| Entries |
| Document | Title | Date |
|---|
| 20080236164 | FAIRING FOR A COMBUSTION CHAMBER END WALL - An annular fairing for covering the annular chamber end wall of a turbomachine combustion chamber, and in particular of an airplane turbojet. The fairing presents openings for passing fuel injectors that are supported by the chamber end wall. The fairing is subdivided into a plurality of adjacent sectors, each sector presenting inner and outer fastener edges capable of being fastened on either side of said chamber end wall. Each sector includes a lip on one of its side edges, which lip is connected to the remainder of the sector by a step, said lip being designed to over the side edge of the adjacent sector. | 10-02-2008 |
| 20080271456 | Fuel supply system - A turbine fuel supply system is disclosed as including a first sub-system having: a first nozzle for injecting fuel into a combustor of a turbine engine; a first valve controllable to communicate fuel to the first nozzle; and a first fuel manifold for communicating fuel to the first valve from a fuel source; the system further including a controller assembly for raising the pressure of fuel in the first fuel manifold; and the system being characterized in that the first valve is adapted to open in response to a predetermined pressure difference between the first fuel manifold and the pressure in the combustor, thereby allowing fuel to be communicated from the first fuel manifold to the first nozzle. The system may include a first recirculating conduit in fluid communication with the first fuel manifold and the fuel source, the first recirculating conduit allowing fuel not communicated by the first valve to be returned to the fuel source. | 11-06-2008 |
| 20080295519 | Turbine engine fuel injector with Helmholtz resonators - An end cap for a fuel injector of a turbine engine is disclosed. The end cap includes an annular first surface including a plurality of perforations. The annular first surface is exposed to a combustion chamber of the turbine engine. The end cap is coupled to an end face of the fuel injector to define an enclosed cavity. The enclosed cavity and the plurality of perforations form an array of Helmholtz resonators. | 12-04-2008 |
| 20080307791 | FUEL NOZZLE PROVIDING SHAPED FUEL SPRAY - A fuel injection nozzle for a gas turbine engine has a central fuel ejection nozzle and a plurality of airflow passages within the spray tip that include a first and second group of circumferentially spaced apart fuel-spray forming airflow passages disposed on opposite sides of a transverse axis and oriented towards each other such as to produce opposed fuel spray shaping air jets which generate a shaped final fuel spray. | 12-18-2008 |
| 20090044538 | FUEL INJECTOR NOZZLES, WITH LABYRINTH GROOVES, FOR GAS TURBINE ENGINES - A fuel injector for a gas turbine engine of an aircraft, and more particularly a novel and unique heatshield structure for a fuel nozzle wherein a labyrinth seal is uniquely provided in the nozzle to isolate a portion of an insulating gap from an interface whereat fuel may enter the insulating gap, and the insulating gap is provided with a positive purge flow for forcing vapors out of the insulating gap. | 02-19-2009 |
| 20090056337 | TURBOMACHINE WITH ANNULAR COMBUSTION CHAMBER - Turbomachine with an annular combustion chamber ( | 03-05-2009 |
| 20090133402 | Gas turbine fuel injector with insulating air shroud - A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing extending from a first end to a second end along a longitudinal axis. The second end of the housing is fluidly coupled to a combustor of the turbine engine and the housing includes a liquid fuel gallery annularly disposed about the longitudinal axis. The fuel injector also includes a stem extending longitudinally from the first end of the housing to a third end. The stem includes a liquid tube configured to deliver liquid fuel to the fuel injector. The fuel injector also includes an annular shell extending along the longitudinal axis from the first end to the third end and circumferentially disposed about the stem. The fuel injector further includes an insulating air shroud formed inside the shell. The air shroud includes a layer of air between the shell and the stem. | 05-28-2009 |
| 20090139238 | AIRFLOW DISTRIBUTION TO A LOW EMISSIONS COMBUSTOR - An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone. | 06-04-2009 |
| 20090139239 | QUENCH JET ARRANGEMENT FOR ANNULAR RICH-QUENCH-LEAN GAS TURBINE COMBUSTORS - An outer liner of a combustor of a gas turbine engine includes a plurality of liner regions arranged adjacent one another and separated by boundary lines; and a plurality of air admission holes formed in the liner regions. The air admission holes within each liner region form a V-pattern. | 06-04-2009 |
| 20090139240 | Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity - A gas-turbine lean combustor includes a combustion chamber ( | 06-04-2009 |
| 20090199563 | Scalable pyrospin combustor - An axial-flow pyrospin combustor comprises inner and outer combustor liners and a plurality of pyrospin effusion holes. The inner liner is coaxially mounted inside the outer liner, about a central combustor axis. The pyrospin effusion holes are formed in at least one of the outer combustor liner and the inner combustor liner. Each of the pyrospin effusion holes has a down angle and a back angle, which control a global swirl flow about the central axis, and promote film cooling without detachment. | 08-13-2009 |
| 20090211257 | FUEL SUPPLY ARRANGEMENT - A fuel supply arrangement for a gas turbine burner is provided. The fuel distribution arrangement includes a rear section external to the burner located between a turbine wall and a fuel distribution system interface directing fuel into fuel supply circuits. The fuel distribution system interface has four fuel connections. An intermediate section is located between the turbine wall and the backside wall of a distribution chamber; and a front section in front of the second section located between said backside wall of the distribution chamber and a burner central backside block. The fuel distribution arrangement includes pipes for gaseous fuel, liquid fuel, as well as pilot gas, and liquid pilot fuel. In the rear section the pipes for gaseous fuel and for liquid fuel are arranged concentrically, and in at least one portion of the intermediate section the pipe for gaseous fuel is arranged non-concentrically with the liquid fuel pipe. | 08-27-2009 |
| 20090277177 | FUEL NOZZLE FOR A GAS TURBINE ENGINE AND METHOD FOR FABRICATING THE SAME - A method for fabricating a fuel nozzle assembly includes providing a nozzle portion including a fuel passageway defined about a center axis of the fuel nozzle assembly. A longitudinal axis of a first peg is oriented to intersect the fuel nozzle assembly center axis such that a first plane is defined. The first peg defines a first opening having a centerline intersecting the first peg longitudinal axis and obliquely oriented with respect to the first plane. The first peg is coupled in flow communication with the fuel passageway such that the first peg extends radially outward from the nozzle portion and such that the first opening is configured to direct a flow of fuel in an oblique direction with respect to the fuel nozzle assembly center axis to facilitate fuel mixing. | 11-12-2009 |
| 20090293483 | VIBRATION DAMPER - Fuel injector assemblies with frictionally damped fuel supply members, including fuel feed strips. More particularly, the invention provides friction dampers and/or assemblies that frictionally damp movement of fuel supply members in at least one direction. Some of the embodiments provide a friction damper that is easily serviceable, and can be installed after final assembly of a fuel injector. Aspects of the invention are applicable to other components of fuel injectors and gas turbine engines in addition to fuel supply members. | 12-03-2009 |
| 20090293484 | GAS TURBINE COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO THE SAME - A fuel flow path and a flow path of air for combustion are disposed coaxially to create a coaxial jet such that a fuel flow is embraced by an air flow. A large number of such fuel flow paths and air flow paths are arranged in a wall surface of a combustion chamber to create coaxial nozzle jets. Some of the flow paths of air for combustion are arranged inclinedly so as to create rotation for the stabilization of combustion and straight portions not having an inclination angle are added respectively to upstream ends of such inclined air flow paths. Fuel is jetted toward or within the straight portions. | 12-03-2009 |
| 20090320481 | Fuel control arrangement - Fuel control arrangements for gas turbine engines generally comprise an injector and a fuel control valve. Typically the fuel control valve is controlled in terms of fuel demand through fuel pressure presented to the valve. Fuel demand may vary and in such circumstances stagnation of fuel adjacent to the valve may cause degradation of the fuel and therefore spurious operational performance. By providing a dedicated working fluid, and typically hydraulic, pressure to the valve a variable aperture port can be displaced to alter the fuel flow configuration within the valve. In such circumstances different fuel valve conditions can be generated by altering the available area of aperture in the port to divert or present fuel to the injector between and across first or primary fuel paths and second or pilot fuel paths as required. Thus more flexibility with regard to fuel presentation to the injector is achieved as well as consistency with respect to avoiding fuel degradation as fuel demand varies. | 12-31-2009 |
| 20100018209 | INTEGRAL FLOW SLEEVE AND FUEL INJECTOR ASSEMBLY - A fuel injector assembly for use in a turbine engine having a combustion section and a turbine section downstream from the combustion section. The fuel injector assembly includes a flow sleeve defining a pre-mixing passage of the combustion section and including a sleeve wall having a forward end proximate to a cover plate of the combustion section and an opposed aft end. An annular cavity in fluid communication with a source of fuel is formed in the sleeve wall adjacent the aft end. A fuel dispensing structure is associated with the cavity and includes at least one fuel distribution aperture for distributing fuel from the cavity to the pre-mixing passage. | 01-28-2010 |
