BTU fuel source, combust for heating the secondary flow stream, and re-inject the heated secondary flow stream into the primary duct. A blower may be used to blow the secondary flow stream through the combustion system. In addition, a system controller may be used to control the stoichiometric flow ratio between the low BTU fuel flow source and the secondary flow stream by actuating the primary and secondary variable geometry diverters. | 03-11-2010 |
| 20100077758 | INTERNAL FUEL MANIFOLD HAVING TEMPERATURE REDUCTION FEATURE - A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced. | 04-01-2010 |
| 20100077759 | Tubular Fuel Injector for Secondary Fuel Nozzle - A fuel injector for a secondary fuel nozzle in a gas turbine includes axially oriented air slots and a plurality of fuel injection holes disposed between the air slots. The plurality of fuel injection holes include axially oriented injection holes and circumferentially oriented injection holes such that fuel input through the plurality of fuel injection holes is injected in both a circumferential direction and an axial direction to mix with air flowing through the air slots. | 04-01-2010 |
| 20100192584 | GAS TURBINE COMBUSTOR - An object is to provide a low cost gas turbine combustor. The gas turbine combustor has a plurality of main nozzles annularly supported on a nozzle pipe base ( | 08-05-2010 |
| 20110154824 | FREQUENCY-TUNABLE BRACKETLESS FLUID MANIFOLD - A fluid manifold apparatus includes: (a) an array of spaced-apart manifold fittings, each manifold fitting aligned in a predetermined angular orientation. Each manifold fitting includes: (i) a tubular neck; (ii) a pair of spaced-apart tubular arms extending away from a first end of the neck; and (iii) a coupling connected to a second end of the neck; and (b) a plurality of curved tubes, each tube being coupled to one arm of each of two adjacent manifold fittings. | 06-30-2011 |
| 20110173982 | GAS TURBINE ENGINE FUEL CONVEYING MEMBER - A fuel conveying member for a gas turbine engine, the fuel conveying member including a fuel manifold having a plurality of fuel nozzles extending therefrom. The fuel manifold is mounted within the engine by a support system, including integral attachment lugs on the fuel manifold for mounting the fuel manifold within the gas turbine engine. The attachment lugs re adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs. | 07-21-2011 |
| 20110203284 | CIRCUMFERENTIAL BIASING AND PROFILING OF FUEL INJECTION IN DISTRIBUTION RING - An annular fluid distribution device ( | 08-25-2011 |
| 20120180488 | GAS TURBINE COMBUSTOR ENDCOVER ASSEMBLY WITH INTEGRATED FLOW RESTRICTOR AND MANIFOLD SEAL - An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles includes a substantially flat plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel passage extends through the substantially flat plate. A fuel manifold porting block is secured to the opposite side of the flat plate with at least one port aligned with the at least one passage. A fuel restrictor insert formed with multiple flow orifices is located between the flat plate and the fuel manifold porting block in alignment with the at least one fuel passage and the at least one port. | 07-19-2012 |
| 20120186257 | GAS TURBINE INTERNAL MANIFOLD MOUNTING ARRANGEMENT - A mounting method and system for supporting and positioning an internal fuel manifold relative to a combustor in a fuel injection system for a gas turbine engine. The method includes positioning the fuel manifold within a gas generator casing, applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, and using the heat shield to at least partially support the fuel manifold within the gas generator casing. | 07-26-2012 |
| 20130086911 | PROCESS AND APPARATUS FOR OVERLAY WELDING - An apparatus and process for depositing an overlay weld on a substrate in a manner that reduces dilution of the substrate material. A consumable electrode is positioned in proximity to the surface of the substrate, and an electrical potential is applied between the electrode and substrate to generate an electrical arc therebetween. The arc melts the electrode and forms a molten spray that deposits on the substrate surface. Energy of the electric arc is absorbed to reduce the temperature at the substrate surface by feeding an additional filler material into the electric arc toward its center axis. The filler material continuously melts prior to reaching the center axis of the electric arc, and the electrode and filler materials are simultaneously deposited to form the overlay weld on the substrate. Sufficient energy is absorbed by the filler material to reduce intermixing between the overlay weld and the substrate. | 04-11-2013 |