| 20100031662 | TURBOMACHINE INJECTION NOZZLE INCLUDING A COOLANT DELIVERY SYSTEM - An injection nozzle for a turbomachine includes a main body having a first end portion that extends to a second end portion defining an exterior wall having an outer surface. A plurality of fluid delivery tubes extend through the main body. Each of the plurality of fluid delivery tubes includes a first fluid inlet for receiving a first fluid, a second fluid inlet for receiving a second fluid and an outlet. The injection nozzle further includes a coolant delivery system arranged within the main body. The coolant delivery system guides a coolant along at least one of a portion of the exterior wall and around the plurality of fluid delivery tubes. | 02-11-2010 |
| 20100058765 | TURBOMACHINE COMBUSTION CHAMBER - A turbomachine combustion chamber including a substantially L-shaped fuel injector and means for mounting and fastening the injector in an orifice of the casing of the chamber, said means including an outer collar carried by the injector and a removable annular spacer surrounding the injector and designed to be interposed between the collar of the injector and the casing. | 03-11-2010 |
| 20100071375 | Apparatus for observing combustion conditions in a gas turbine engine - A fuel injector for a gas turbine combustor is disclosed which includes a fuel nozzle for issuing fuel into the combustor for combustion, at least one photodetector responsive to flame radiation indicative of an OH chemiluminescence peak, and at least one photodiode responsive to flame radiation indicative of a CH chemiluminescence peak. | 03-25-2010 |
| 20100071376 | Combustor Assembly in a Gas Turbine Engine - A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct. | 03-25-2010 |
| 20100071377 | Combustor Apparatus for Use in a Gas Turbine Engine - A combustor apparatus for use in a gas turbine engine. The combustor apparatus includes a liner, a flow sleeve, and a fuel injection system. The liner includes an inner volume, wherein a portion of the inner volume defines a main combustion zone. The flow sleeve receives compressed air, is positioned radially outward from the liner, and includes a forward end and an aft end. The fuel injection system is coupled to the flow sleeve and provides fuel into the inner volume of the liner downstream from the main combustion zone. The fuel injection system includes a fuel manifold and a fuel dispensing structure. The fuel manifold is coupled to the flow sleeve and includes a cavity for receiving fuel. The fuel dispensing structure is associated with the cavity and distributes fuel from the cavity to the liner inner volume. | 03-25-2010 |
| 20100115955 | THERMAL MANAGEMENT FOR FUEL INJECTORS - Methods of managing fuel temperatures in fuel injectors for gas turbine engines include cooling fuel circuits by initiating fuel flow therethrough using opened, closed, and semi-open control techniques. A fuel injector for a gas turbine engine includes a feed arm having a fuel inlet fitting for delivering fuel to at least one fuel conduit extending through the feed arm. A nozzle body depends from the feed arm and has at least one fuel circuit extending therethrough. The fuel circuit is configured and adapted to receive fuel from the feed arm and to issue fuel from an exit orifice of the nozzle body. Sensing means are provided adjacent to the at least one fuel circuit. The sensing means are configured and adapted to provide temperature feedback in order to control fuel flow in the at least one fuel circuit to maintain fuel temperature within a predetermined range. | 05-13-2010 |
| 20100132363 | TURBOMACHINE WITH SEPARATE FUEL INJECTION SYSTEMS, USING IDENTICAL SEALING JOINTS - The present invention concerns a unit ( | 06-03-2010 |
| 20100154424 | Low cross-talk gas turbine fuel injector - A pilot assembly for a fuel injector of a gas turbine engine may include a longitudinal passageway having an outlet end. A mass flow in the longitudinal passageway may generally flow towards the outlet end during operation of the engine. The pilot assembly may also include a liquid fuel nozzle that is positioned to direct a mixture of liquid fuel and air near the outlet end, and a compressed air inlet that is configured to direct air compressed by a compressor of the engine to a compressor discharge pressure into the longitudinal passageway without a substantial loss of pressure. The longitudinal passageway may also include a flow restriction section. The flow restriction section may be a narrowed section of the longitudinal passageway, in which an upstream side of the flow restriction section may have compressed air at substantially the compressor discharge pressure and a downstream side may have air at a lower pressure and a higher velocity. The pilot assembly may further include a nozzle for injecting one of assist air or gaseous fuel into the longitudinal passageway. The nozzle may be positioned at the flow restriction section or on an upstream side of the flow restriction section to reduce cross-talk. | 06-24-2010 |
| 20100154425 | STRAIN TOLERANT THERMAL BARRIER COATING SYSTEM - A method for forming a thermal barrier coating on a combustor panel or a fuel nozzle comprises the steps of: providing a component selected from the group consisting of a combustor panel, a bulkhead heat shield, and a fuel nozzle; optionally depositing a first layer of a metallic alloy onto the component; and depositing a ceramic composition layer using an electron beam physical vapor deposition technique. If the component is formed from a yttrium or other active element doped single crystal superalloy, the first layer may be omitted and the ceramic composition layer may be deposited directly onto a surface of the component. | 06-24-2010 |
| 20100170251 | LATE LEAN INJECTION WITH EXPANDED FUEL FLEXIBILITY - A gas turbine engine is provided and includes a fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors which supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages. | 07-08-2010 |
| 20100180600 | NOZZLE FOR A TURBOMACHINE - A turbomachine includes a compressor, a combustor operatively connected to the compressor, and an injection nozzle operatively connected to the combustor. The injection nozzle includes a main body having a first end section that extends to a second end section to define an inner flow path. The injection nozzle further includes an outlet arranged at the second end section of the main body, at least one passage that extends within the main body and is fluidly connected to the outlet, and at least one conduit extending between the inner flow path and the at least one passage. | 07-22-2010 |
| 20100186413 | BUNDLED MULTI-TUBE NOZZLE FOR A TURBOMACHINE - A turbomachine includes a compressor, a combustor operatively connected to the compressor, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a cap member having a first surface that extends to a second surface. The cap member further includes a plurality of openings. A plurality of bundled mini-tube assemblies are detachably mounted in the plurality of openings in the cap member. Each of the plurality of bundled mini-tube assemblies includes a main body section having a first end section and a second end section. A fluid plenum is arranged within the main body section. A plurality of tubes extend between the first and second end sections. Each of the plurality of tubes is fluidly connected to the fluid plenum. | 07-29-2010 |
| 20100186414 | MAGNETIC ION PLASMA ANNULAR INJECTION COMBUSTOR - Discloses a technique for application of an external electric field to a mixture of atomized air, molecularized with fuel to a specific predetermined density, in an annular turbine combustor configuration. An electric current is distributed into the atomized air by a plurality of ion plasma fuel injector devices to affect the propagation speed, stability, flame size and shape and combustion chemistry of the fuel air mixture at the flame front. | 07-29-2010 |
| 20100229558 | Methods and Apparatus for Providing A Sacrificial Shield For A Fuel Injector - Embodiments of methods and apparatus for providing a sacrificial shield for a fuel injector are provided. According to one example embodiment, a method for shielding a fuel injector associated with a combustion device is provided. The method can include providing at least one shield support device operable to mount to a tip of a fuel injector. The method can also include mounting a plurality of shields to the at least one support device, wherein each of the plurality of shields is spaced apart from each respective adjacent shield by at least one segmentation, and wherein each of the plurality of shields is operable to reduce heat exposure to the tip of the fuel injector. | 09-16-2010 |
| 20100229559 | FUEL INJECTION SYSTEMS IN A TURBOMACHINE COMBUSTION CHAMBER - Turbomachine, comprising a combustion chamber provided with systems ( | 09-16-2010 |
| 20100236246 | BURNER OF A GAS TURBINE - An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052. | 09-23-2010 |
| 20100251720 | FUEL INJECTOR NOZZLES FOR GAS TURBINE ENGINES - A fuel injector for a gas turbine engine comprises a housing stem and a nozzle, the nozzle including an internal wall in heat transfer relation with fuel flowing through the nozzle, and an external wall in heat transfer relation with ambient air. The internal and external walls have downstream tip ends that are relatively moveable at an interface due to relative thermal growth during operation of the engine. An internal insulating gap is disposed between the internal and external walls to provide a heat shield for the internal wall, and a bellows internal to the injector has an upstream end sealingly attached to an upstream portion of one of the internal and external walls, and a downstream end sealingly attached to a downstream portion of the other wall to fluidly separate the insulating gap from any fuel entering into the nozzle through the interface. | 10-07-2010 |
| 20100287937 | AUTOMATIC FUEL NOZZLE FLAME-HOLDING QUENCH - A flame-holding control method in a gas turbine having a combustor can and a fuel nozzle disposed in the combustor can. The method can include performing a first scheduled injection of a diluent stream into the nozzle, checking to see if a time period has exceeded a time threshold and in response to the time period being greater than that the time threshold, performing a second scheduled injection of the diluent stream into the nozzle. | 11-18-2010 |
| 20100287938 | CROSS FLOW VANE - The present application provides a cross flow vane for a turbine. The cross flow vane may include a number of jets positioned therein and a divider positioned within one or more of the jets so as to form a number of fuel slots therein. | 11-18-2010 |
| 20100293954 | METHOD AND APPARATUS FOR COMBUSTOR NOZZLE WITH FLAMEHOLDING PROTECTION - The structure and operation of a fuel nozzle for a gas turbine combustor is disclosed where the fuel nozzle provides for flameholding protection and, more specifically, to such a nozzle that provides for nondestructive protection from flamebolding. The nozzle provides for differential thermal expansion between tubes forming fuel passages to allowing for the nondestructive venting of fuel during a flameholding condition. Upon extinguishing the flameholding condition, the nozzle returns to normal operating condition. | 11-25-2010 |
| 20100300104 | BURNER, OPERATING METHOD AND ASSEMBLY METHOD - A burner incorporating a pilot cone and a mounting insert is provided. The pilot cone is constructed as a pilot cone assembly which is decoupled from the mounting insert. Further, an operating method for increasing the service life of a burner which incorporates a pilot cone assembly and a mounting insert is provided. The pilot cone assembly has a cone side and incorporates at least one further side where the further side is arranged to be essentially parallel to one of the sides of the mounting insert and spaced apart from it, so that between the further side and the side of the mounting insert there is a defined gap. In an operation of the burner, the gap is significantly reduced by the thermal expansion in at least at one point of contact between the further side and the side of the mounting insert. Finally, an assembly method is provided. | 12-02-2010 |
| 20100300105 | AIRBLAST FUEL NOZZLE ASSEMBLY - An airblast fuel nozzle assembly ( | 12-02-2010 |
| 20100326078 | TURBOMACHINE COMBUSTION CHAMBER - A turbomachine combustion chamber in which a chamber end wall presents an opening for receiving a pre-vaporization bowl, and including a device for injecting air and fuel mounted on the axis thereof, the bowl being floatingly mounted relative to the chamber end wall to move in a predetermined radial direction and flaring downstream so as to form a collar, a deflector forming a thermal shield being made integrally with the bowl beside the chamber end wall so that the floating movement of the bowl-and-deflector assembly takes place in a sliding plane situated between the deflector and the chamber end wall. | 12-30-2010 |
| 20110005231 | FUEL NOZZLE GUIDE PLATE MISTAKE PROOFING - A fuel nozzle guide plate has mirror symmetry about a first plane perpendicular to the fuel nozzle guide plate and mirror symmetry about a second plane parallel to the fuel nozzle guide plate. The fuel nozzle guide plate is attached to an air swirler, which is mounted in an opening of a bulkhead for mixing air and fuel at an upstream side of a combustor. | 01-13-2011 |
| 20110056206 | Fuel Injector for Use in a Gas Turbine Engine - A fuel injector in a combustor apparatus of a gas turbine engine. An outer wall of the injector defines an interior volume in which an intermediate wall is disposed. A first gap is formed between the outer wall and the intermediate wall. The intermediate wall defines an internal volume in which an inner wall is disposed. A second gap is formed between the intermediate wall and the inner wall. The second gap receives cooling fluid that cools the injector. The cooling fluid provides convective cooling to the intermediate wall as it flows within the second gap. The cooling fluid also flows through apertures in the intermediate wall into the first gap where it provides impingement cooling to the outer wall and provides convective cooling to the outer wall. The inner wall defines a passageway that delivers fuel into a liner downstream from a main combustion zone. | 03-10-2011 |
| 20110067402 | Fuel Nozzle Assembly for Use in a Combustor of a Gas Turbine Engine - A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a flow passage for combustion gases flowing within the combustor apparatus. The fuel manifold defines a fuel supply channel therein in fluid communication with a source of fuel. A fuel injector of the fuel nozzle assembly is provided in the inner volume of the outer housing and defines a fuel passage therein. The fuel passage is in fluid communication with the fuel supply channel of the fuel manifold for distributing the fuel from the fuel supply channel into the flow passage of the duct structure. | 03-24-2011 |
| 20110079013 | FUEL INJECTOR AND AERODYNAMIC FLOW DEVICE - A gas turbine engine includes a reverse flow annular combustor having a liner with opposing ends. One end includes apertures configured to receive compressed air, and an outlet is provided at the other end and is configured to connect to a turbine nozzle. A fuel injector extends through the liner at a base and axially between the apertures and the outlet. The fuel injector includes a housing extending from the base to a dome and provides an exterior surface surrounding an injector cavity. The exterior surface has forward and rearward surfaces respectively facing the apertures and the outlet and provides shapes that are different than one another to influence and improve the aerodynamic flow field of the gas mixture (i.e., air, fuel and combustion-products) within the combustor volume. | 04-07-2011 |
| 20110083440 | HIGH STRENGTH CROSSOVER MANIFOLD AND METHOD OF JOINING - A secondary fuel nozzle includes a plurality of tubes axially extending downstream within the secondary fuel nozzle, the tubes defining passages operable to allow a flow of fluid to flow through each of the passages, the passages including an outermost tertiary passage and a radially inner secondary fuel passage. The secondary fuel nozzle also includes a fuel peg extending radially outward from the axially extending tubes, the fuel peg operable to emit a fluid radially outward therefrom. The secondary fuel nozzle further includes a crossover manifold attached to the fuel peg and in fluid communication with the radially inner secondary fuel passage and the fuel peg, wherein the crossover manifold is attached to the corresponding tubes that define the tertiary passage and the radially inner secondary passage by butt welds. | 04-14-2011 |
| 20110138813 | IMPURITY DETECTION IN COMBUSTOR SYSTEMS - The present invention discloses a combustor system and method of measuring impurities in the combustion system. The combustion system includes an up-stream fuel injection point; a down-stream turbine combustor; a flame zone in the turbine combustor comprising a plurality of axial sub-zones; an optical port assembly configured to obtain a non-axial, direct, optical view of at least one of the plurality of axial sub-zones, and an impurity detection system in optical communication with the optical port assembly. | 06-16-2011 |
| 20110146285 | PULSE DETONATION SYSTEM WITH FUEL LEAN INLET REGION - In one embodiment, a pulse detonation system includes a pulse detonation tube and an air valve disposed at an upstream end of the pulse detonation tube. The air valve is configured to provide an air flow into the pulse detonation tube. The pulse detonation system also includes a fuel injector configured to inject fuel into the air flow to establish a fuel-air mixture configured to support detonation, and to establish a region in the fuel-air mixture having a fuel to air ratio insufficient to support a detonation wave. The pulse detonation system further includes an ignition source configured to detonate the fuel-air mixture when the region is disposed adjacent to the air valve. | 06-23-2011 |
| 20110162372 | INTEGRAL FLANGE CONNECTION FUEL NOZZLE BODY FOR GAS TURBINE - A fuel nozzle for a gas turbine includes a fuel nozzle body or endcover. The fuel nozzle body or endcover includes at least one seal surface. The fuel nozzle also includes at least one flexible hose and at least one flange connected to the flexible hose. The at least one flange is fastened to the fuel nozzle body at the at least one seal surface. | 07-07-2011 |
| 20110162373 | FUEL NOZZLE FOR A TURBINE ENGINE WITH A PASSIVE PURGE AIR PASSAGEWAY - A secondary fuel nozzle for a turbine includes a passive purge air passageway which provides purge air to the secondary nozzle at all times that the nozzle is in operation. The passive purge air passageway draws in air from a location adjacent an upstream end of the nozzle. Because of a pressure differential between air located at the downstream end of the nozzle and air located at the upstream end of the nozzle, purge air will run through the passive purge air passageway at all times the nozzle is in operation. There is no need for a supply of compressed purge air. | 07-07-2011 |
| 20110162374 | ARTICLES HAVING DAMPING COATINGS THEREON - An article, such as a bucket, a blade, a nozzle, a vane, a strut, a fuel nozzle, a combustion casing, and a transition piece, the article having a damping coating comprising approximately 8 wt % to approximately 15 wt % Y | 07-07-2011 |
| 20110167828 | COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE THAT MIXES COMBUSTION PRODUCTS WITH PURGE AIR - A combustor assembly for a turbine engine includes a fuel nozzle located at an upstream end of the combustor assembly. The fuel nozzle includes both a fuel delivery passageway and a purge air passageway. The purge air passageway conveys a flow of purge air to cool the fuel nozzle. The combustor assembly also includes a combustion product return line that conveys a flow of combustion products from a position downstream of a combustion zone of the combustor back to the fuel nozzle. The combustion products are mixed with purge air, and the mixture is delivered into a combustion zone located just downstream of the fuel nozzle. The addition of the combustion products into the purge air reduces the amount of oxygen in mixed flow, which helps to reduce the generation of undesirable nitrogen oxide combustion byproducts. Also, the greater heat of the combustion products helps to increase the temperature of the mixture, which helps to maintain the stability of a pilot flame fed by the mixture. | 07-14-2011 |
| 20110167829 | FUEL CONTROL ARRANGEMENTS - Fuel injection apparatus | 07-14-2011 |
| 20110167830 | VIBRATION DAMPER - Fuel injector assemblies with frictionally damped fuel supply members, including fuel feed strips. More particularly, the invention provides friction dampers and/or assemblies that frictionally damp movement of fuel supply members in at least one direction. Some of the embodiments provide a friction damper that is easily serviceable, and can be installed after final assembly of a fuel injector. Aspects of the invention are applicable to other components of fuel injectors and gas turbine engines in addition to fuel supply members. | 07-14-2011 |