| 20130152590 | FUEL MANIFOLD WITH JUMPER TUBES - A gas turbine engine fuel delivery system which includes an external fuel manifold fastened to the outer surface of a casing surrounding the combustor of the engine and which includes a plurality of inlet manifold tubes circumferentially disposed in serial flow communication. A plurality of fuel nozzles are mounted to the casing and are axially spaced apart from the fuel manifold on the outer surface of the casing. A plurality of jumper tubes are disposed outside the casing and feed fuel flow from the fuel manifold to the fuel nozzles. The jumper tubes have a rigidity that is less than that of the inlet manifold tubes of the fuel manifold such that the jumper tubes elastically deflect under load. | 06-20-2013 |
| 20130174561 | Late Lean Injection System Transition Piece - A late lean injection system transition piece includes a flowsleeve interface extending circumferentially around a transition interior. Also included is an impingement sleeve mounting surface extending circumferentially around the transition interior. Further included is a plurality of fuel injectors integrated substantially within the transition piece and disposed between the flowsleeve interface and the impingement sleeve mounting surface. Yet further included is an inner surface extending circumferentially around the transition interior, wherein the inner surface is spaced radially inward of the flowsleeve interface and the impingement sleeve mounting surface. | 07-11-2013 |
| 20130263602 | HIGH TEMPERATURE FUEL MANIFOLD FOR GAS TURBINE ENGINES - A segment of a fluid manifold includes a flexible thermal shield with an insulation space defined inboard of the thermal shield to provide thermal isolation from conditions external to the thermal shield. The thermal shield includes a helically corrugated metal tube having opposed first and second ends. An outer collar is threaded to an end of the helically corrugated metal tube. The outer collar includes a crimped portion and an uncrimped portion. The uncrimped portion is spaced apart from the corrugated helical metal tube more than the crimped portion to define a vent between the outer collar and the corrugated helical metal tube in venting communication with the insulation space to vent hot gases. | 10-10-2013 |
| 20130318977 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes an end cover, an endcap assembly, a fluid supply chamber, and a plurality of tube assemblies positioned at the endcap assembly. Each of the tube assemblies includes a housing having a fuel plenum and a cooling fluid plenum defined therein, the cooling fluid plenum downstream from the fuel plenum and separated therefrom by an intermediate wall, a plurality of tubes extending through the housing, each of the plurality of tubes in flow communication with the fluid supply chamber and a combustion chamber downstream from the tube assembly, and an aft plate at a downstream end of the cooling fluid plenum, the aft plate including at least one aperture defined therethrough. The fuel injection assembly further includes at least one fuel delivery pipe coupled to at least one of the plurality of tube assemblies. | 12-05-2013 |
| 20140116054 | RADIAL FLOW FUEL NOZZLE FOR A COMBUSTOR OF A GAS TURBINE - A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold. | 05-01-2014 |
| 20140137558 | FUEL SUPPLY SYSTEM FOR SUPPLYING FUEL TO A COMBUSTION SECTION OF A GAS TURBINE - A fuel supply system supplies fuel to a plurality of combustion sectors of a combustion section of a gas turbine. Each of the combustion sectors includes at least two combustors. The fuel supply system generally includes a fuel distribution manifold that is in fluid communication with a fuel supply. A first flow path is defined between the fuel distribution manifold and a first combustion sector. A second flow path is defined between the fuel distribution manifold and a second combustion sector. | 05-22-2014 |
| 20140150434 | FUEL NOZZLE FOR A COMBUSTOR OF A GAS TURBINE ENGINE - A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages. | 06-05-2014 |
| 20140157780 | FUEL CONTROL MODULE - A fuel control module for a gas turbine engine and method of installation. The fuel control module includes a first frame unit, a second frame unit, a fuel path, and a fuel controller components. The first frame unit and the second frame unit include features for installation in multiple installations and/or multiple configurations. | 06-12-2014 |
| 20140260272 | SYSTEM FOR PROVIDING FUEL TO A COMBUSTOR - A system for providing fuel to a combustor of a gas turbine includes an annular fuel distribution manifold that at least partially defines a fuel plenum. The fuel distribution manifold includes a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange. A LLI assembly extends downstream from the fuel distribution manifold. The LLI assembly includes a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone within the combustor. A LLI injector extends substantially radially through the unibody liner and provides for fluid communication through the unibody liner into the secondary combustion zone. A fluid conduit in fluid communication with the fuel plenum extends between the LLI injector and the fuel distribution manifold. | 09-18-2014 |