| 20110197587 | MULTI-TUBE PREMIXING INJECTOR - A fuel injection nozzle includes at least one tube disposed in the nozzle having a venturi shaped profile defining a gas flow path including an inlet operative to receive a first gas, at least one port operative to emit a second gas into the gas flow path, and an outlet operative to emit a mixture of the first gas and the second gas into a combustor. | 08-18-2011 |
| 20110239653 | ANNULAR RING-MANIFOLD QUATERNARY FUEL DISTRIBUTOR - A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support. | 10-06-2011 |
| 20110247338 | FUEL LANCE FOR A BURNER - Disclosed is a fuel lance for a burner, in particular a gas turbine burner, including a tip that has a nozzle surface including at least two fuel nozzles. The nozzle surface is provided with slots between the fuel nozzles. As a rule, the lance is provided for operation with a liquid fuel. | 10-13-2011 |
| 20110265482 | POCKETED AIR AND FUEL MIXING TUBE - An improved mixing tube design and fuel nozzle that allows for a more uniform and thorough mixing of fuel and air being fed to the combustor of a gas turbine engine, wherein each of a plurality of mixing tubes comprises a pair of concentric hollow cylinders that define a ring-like, annular path for the flow of fuel between the two hollow cylinders in each mixing tube, a plurality of air injection slots formed in the concentric hollow cylinders defining corresponding air flow paths from the outside into the interior of each mixing tube, and one or more fuel injection ports formed in selected ones of the plurality of air injection slots that allow for the flow of fuel from the annular path formed by the hollow cylinders into the air flow path, resulting in significantly better mixing and improved thermodynamic behavior of the fuel and air mixture downstream of the nozzle and upstream of the combustor. | 11-03-2011 |
| 20110289928 | AIR/FUEL SUPPLY SYSTEM FOR USE IN A GAS TURBINE ENGINE - A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main body comprises a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet. The fuel supply structure communicates with and supplies fuel to the air/fuel passages for providing an air/fuel mixture within each air/fuel passage. The air/fuel mixtures exit the main body through respective air/fuel passage outlets. | 12-01-2011 |
| 20110308254 | Turbine Engine Fuel Injector - A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows. | 12-22-2011 |
| 20110314826 | Burner Assembly - A burner assembly for a firing system for firing fluidic fuels is provided. The burner assembly has a burner hub, an air inlet channel and a fuel inlet channel, wherein the fuel inlet channel is at least partially designed in the burner hub. A screening wall is arranged in the fuel inlet channel. The screening wall is spaced apart from a wall of the fuel inlet channel so that an intermediate space is formed between the wall of the fuel inlet channel and the screening wall. A sleeve is equipped with at least one radial positioning means that ensures a clearance of the sleeve from the wall of the fuel inlet channel. The at least one radial positioning means of the sleeve is designed as a positioning projection arranged in a circular manner, protruding out radially. | 12-29-2011 |
| 20120031098 | FUEL NOZZLE WITH CENTRAL BODY COOLING SYSTEM - A fuel nozzle for turbine engine includes a cooling shroud located at the downstream end of the fuel nozzle to help cool the downstream end of the fuel nozzle. The cooling shroud surrounds the exterior circumference of the downstream end of the fuel nozzle. A flow of air is admitted into the cooling shroud and the flow of air travels in the downstream direction through a first passageway which covers the exterior of the fuel nozzle. The cooling air flow then turns 180° and travels in the upstream direction through a second passageway which is located concentrically outside the first passageway. The airflow then leaves the upstream end of the cooling shroud and enters the interior of the fuel nozzle. | 02-09-2012 |
| 20120055162 | LANCE OF A BURNER - The lance of a burner includes a body that defines a first duct with first nozzles for injecting a liquid fuel and a second duct with second nozzles for injecting a gaseous fuel. Outlets of the first nozzles are spaced apart from outlets of the second nozzles. The body includes a third duct with third and fourth nozzles for injecting air. The third nozzles surround an axis of the first nozzles and the fourth nozzles surround an axis of the second nozzles. | 03-08-2012 |
| 20120067051 | GAS TURBINE ENGINE AND COMBUSTOR - The present invention provides in one embodiment a unique gas turbine engine. Another embodiment is a unique gas turbine engine combustion system. Still another embodiment is a unique gas turbine engine combustor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine combustion systems and combustors. | 03-22-2012 |
| 20120073299 | HIGH TEMPERATURE MANIFOLDS FOR GAS TURBINE ENGINES - A fuel manifold for distributing fuel to a gas turbine engine includes a plurality of interconnected manifold segments. Each manifold segment extends between a pair of fuel injector inlet fittings. Each manifold segment includes a fuel liner defining an internal fuel passage therethrough fluidly connecting a pair of fuel injector inlet fittings. A wire braid layer surrounds the fuel liner, a fire sleeve surrounds the wire braid layer, and a flexible thermal shield surrounds the fire sleeve. An insulation space is defined between the fire sleeve and the thermal shield to thermally isolate the fire sleeve from conditions external to the thermal shield. | 03-29-2012 |
| 20120079828 | Gas Turbine Combustor - A gas turbine combustor comprising a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a transition piece which is a flow path for leading combustion gas generated in the liner to turbine blades, and a transition piece flow sleeve for wrapping an outside surface of the transition piece,
| 04-05-2012 |
| 20120102958 | LATE LEAN INJECTION MANIFOLD - A late lean injection (LLI) manifold is provided and includes a central nozzle and first and second side nozzles positioned at circumferential locations defined around a vessel, a connector, a first leg, to which the connector is connected, formed to define a tube extending from the central nozzle to the first side nozzle such that fuel is communicable between the connector, the central nozzle and the first side nozzle and a second leg. The second leg is formed to define a tube extending from the central nozzle to the second side nozzle such that the fuel is communicable between the central nozzle and the second side nozzle. | 05-03-2012 |
| 20120117972 | THERMAL MANAGEMENT FOR FUEL INJECTORS - Methods of managing fuel temperatures in fuel injectors for gas turbine engines include cooling fuel circuits by initiating fuel flow therethrough using opened, closed, and semi-open control techniques. A fuel injector for a gas turbine engine includes a feed arm having a fuel inlet fitting for delivering fuel to at least one fuel conduit extending through the feed arm. A nozzle body depends from the feed arm and has at least one fuel circuit extending therethrough. The fuel circuit is configured and adapted to receive fuel from the feed arm and to issue fuel from an exit orifice of the nozzle body. Sensing means are provided adjacent to the at least one fuel circuit. The sensing means are configured and adapted to provide temperature feedback in order to control fuel flow in the at least one fuel circuit to maintain fuel temperature within a predetermined range. | 05-17-2012 |
| 20120137695 | FUEL NOZZLE WITH GAS ONLY INSERT - The present application provides a fuel nozzle. The fuel nozzle may include a tube and a gas only insert tip positioned on the tube. The gas only insert tip may include a tip aperture. A plug may be positioned within the tip aperture. | 06-07-2012 |
| 20120151929 | AERODYNAMICALLY ENHANCED FUEL NOZZLE - A gas turbine engine fuel nozzle assembly includes a pilot fuel injector tip substantially centered about a centerline axis in an annular pilot inlet to a pilot mixer. A cross over arm extends across inlet to tip. Arm includes an arm fairing surrounding at least one fuel transfer tube to tip. A pilot nose cap is at an upstream end of tip. At least one of the cross over arm and the pilot nose cap includes a rounded forebody followed by a straight afterbody. Rounded forebody of pilot nose cap includes a substantially rounded dome extending forwardly from a rounded nose base and straight afterbody includes a substantially cylindrical nose afterbody parallel to a pilot nose centerline normal to nose base. An arm fairing surrounding fuel transfer tubes to tip includes rounded leading and trailing edges and a rectangular middle section therebetween having flat first and second sides. | 06-21-2012 |
| 20120174588 | GAS-TURBINE LEAN COMBUSTOR WITH FUEL NOZZLE WITH CONTROLLED FUEL INHOMOGENEITY - A gas-turbine lean combustor includes a combustion chamber ( | 07-12-2012 |
| 20120180489 | FUEL INJECTOR - A fuel injector is provided and includes a first tube connectable with a vessel and second and third tubes to deliver fuel to an interior of the vessel, the second and third tubes being supported within the first tube such that the second and third tubes are offset in first and second opposing directions from a first plane of the first tube, respectively, and in a third direction from a second plane of the first tube, the first tube defining an annulus about the second and third tubes through which gas is deliverable to the vessel interior. | 07-19-2012 |
| 20120180490 | FUEL NOZZLE, GAS TURBINE COMBUSTOR WITH THE SAME, AND GAS TURBINE WITH THE SAME - A fuel nozzle for a gas turbine combustor includes: an internal cylinder; a burner cylinder concentrically provided on the outer circumference of the internal cylinder in the vicinity of its distal end to surround the distal end portion of the internal cylinder; an air passage provided between the burner cylinder and the internal cylinder for delivering combustion air; a space provided at an axial center of the internal cylinder and extending in the axial direction of the internal cylinder; a plurality of inner passages provided at approximately equal intervals in the circumferential direction of the internal cylinder for injecting fluid through its distal end portion; and at least one communication portion provided on the upstream side of the distal end portion of the internal cylinder and extending from the outer wall of the internal cylinder toward the inner side in the radial direction to communicate with the space. | 07-19-2012 |
| 20120192566 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A method for assembling a fuel injection assembly for use in a turbine engine is provided. The method includes providing a cap assembly that has at least one first opening extending at least partially through it and a plurality of second openings extending at least partially through it. Moreover, a plurality of tube assemblies are coupled within the cap assembly. Each tube assembly includes a plurality of tubes. Further, at least one injection system is coupled to the cap assembly to enable a fluid from a fluid source to be discharged through at least one of the plurality of second openings. The fluid flows between at least two adjacent tube assemblies to facilitate at least one of reducing a temperature within the cap assembly and reducing dynamic pressure oscillations within a combustor during operation of the turbine engine. | 08-02-2012 |
| 20120198851 | TRAVERSING FUEL NOZZLES IN CAP-LESS COMBUSTOR ASSEMBLY - A combustor includes a central fuel nozzle assembly and a plurality of outer fuel nozzle assemblies, each of the plurality of outer fuel nozzle assemblies having a center body and an outer shroud, the plurality of outer fuel nozzle assemblies being configured to abut one another in a surrounding relationship to the central cylinder such that no gaps are present between any two abutting ones of the plurality of outer fuel nozzle assemblies. One or more of the plurality of fuel nozzle assemblies may traverse axially back and forth according to embodiments of the invention. | 08-09-2012 |
| 20120198852 | MULTIPOINT INJECTOR FOR A TURBINE ENGINE COMBUSTION CHAMBER - A fuel injector device for an annular combustion chamber including a pilot circuit feeding an injector and a multipoint circuit feeding injection orifices formed in a front face of an annular chamber, an annular ring being mounted in the annular chamber to define therein a fuel feed circuit for the injection orifices and a cooling circuit operating by passing the fuel feeding the injector and extending over the front face of the chamber in immediate vicinity of the injection orifices. | 08-09-2012 |
| 20120198853 | MULTIPOINT INJECTION DEVICE FOR A COMBUSTION CHAMBER OF A TURBINE ENGINE - A fuel injector device for an annular combustion chamber of a turbine engine, including a pilot circuit feeding an injector and a multipoint circuit feeding injection orifices formed in a front face of an annular ring mounted in an annular chamber, together with a thermal insulation mechanism insulating the front face and including an annular cavity formed around the injection orifices between the front face of the annular ring and a front wall of the annular chamber and configured to be filled in operation with air or with coked fuel. | 08-09-2012 |
| 20120234011 | GAS TURBINE COMBUSTOR HAVING A FUEL NOZZLE FOR FLAME ANCHORING - A combustor includes an end cover having a nozzle. The nozzle has a front end face and a central axis. The nozzle includes a plurality of fuel passages and a plurality of oxidizer passages. The fuel passages are configured for fuel exiting the fuel passage. The fuel passages are positioned to direct fuel in a first direction, where the first direction is angled inwardly towards the center axis. The oxidizer passages are configured for having oxidizer exit the oxidizer passages. The oxidizer passages are positioned to direct oxidizer in a second direction, where the second direction is angled outwardly away from the center axis. The plurality of fuel passages and the plurality of oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor. | 09-20-2012 |
| 20120272652 | HEAD PART OF AN ANNULAR COMBUSTION CHAMBER - A head part of an annular gas turbine combustion chamber including: an end wall with a passage opening for accommodating a burner, the end wall including a set back portion adjacent the passage opening; a heat shield covering a back side of the end wall which faces towards the combustion chamber, the heat shield including a protruding portion shaped to cooperate with the set back portion of the end wall; and a burner collar adapted to fit within the passage opening and receive a burner, the burner collar including a protruding portion radially protruding from an outer surface of the burner collar; wherein the head part of the annular gas turbine combustion chamber is configured such that in an installed configuration the protruding portion of the burner collar is held between the protruding portion of the heat shield and the set back portion of the end wall. | 11-01-2012 |
| 20120279223 | Fuel Injector and Support Plate - An integrated plate is provided for use with a combustor including a casing, a fuel plenum extending circumferentially about the casing, and a fuel nozzle extending axially through the casing. The integrated plate includes a plurality of fuel injection pegs that extend radially between the fuel plenum and the fuel nozzle. | 11-08-2012 |
| 20120304651 | INTEGRATED FUEL NOZZLE AND IGNITION ASSEMBLY FOR GAS TURBINE ENGINES - There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage. | 12-06-2012 |
| 20120304652 | INJECTOR APPARATUS - An injector apparatus is provided and includes an annular inlet in which a first fluid traveling in a first direction is mixable with a second fluid to form a mixture, an annular outlet disposed downstream from the inlet from which the mixture is injectable into a main flow in a third direction and an annular intermediate section fluidly interposed between the inlet and the outlet and along which the mixture is re-directable from the inlet to the outlet. | 12-06-2012 |
| 20120304653 | LOAD MEMBER FOR TRANSITION DUCT IN TURBINE SYSTEM - A loading assembly for a turbine system is disclosed. The loading assembly includes a transition duct and a load member. The transition duct extends between a fuel nozzle and a turbine section, and has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The load member extends from the transition duct and is configured to transfer a load between the transition duct and an adjacent transition duct along at least one of the longitudinal axis, the radial axis, or the tangential axis. | 12-06-2012 |
| 20130008169 | APPARATUS AND SYSTEMS RELATING TO FUEL INJECTORS AND FUEL PASSAGES IN GAS TURBINE ENGINES - A combustor casing fuel injector in a combustor of a combustion turbine engine, the combustor including a combustor casing that encloses internal structure of the combustor, wherein the combustor casing fuel injector includes a fuel manifold adjacent to an outer surface of the combustor casing. In certain embodiments, the combustor casing fuel injector includes a fuel injector; wherein the fuel injector extends through the combustor casing from a position within the fuel manifold to a predetermined fuel injection location; and wherein the fuel injector includes a protruding injector inlet within the fuel manifold. | 01-10-2013 |
| 20130025285 | SYSTEM FOR CONDITIONING AIR FLOW INTO A MULTI-NOZZLE ASSEMBLY - A system includes a turbine fuel nozzle assembly. The turbine fuel nozzle assembly includes a first fuel nozzle including a first air inlet and a second fuel nozzle including a second air inlet. The turbine fuel nozzle assembly also includes a first inlet flow conditioner disposed adjacent the first air inlet of the first fuel nozzle, wherein the first air inlet flow conditioner extends only partially around the first fuel nozzle. The turbine fuel nozzle further includes a second inlet flow conditioner disposed adjacent the second air inlet of the second fuel nozzle, wherein the second air inlet flow conditioner extends only partially around the second fuel nozzle, and the second inlet flow conditioner is separate from the first inlet flow conditioner. | 01-31-2013 |
| 20130031907 | FUEL INJECTING ASSEMBLY FOR GAS TURBINE ENGINE - A fuel injecting assembly for a combustor of a gas turbine engine has a gas supply structure, steam supply structure and oil fuel nozzle that are substantially separated to allow relative movement between a respective end section, end portion and end part due to thermal expansion and contraction. | 02-07-2013 |
| 20130036740 | MULTI-FUEL INJECTION NOZZLE - A multi-fuel nozzle ( | 02-14-2013 |
| 20130055719 | FUEL SUPPLY DEVICE OF GAS TURBINE ENGINE - In a fuel supply device of a gas turbine engine of the present invention, a fuel divider | 03-07-2013 |
| 20130061594 | TURNING GUIDE FOR COMBUSTION FUEL NOZZLE IN GAS TURBINE AND METHOD TO TURN FUEL FLOW ENTERING COMBUSTION CHAMBER - A fuel nozzle assembly for a gas turbine, the assembly including: a cylindrical center body; a cylindrical shroud coaxial with and extending around the center body, and a turning guide having an downstream edge extending in a passage between the center body and an inlet to the shroud, wherein the turning guide extends only partially around the center body. | 03-14-2013 |
| 20130074503 | SYSTEM FOR SUPPLYING PRESSURIZED FLUID TO A CAP ASSEMBLY OF A GAS TURBINE COMBUSTOR - A system for supplying pressurized fluid to a combustor of a gas turbine is disclosed. The system may include an end cover and a fuel nozzle extending from the end cover. The fuel nozzle may include a downstream end. Additionally, the system may include a cap assembly configured to receive at least a portion of the fuel nozzle. The cap assembly may include an upstream wall spaced apart from the downstream end, a downstream wall disposed proximate to the downstream end and a cap chamber defined between the upstream and downstream walls. Moreover, a conduit may extend through the end cover and the upstream wall such that a discharge end of the conduit is in flow communication with the cap chamber. | 03-28-2013 |
| 20130098043 | Hydrajetting Nozzle and Method - A jetting device comprises a body, and an interior flow path within the body. The interior flow path comprises a flow section, an expansion section, and a shoulder formed at the intersection of the flow section and the expansion section. The length and diameter of the expansion section are configured to allow a portion of the pressure of the fluid downstream of the expansion section to provide power to a fluid flowing through the nozzle when the fluid is flowing through the nozzle. | 04-25-2013 |
| 20130104553 | INJECTION APPARATUS | 05-02-2013 |
| 20130104554 | BURNER ASSEMBLY | 05-02-2013 |
| 20130118177 | FUEL INJECTION SYSTEM FOR TURBOJET ENGINE AND METHOD OF ASSEMBLING SUCH AN INJECTION SYSTEM - A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion. | 05-16-2013 |