| 20140260273 | CONTINUOUS COMBUSTION LINER FOR A COMBUSTOR OF A GAS TURBINE - A combustion liner for a gas turbine combustor includes an annular main body having a forward end axially separated from an aft end, and a transitional intersection defined between the forward end and the aft end. The main body extends continuously from the forward end to the aft end. A plurality of fuel injector passages extend radially through the main body upstream from the transitional intersection. The main body comprises a conical section having a circular cross section that diverges between the forward end and the transitional intersection, and a transition section having a non-circular cross section that extends from the transitional intersection to the aft end of the main body. | 09-18-2014 |
| 20140260274 | FUEL DISTRIBUTION MANIFOLD FOR A COMBUSTOR OF A GAS TURBINE - A fuel distribution manifold for a combustor of a gas turbine includes an annular flange having an outer surface that extends circumferentially around the flange. A primary fuel plenum extends circumferentially within the flange. A first orifice and a second orifice extend radially through the outer surface of the flange to provide for fluid communication into the primary fuel plenum. The first orifice includes an inlet that is adjacent to the outer surface. The second orifice includes an inlet that is adjacent to the outer surface. A fuel distribution cap extends partially across the outer surface of the flange. The fuel distribution cap includes an inlet port. A fuel distribution plenum is at least partially defined within the fuel distribution cap. The fuel distribution plenum is in fluid communication with the inlet port and with the first orifice inlet and the second orifice inlet. | 09-18-2014 |
| 20150027126 | SYSTEM FOR PROVIDING FUEL TO A COMBUSTOR - A fuel supply system for a gas turbine combustor includes an annular duct that at least partially defines a hot gas path within the combustor. An orifice is at least partially defined by the annular duct and defines a flow path through the annular duct into the hot gas path. A plurality of fuel injectors are arranged circumferentially around the annular duct to provide for fluid communication through the annular duct into the hot gas path. A fuel distribution manifold is disposed adjacent to an outer side of the annular duct. The fuel distribution manifold includes a main body that at least partially defines an inlet for receiving fuel, an outlet that is in fluid communication with the fuel injectors, and a fuel purge passage that provides for fluid communication between the inlet and the orifice. | 01-29-2015 |
| 20150107256 | COMBUSTOR FOR GAS TURBINE ENGINE - An assembly of a combustor and fuel manifold comprises a fuel manifold having at least an annular portion with a plurality of fuel outlets facing at least partially radially inward. A combustor comprises an annular inner liner and an annular outer liner spaced apart from the inner liner, the inner liner and outer liner concurrently forming an annular combustor chamber therebetween. The inner and outer liners concurrently define an annular receptacle in the annular combustor chamber for receiving the fuel manifold. The inner liner and outer liners are shaped to define an annular gas path in the annular combustor chamber having an upstream portion that is substantially radial and oriented toward a center when the combustor is in a gas turbine engine. | 04-23-2015 |
| 20150121883 | FLUID CONDUIT - A gas turbine engine is provided. The gas turbine engine includes a compressor assembly and a combustion assembly in flow communication with the compressor assembly. The combustion assembly includes a plurality of fuel nozzles and a fluid conduit for delivering fuel to the fuel nozzles. The fluid conduit has a plurality of first outlet ports that are spaced apart from one another along the fluid conduit, and the fluid conduit also has a plurality of second outlet ports that are spaced apart from one another along the fluid conduit. The fluid conduit further has a first flow path extending along the fluid conduit in flow communication with the first outlet ports, and the fluid conduit also has a second flow path extending along the fluid conduit in flow communication with the second outlet ports. At least a portion of the first flow path is circumscribed by the second flow path. | 05-07-2015 |
| 20150315968 | FUEL SUPPLY SYSTEM - A fuel supply system includes a fuel manifold and a main fuel line path configured to receive a fuel from the fuel manifold. The main fuel line path routes the fuel to a combustion inlet region. The fuel supply system also includes a secondary fuel line path having an inlet configured to receive a portion of the fuel and an outlet configured to route the portion of the fuel to the main fuel line path through an outlet at a location of the main fuel line path that is downstream of the inlet of the secondary fuel line path. A storage volume is fluidly coupled to the secondary fuel line path and is configured to cyclically store and release the portion of the fuel. | 11-05-2015 |