| 20130125550 | GAS TURBINE COMBUSTION CHAMBER - A gas turbine combustion chamber is provided including a pilot fuel nozzle arranged in the central section of a cylinder that opens at one end towards a combustion chamber. The pilot fuel nozzle includes a fuel nozzle and a cylindrical outer casing around the outer circumference of the fuel nozzle. A pilot swirl element is arranged between fuel nozzle and outer casing, including a plurality of main burners which are arranged around the pilot fuel nozzle, and including a pilot cone having an inner side and an outer side. The pilot cone is arranged on the pilot fuel nozzle and an opening, such that a pilot flame is formed in the pilot cone by mixing air and pilot fuel in order to ignite a fuel injected by the main burners, wherein the pilot cone has turbulence generators on the inner side and/or outer side thereof. | 05-23-2013 |
| 20130139512 | LEAF SPRING DAMPER FOR A TURBINE ENGINE FUEL DELIVERY SYSTEM - A turbine engine fuel delivery system includes a mounting platform, a spray bar assembly and a leaf spring damper with a stack of a plurality of leaf springs. The stack includes a base segment connected longitudinally between a first spray bar contact segment and a second spray bar contact segment. The base segment is connected to the mounting platform and is located a first distance from the spray bar assembly. The first spray bar contact segment engages the spray bar assembly and is located a second distance from the mounting platform. The second spray bar contact segment engages the spray bar assembly and is located a third distance from the mounting platform. | 06-06-2013 |
| 20130139513 | FUEL NOZZLE AND METHOD OF REPAIR - A modular fuel nozzle tip for a gas turbine engine includes a body defining one or more fuel conveying passages extending therethrough, an annular cap having a radially inner shoulder surface interfacing with the peripheral end surface of the body to define a plurality of air channels extending through the head portion of the modular fuel nozzle tip. At least two fasteners fasten the annular cap to the body. | 06-06-2013 |
| 20130145766 | TWO-STAGE COMBUSTOR FOR GAS TURBINE ENGINE - A combustor for a gas turbine engine comprises an inner annular liner wall and an outer annular liner wall cooperating to form a combustion chamber of the combustor. A first dome wall has a circumferential array of first fuel injection bores. A second dome has a circumferential array of second fuel injection bores, An intermediate wall extends between the first dome wall and the second dome wall. A first combustion stage is defined by the inner liner wall forward end, the first dome wall and the intermediate wall. A second combustion stage is defined at least by the outer liner wall forward end, the second dome wall and the intermediate wall, the first combustion stage communicating with the first fuel injection bores, the second combustion stage communicating with the second fuel injection bores. | 06-13-2013 |
| 20130145767 | TWO-STAGE COMBUSTOR FOR GAS TURBINE ENGINE - A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. First and second combustion stages are defined between the liners. Each combustion stage has a plurality of fuel injection bores distributed in a liner wall defining the respective stage. A lobed mixer extends into the combustor, the lobed mixer arranged to receive combustion gases from each combustion stage for mixing flows of said combustion gases. | 06-13-2013 |
| 20130180249 | SYSTEM FOR INJECTING A FLUID, COMPRESSOR AND TURBOMACHINE - A system for injecting a fluid into a wall boundary layer of a flow in a turbomachine is disclosed. The system has a plurality of nozzles which are disposed in a side wall limiting the flow and are oriented diagonally in the direction of flow. The nozzles each have a rectangular, flat nozzle cross-section. A compressor having such a system, as well as a turbomachine having such a compressor, are also disclosed. | 07-18-2013 |
| 20130180250 | FUEL SUPPLY APPARATUS, FUEL-FLOW-RATE-CONTROL APPARATUS, AND GAS-TURBINE POWER PLANT - A fuel supply apparatus is provided with a plurality of flow-rate regulating valves that regulate the flow rate of fuel flowing in a fuel supply line; a calculating section that calculates a required flow-rate coefficient on the basis of at least a fuel pressure in the fuel flow upstream of the flow-rate regulating valves, a pressure determined in advance as a fuel pressure downstream of the flow-rate regulating valves, and the flow rate of fuel to be supplied to one fuel nozzle among different kinds of fuel nozzles, the required flow-rate coefficient being the coefficient of the flow-rate regulating valve corresponding to the one fuel nozzle; and a valve control section that controls the degree-of-opening of the flow-rate regulating valve corresponding to the one fuel nozzle on the basis of the required flow-rate coefficient. | 07-18-2013 |
| 20130186093 | PROCESS OF FABRICATING A FUEL NOZZLE ASSEMBLY, PROCESS OF FABRICATING A FUEL NOZZLE RING, AND A FUEL NOZZLE RING - Disclosed is a process of fabricating a fuel nozzle assembly, a process of fabricating a fuel nozzle ring, and a fuel nozzle ring. The process of fabricating the fuel nozzle assembly includes providing a fuel nozzle end cover, positioning a fuel nozzle ring within a cavity of the fuel nozzle end cover, and securing the fuel nozzle ring to the fuel nozzle end cover to form features corresponding to one or more of the fuel nozzle end cover and a fuel nozzle insert. The process of fabricating the fuel nozzle ring includes forming the fuel nozzle ring with at least one surface corresponding to one or more of a fuel nozzle end cover and a fuel nozzle insert. The fuel nozzle ring includes at least one surface corresponding to one or more of a fuel nozzle end cover and a fuel nozzle insert. | 07-25-2013 |
| 20130199190 | 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 a plurality of tube assemblies wherein each of the plurality of tube assemblies includes a plurality of tubes. At least one injection system is coupled to at least one tube assembly of the plurality of tube assemblies. The injection system includes a fuel delivery pipe and a fluid supply member coupled to the fuel delivery pipe, wherein the fluid supply member is positioned a predefined distance upstream from the tube assembly and includes at least one first portion having an annular end portion. The annular end portion includes at least one opening for delivering fluid toward the tube assembly for reducing dynamic pressure oscillations and/or reducing the temperature within a combustor during operation of the turbine engine. | 08-08-2013 |
| 20130205789 | FUEL NOZZLE END COVER, FUEL NOZZLE, AND PROCESS OF FABRICATING A FUEL NOZZLE END COVER - Disclosed is a fuel nozzle end cover, a fuel nozzle and a process of fabricating a fuel nozzle end cover. The fuel nozzle end cover includes a base material and one or more features extending from the base material into a cavity of the fuel nozzle end cover. The one or more features are secured to the base material by a process selected from the group consisting of beam welding, friction welding, gas tungsten arc welding, gas metal arc welding, and combinations thereof. The fuel nozzle includes a fuel nozzle insert and a fuel nozzle end cover. The process of fabricating the fuel nozzle end cover includes providing a base material and securing one or more features to the base material by a welding process selected from the group consisting of beam welding, friction welding, gas tungsten arc welding, gas metal arc welding, and combinations thereof. | 08-15-2013 |
| 20130213046 | LATE LEAN INJECTION SYSTEM - A late lean injection system includes at least one fuel injector disposed proximate a combustion zone. Also included is at least one guide for directing an airflow from a region proximate a compressor discharge exit to the at least one fuel injector. | 08-22-2013 |
| 20130219900 | Gas Turbine Combustor - The present invention provides a gas turbine combustor that has a fuel injection nozzle using a fluid other than liquid fuel to atomize the liquid fuel and that can suppress a reduction in power generation efficiency resulting from a heat loss while promoting the atomization of the liquid fuel. The gas turbine combustor is adapted to mix liquid fuel with combustion air led from a compressor, burn the mixture, and supply combustion gas generated to a gas turbine. The gas turbine combustor includes a fuel injection nozzle that atomizes the liquid fuel into fine liquid droplets. The fuel injection nozzle includes a first system adapted to supply the liquid fuel and a second system adapted to supply a fluid for atomizing the liquid fuel. Low-boiling liquid fuel is supplied to the second system as the fluid. The second system is adapted to heat and supply the low-boiling liquid fuel. | 08-29-2013 |
| 20130255264 | NOZZLE ASSEMBLY - A nozzle assembly ( | 10-03-2013 |
| 20130263603 | NOZZLE DESIGN TO REDUCE FRETTING - A method of designing a fuel nozzle of a gas turbine engine to reduce fretting thereof during use, including establishing an initial nozzle design, determining a first natural frequency of that design and a running frequency range of the gas turbine engine, and increasing a first transverse dimension of the stem member of the nozzle across a length of a portion thereof adjacent the inlet end until the first natural frequency of the nozzle is outside the running range, while a second transverse dimension of the portion remains at least substantially unchanged across the length thereof. | 10-10-2013 |
| 20130276450 | COMBUSTOR APPARATUS FOR STOICHIOMETRIC COMBUSTION - Gas turbine combustor with a specific fuel and oxidizer flow arrangement which provides high combustion efficiency for stoichiometric diffusion combustion in gas turbine applications operating with oxygen deficient working fluids. | 10-24-2013 |
| 20130283804 | TRANSITION DUCT WITH LATE INJECTION IN TURBINE SYSTEM - A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber. | 10-31-2013 |
| 20130298563 | Secondary Combustion System - The present application provides a secondary combustion system for introducing a fuel/air mixture into a flow of combustion gases in a combustor of a gas turbine engine. The secondary combustion system may include a manifold ring and a number of injectors extending from the manifold ring. Each of the injectors may include a number of jets in communication with the manifold ring. One or more of the jets may include an angled configuration for the introduction of the fuel/air mixture into the flow of combustion gases at an angle. | 11-14-2013 |
| 20140033724 | FUEL NOZZLE ASSEMBLY AND METHODS OF ASSEMBLING SAME - A fuel nozzle assembly for use with a turbine engine is provided. The fuel nozzle assembly includes a tube assembly that includes a plurality of openings, wherein the tube assembly is configured to channel at least a first type of fuel through the turbine engine. A plurality of fasteners are removably coupled to the tube assembly such that each of the fasteners are severally removable from the tube assembly to enable a plurality of different types of fuel to be channeled through the turbine engine for operation of the turbine engine. | 02-06-2014 |
| 20140033725 | INJECTOR SEAL FOR A GAS TURBOMACHINE - An injector seal for a gas turbomachine includes a seal body having a first surface, an opposing second surface, a central opening configured and disposed to receive a gas turbomachine injector, an outer edge, and a plurality of passages extending through the seal body. The plurality of passages are configured and disposed to guide a fluid at the first surface through the second surface. | 02-06-2014 |
| 20140060059 | FUEL DELIVERY SYSTEM WITH A CAVITY COUPLED FUEL INJECTOR - A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area. | 03-06-2014 |
| 20140069103 | SEAL FOR USE BETWEEN INJECTOR AND COMBUSTION CHAMBER IN GAS TURBINE - A seal assembly for use between an injector and a combustion chamber in a gas turbine. A liner at least partially defines the combustion chamber, and the liner has at least one tubular liner collar, through which an injector is inserted. In one embodiment, the liner collar has a partially convex outer diameter and a floating collar is positioned at least partially around the liner collar. The floating collar has a retention member having a first end fixed to the floating collar and a second end configured to abut the convex outer diameter of liner collar, wherein the retention member maintains the floating collar at a radial distance from the injector less than a radial distance between the liner collar and the injector. | 03-13-2014 |
| 20140075949 | MULTIPOINT FUEL INJECTION ARRANGEMENTS - A multipoint fuel injection system includes a plurality of fuel manifolds. Each manifold is in fluid communication with a plurality of injectors arranged circumferentially about a longitudinal axis for multipoint fuel injection. The injectors of separate respective manifolds are spaced radially apart from one another for separate radial staging of fuel flow to each respective manifold. | 03-20-2014 |
| 20140083103 | GAS TURBINE ASYMMETRIC NOZZLE GUIDE VANES - A gas turbine engine includes a multiple of Nozzle Guide Vanes (NGVs) arranged asymmetrically and a multiple of NGVs clocked with respect to the multiple of fuel nozzles around a 360 degree circumference. | 03-27-2014 |
| 20140090381 | INJECTION DEVICE FOR A COMBUSTION CHAMBER OF A TURBINE ENGINE - A fuel injection device ( | 04-03-2014 |
| 20140090382 | ANNULAR COMBUSTION CHAMBER FOR A TURBINE ENGINE - An annular combustion chamber for a turbine engine, the chamber including an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall, each injector head including at least one fuel-passing helical channel for causing fuel to rotate about the longitudinal axis of the head, and each injection system including at least one swirler including air-passing channels of sections with axes that are inclined relative to the plurality axis of the swirler at an angle that is substantially equal to a helix angle of the helical channel, to within ±10°, and are oriented in a same direction as the channel about the longitudinal axis of the swirler. | 04-03-2014 |
| 20140109584 | MODULATING ELECTRIC LIQUID METERING VALVE WITH FLOW SENSING - A fluid flow valve includes a movable valve piston positioned in a valve body, the valve piston configured to flow a fluid therethrough. A metering window is interactive with the movable valve piston to meter flow through the movable valve piston. A flow meter is positioned at the valve piston to measure a flow rate of fluid through the valve piston. A valve controller is operable connected to the flow meter and the movable valve piston to control position of the valve piston based on flow rate measured at the flow meter. | 04-24-2014 |
| 20140109585 | High Pressure Relief Valve Nozzle - In one featured embodiment, a nozzle for a valve comprises a nozzle body surrounding a center axis and defined by an overall length extending from an inlet end to an outlet end. The nozzle body has a nozzle bore defined by an outlet bore inner diameter at the outlet end and an inlet bore inner diameter at the inlet end. The inlet bore inner diameter is greater than the outlet bore inner diameter, and the nozzle body has a nozzle face defined at the outlet end. The nozzle face is defined between the outlet bore inner diameter and an outlet bore outer diameter spaced radially outwardly of the outlet bore inner diameter. A ratio of the outlet bore inner bore diameter to the outlet bore outer diameter at the nozzle face is between 0.95 and 0.98. | 04-24-2014 |
| 20140116055 | COMBUSTION SYSTEM - A first orifice on a first inner surface of a first annular zone of a forward-bounded annular combustor provides for injecting air forward and radially outwards thereinto, from a location aft of a fuel slinger/injector. A radial dimension of a first outer surface of the first annular zone exceeds that of a corresponding first inner surface. A radial dimension of a second outer surface of a second annular zone of the annular combustor—aft of the first annular zone—exceeds that of a corresponding second inner surface. The first and second outer surfaces, and the first and second inner surfaces, are respectively coupled by transitional outer and inner surfaces of an annular transition zone located therebetween. The radial dimensions of the transitional outer and inner surfaces at the junctions with the corresponding second surfaces exceed the corresponding radial dimensions at the junctions with the corresponding first surfaces. | 05-01-2014 |
| 20140123653 | ENHANCEMENT FOR FUEL INJECTOR - A fuel injector is provided and includes a surface disposed proximate to a flow of a first fluid and a delta wing feature. The surface has upstream and downstream portions defined relative to the flow and defines an injector hole in the downstream portion by which a jet of a second fluid is injectable into the flow. The delta wing feature is disposed on the surface at the upstream portion and is configured to lift an oncoming portion of the flow off the surface and to cause the oncoming portion of the flow to form a pair of counter-rotating vortices that respectively co-rotate with the jet in a cross-flow direction. | 05-08-2014 |
| 20140174089 | SYSTEM FOR REDUCING FLAME HOLDING WITHIN A COMBUSTOR - A system for reducing flame holding within a combustor includes a high pressure plenum and a head end plenum defined within the combustor. A cap assembly defines an inner plenum within the combustor and a fuel nozzle passage that extends through the cap assembly. A primary fuel nozzle has an annular burner tube that at least partially defines a premix flow passage through the cap assembly. The primary fuel nozzle and the burner tube at least partially define an inlet to the premix flow passage. A high pressure flow passage and a cooling flow passage are defined within the combustor. The high pressure flow passage defines a flow path between the high pressure plenum and the inner plenum, and the cooling flow passage defines a flow path between the high pressure plenum and the head end plenum. | 06-26-2014 |
| 20140174090 | SYSTEM FOR SUPPLYING FUEL TO A COMBUSTOR - A system for supplying fuel to a combustor includes a combustion chamber and a liner that circumferentially surrounds at least a portion of the combustion chamber. A plurality of fuel nozzles are radially arranged across the combustor upstream from the combustion chamber to supply a swirling flow of fuel into the combustion chamber. A first fuel injector downstream from the plurality of fuel nozzles provides fluid communication for fuel to flow through the liner and into the combustion chamber. The first fuel injector is circumferentially clocked with respect to the swirling flow of fuel in the combustion chamber. | 06-26-2014 |
| 20140182295 | CONTINUOUS DETONATION WAVE ENGINE AND AIRCRAFT PROVIDED WITH SUCH AN ENGINE - The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine ( | 07-03-2014 |
| 20140202160 | GAS TURBINE SYSTEM WITH MANIFOLD - A system including a gas turbine engine, including a combustor configured to generate products of combustion, a turbine driven by the products of combustion from the combustor, a compressor having a compressor discharge leading into a chamber between the combustor and a compressor discharge casing, an extraction manifold coupled to the combustor, wherein the extraction manifold is fluidly coupled to the chamber. | 07-24-2014 |
| 20140208757 | Air/Fuel Supply System for Use in a Gas Turbine Engine - A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main body comprises a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet. The fuel supply structure communicates with and supplies fuel to the air/fuel passages for providing an air/fuel mixture within each air/fuel passage. The air/fuel mixtures exit the main body through respective air/fuel passage outlets. | 07-31-2014 |
| 20140245740 | COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE - A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall. | 09-04-2014 |
| 20140260275 | FLOW SLEEVE ASSEMBLY FOR A COMBUSTION MODULE OF A GAS TURBINE COMBUSTOR - A flow sleeve assembly for a combustor of a gas turbine includes an annular support sleeve disposed at a forward end of the flow sleeve assembly. The support sleeve includes a forward portion axially separated from an aft portion. An aft frame is disposed at an aft end of the flow sleeve assembly. An annular flow sleeve extends from the aft portion of the support sleeve towards the aft frame. The flow sleeve includes a forward end that is axially separated from an aft end. The forward end of the flow sleeve circumferentially surrounds the aft end of the support sleeve. An annular impingement sleeve extends between the aft end of the flow sleeve and the aft frame. A forward end of the impingement sleeve is connected to the aft end of the flow sleeve, and an aft end of the impingement sleeve is connected to the aft frame. | 09-18-2014 |
| 20140318136 | Gas Turbine Combustor Including a Transition Piece Flow Sleeve Wrapped on an Outside Surface of a Transition Piece - A gas turbine combustor including a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a transition piece which is a flow path for leading combustion gas generated in the liner to turbine blades, and a transition piece flow sleeve for wrapping an outside surface of the transition piece, wherein a plurality of air introduction holes for introducing air into the transition piece flow sleeve are formed in regions of the transition piece flow sleeve excluding regions which are corner portions of the transition piece flow sleeve in a sectional direction thereof. | 10-30-2014 |