| 20150315969 | FUEL SUPPLY SYSTEM - A fuel supply system includes a main fuel line path configured to route a fuel to a combustion inlet region and a secondary fuel line path fluidly coupled to the main fuel line path. The secondary fuel line path is configured to divert a portion of the fuel from the main fuel line path through a first segment of the secondary fuel line path and return the fuel to the main fuel line path through a second segment of the secondary fuel line path. An obstruction mechanism is located proximate the main fuel line path at an obstruction location and is configured to cyclically translate into the main fuel line path to cyclically alter a cross-sectional area of the main fuel line path to effectively oscillate fuel flow pressure into a combustion system. | 11-05-2015 |
| 20150322862 | FUEL MANIFOLD AND FUEL INJECTOR ARRANGEMENT FOR A COMBUSTION CHAMBER - Each fuel injector has a main nozzle and pilot nozzle. A main fuel manifold to supply fuel to the main nozzle of each fuel injector and pilot fuel manifold to supply fuel to the pilot nozzle of each fuel injector. The main fuel manifold includes plurality of flexible main fuel pipes. Also, plurality of cross-piece connectors including a stem and four arms. The stem of each connector mounted on one fuel injector. The first and third arms extend in opposite directions from the stem and second and fourth arms extend in opposite directions from the stem. Each fuel pipe interconnects the first arm of one connector with a third arm of an adjacent connector and each connector so the first and third arms are at an angle relative perpendicular to the axis of the annular combustion chamber casing so the main fuel manifold extends around the combustion chamber casing sinusoidally. | 11-12-2015 |
| 20150361897 | FUEL MANIFOLD AND FUEL INJECTOR ARRANGEMENT - A fuel manifold and fuel injector arrangement comprises an annular fuel manifold and a plurality of fuel injectors. Each fuel injector comprises a fuel injector head and a hollow fuel feed arm. Each fuel injector has a pipe to supply fuel to the fuel injector head. The pipe extends from the fuel feed arm and through a corresponding aperture in the casing. The annular fuel manifold is arranged around the casing and the annular fuel manifold comprises a plurality of connectors. Each connector has a socket aligned with a corresponding aperture in the casing. Each pipe has a plug arranged to be radially slidably mounted in the socket of the corresponding connector of the annular fuel manifold to allow relative radial movement between the casing and the annular fuel manifold. | 12-17-2015 |
| 20160011030 | METHOD FOR MEASURING THE MASS FLOW OF A STREAM OF A GASEOUS MEDIUM AND FUEL SUPPLY SYSTEM FOR CONDUCTING THE METHOD | 01-14-2016 |
| 20160108818 | FLUID CONDUIT - A fluid conduit for a gas turbine engine. The conduit includes a superelastic material such as TNTZ or Ti2448. The conduit is installed such that at least part of the conduit is subject to a stress which lies in one of a superelastic and a plastic region of the material in use. | 04-21-2016 |
| 20160169121 | Speed Card-Controlled Override Fuel Pump Assist | 06-16-2016 |
| 20160201562 | FUEL MANIFOLD FOR A GAS TURBINE ENGINE | 07-14-2016 |
| 20160376997 | COMBUSTION SYSTEMS - A combustion system for a gas turbine engine includes a combustor dome. The combustor dome includes a fuel manifold with an inlet and nozzle components of a plurality of nozzles circumferentially spaced around the combustor dome. The fuel manifold and nozzle components are integrated with the combustor dome for fluid communication from the inlet to the nozzle components. | 12-29-2016 |
| 20160377291 | COOLING IN STAGED FUEL SYSTEMS - A fuel system includes a fuel supply system. A plurality of fuel nozzles are connected in fluid communication with the fuel supply system to supply fuel from a fuel source to be issued for combustion from the fuel nozzles. A cooling system is included, wherein at least one of the fuel nozzles includes a cooling circuit in addition to a fuel circuit for issuing fuel from the fuel supply system for combustion. The cooling circuit includes an inlet and an outlet. The inlet is in fluid communication with the cooling system for circulation of coolant through the cooling circuit and back to the cooling system out the outlet of the cooling circuit for cooling the fuel circuit with the fuel circuit staged off. | 12-29-2016 |
| 20170234228 | GAS TURBINE ENGINE PIPE COVER | 08-17-2017 |
| 20180023477 | INTERNAL MANIFOLD WITH FUEL INLET | 01-25-2018 |