| 20140331676 | TAPERED GAS TURBINE ENGINE LIQUID GALLERY - A liquid gallery for a fuel injector of a gas turbine engine includes a gallery body, a liquid gallery scroll, a plurality of atomizer inlets, and a plurality of atomizer bosses. The liquid gallery scroll extends into the gallery body spanning from a first end to a second end in a circumferential direction. The liquid gallery scroll includes a taper with a cross-sectional area of the liquid gallery scroll reducing from the first end to the second end. Each atomizer inlet is in flow communication with the liquid gallery scroll. Each atomizer boss is aligned with one of the plurality of atomizer inlets. | 11-13-2014 |
| 20140331677 | OUTER PREMIX BARREL VENT AIR SWEEP - A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet. | 11-13-2014 |
| 20140338341 | LIQUID FUEL TURBINE ENGINE FOR REDUCED OSCILLATIONS - A gas turbine engine may include a plurality of pilot fuel supply lines configured to supply liquid fuel. Each pilot fuel supply line may be coupled to a respective fuel injector. The turbine engine may include a plurality of main fuel supply lines configured to supply liquid fuel. Each main fuel supply line may be coupled to a respective fuel injector. The turbine engine may also include a flow restriction provided in a first plurality of the plurality of main fuel supply lines. A second plurality of the plurality of main fuel supply lines may be free from the flow restriction. | 11-20-2014 |
| 20140338342 | FUEL INJECTOR HAVING AN IGNITOR FOR IGNITING A COMBUSTOR OF A GAS TURBINE - A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid circuit extends at least partially through the main body. An axially extending inner body extends within the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid circuit. A retractable igniter extends linearly outward from the inner chamber when the fluid circuit is charged. | 11-20-2014 |
| 20140338343 | SYSTEM FOR VIBRATION DAMPING OF A FUEL NOZZLE WITHIN A COMBUSTOR - A system for vibration damping a fuel nozzle within a combustor includes a support plate, a fuel nozzle passage that extends through the support plate and a cylindrical damping insert that is coaxially aligned within the fuel nozzle passage and at least partially defines the fuel nozzle passage. The damping insert may include a metallic-mesh liner. | 11-20-2014 |
| 20150007572 | FUEL INJECTOR FOR A TURBINE ENGINE - A fuel injector for a turbine engine, the injector including a body including a mechanism for admitting fuel under pressure, a stop valve for feeding a primary fuel circuit, and a metering valve mounted downstream from the stop valve for feeding a secondary fuel circuit. The injector further includes at least one leakage channel, that can be formed by a thread, that extends from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary circuit. | 01-08-2015 |
| 20150068210 | TUBE FED TANGENTIAL ON-BOARD INJECTOR FOR GAS TURBINE ENGINE - A tangential on-board injector assembly for a gas turbine engine includes an annular housing including a plenum. A plurality of discrete tubes is fluidly connected to the plenum and is configured to provide a cooling fluid to the annular housing. | 03-12-2015 |
| 20150322891 | CRYOGENIC FUEL COMBUSTION ENGINES - The invention relates to systems enabling the use of cryogenic fuels within combustion engines, including jet engines. | 11-12-2015 |
| 20160003142 | GEARED TURBOFAN WITH GEARBOX SEAL - A gas turbine engine comprises a fan, a compressor section, a turbine section, and a gear reduction for driving the fan through the turbine section. A rotating element and at least one bearing compartment includes a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment, and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. The seal has a plurality of sealing members extending radially toward a sealing surface. | 01-07-2016 |
| 20160010865 | FUEL LANCES HAVING THERMALLY INSULATING COATING | 01-14-2016 |
| 20160017808 | COMPACT DOSING DEVICE FOR AN INJECTOR WITH TWO FUEL CIRCUITS FOR AN AIRCRAFT TURBOMACHINE - A fuel dosing device for a fuel injector of an aircraft turbomachine, including an opening, a movable member for sealing the opening, and elastic return, with the member able to be displaced under the effect of the fuel pressure. The device includes a first outlet communicating with a primary circuit of the injector as well as a second outlet communicating with a secondary circuit. In addition, it is designed such that up to a defined level of displacement of the sealing member, the latter allows the fuel coming from the opening to reach the first outlet and, only beyond the defined level of displacement, the member allows the fuel coming from the opening to reach the second outlet. | 01-21-2016 |
| 20160033130 | FUEL NOZZLE FOR A GAS TURBINE ENGINE - A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator. | 02-04-2016 |
| 20160033134 | SEAL IN COMBUSTOR NOZZLE OF GAS TURBINE ENGINE - A nozzle for use in a combustor of a combustion turbine engine, the nozzle including: radial sections defined by sidewalls; a gap formed between opposing sidewalls of adjacent ones of the radial sections; a groove formed on each of the sidewalls that define the gap, the grooves positioned correspondingly so to together form a pocket; and a seal having a zigzagging profile disposed within the pocket. The pocket may intercept the gap over a seal length, and the seal may extend longitudinally within the pocket such that the zigzagging profile intersects the gap over the seal length. | 02-04-2016 |
| 20160047314 | NOZZLE HAVING AN ORIFICE PLUG FOR A GAS TURBOMACHINE - A gas turbomachine nozzle includes a base portion having a first fluid inlet and a second fluid inlet, and an outlet portion having one or more outlets. A connection section fluidically connects the base portion and the outlet portion. An orifice plug is arranged in the base portion at the second fluid inlet. The orifice plug includes one or more openings fluidically connecting the second fluid inlet and the connection section. | 02-18-2016 |
| 20160047316 | SYSTEMS AND APPARATUS RELATING TO GAS TURBINE COMBUSTORS - A gas turbine engine having a combustor that includes: an inner radial wall defining axially stacked first and second interior chambers, wherein the first interior chamber extends axially from an end cover to a fuel nozzle, and the second interior chamber extends axially from the fuel nozzle to an inlet of the turbine; and an outer radial wall formed about the inner radial wall so to form a flow annulus therebetween. The flow annulus may include a flow conditioning section that has: conditioning passages defined therethrough for directing a flow from inlets formed at an upstream end to outlets formed at a downstream end of the flow conditioning section; and structure rigidly attaching the inner radial wall to the outer radial wall. | 02-18-2016 |
| 20160047317 | FUEL INJECTOR ASSEMBLIES IN COMBUSTION TURBINE ENGINES - A downstream nozzle for use in a combustor that includes an inner radial wall defining a combustion zone downstream of a primary nozzle and an outer radial wall surrounding the inner radial wall so to form a flow annulus therebetween. The downstream nozzle may include: an injector tube extending between the outer radial wall and the inner radial wall; a first plenum adjacent to the injector tube, and, inboard of the ceiling, a floor disposed between the inner radial wall and the outer radial wall. A feed passage may connect the first plenum to an inlet formed outboard of the outer radial wall and impingement ports may be formed through the floor of the first plenum. | 02-18-2016 |
| 20160109134 | FUEL SUPPLY SYSTEM, JET ENGINE AND MANUFACTURING METHOD OF FUEL SUPPLY SYSTEM - A fuel supply system includes a fuel reformer disposed to contact at least one of a combustion chamber or a wall of the combustion chamber. The fuel reformer includes a reformer chamber wall enclosing a fuel reformer chamber, and a reforming catalyst support sheet disposed in the fuel reformer chamber. | 04-21-2016 |
| 20160123231 | FLANGE WITH CURVED CONTACT SURFACE | 05-05-2016 |
| 20160161123 | FUEL SUPPLY SYSTEM FOR A GAS TURBINE ENGINE - In one aspect, a fuel supply system may include a fuel injector having a primary and a secondary pilot fuel nozzle in fluid communication with a primary and a secondary fuel circuit, respectively, and a main fuel nozzle in fluid communication with a main fuel circuit. The fuel injector may also define a by-pass fuel circuit connected between the primary circuit and the secondary circuit and/or the main circuit. The system may also include a primary fuel manifold configured to be fluidly connected to the primary pilot fuel nozzle via the primary fuel circuit. Moreover, the system may include a by-pass valve provided in operative association with the by-pass fuel circuit. The by-pass valve may be configured to be opened such that a portion of the fuel flowing through the primary circuit from the primary fuel manifold is directed to the secondary circuit and/or the main circuit. | 06-09-2016 |
| 20160161124 | SINGLE-FITTING, DUAL-CIRCUIT FUEL NOZZLE - A manifold fitting receiving radial and axial manifolds and providing two radial outlets is disclosed. The manifold fitting, when used in conjunction with a fuel injector and a combustor for a gas turbine engine, reduces the radial footprint of the fuel injector and thereby allows for a more compact engine. Additionally, the manifold fitting eliminates parts, reducing weight in the process, as compared to prior art fittings. Such reductions in size, parts count, and weight are particularly beneficial for aircraft applications. | 06-09-2016 |
| 20160169521 | SWIRLER MOUNT INTERFACE FOR GAS TURBINE ENGINE COMBUSTOR | 06-16-2016 |
| 20160169522 | FUEL INJECTOR GUIDE(S) FOR A TURBINE ENGINE COMBUSTOR | 06-16-2016 |
| 20160169523 | FUEL INJECTION DEVICE FOR GAS TURBINE | 06-16-2016 |
| 20160177837 | FUEL/AIR MIXING SYSTEM FOR FUEL NOZZLE | 06-23-2016 |
| 20160252252 | LINE REPLACEABLE FUEL NOZZLE APPARATUS, SYSTEM AND METHOD | 09-01-2016 |
| 20170234539 | CONNECTION DEVICE COMPRISING SEVERAL CURVED CONCENTRIC TUBES | 08-17-2017 |
| 20180023478 | IGNITION DEVICE AND GAS TURBINE COMBUSTOR | 01-25-2018 |
| 20190145619 | FUEL SWIRLER WITH ANTI-ROTATION FEATURES | 05-16-2019 |
