Abstract: The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels. The system may include (a) a low energy gas delivery system comprising a low energy gas inlet, a gas split, a low energy gas primary manifold outlet, and a low energy gas secondary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; (c) a primary manifold; and (d) a secondary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold, wherein the low energy gas secondary manifold outlet is coupled to the secondary manifold, and wherein the low energy gas delivery system further comprises a primary low energy gas stop and pressure control valve between the gas split and the low energy gas primary manifold outlet.

Abstract: A gas turbine combustion system includes a supporting fuel manifold including a plurality of fuel nozzle support openings and a plurality of fuel line passages, and an aft case defining at least part of a combustion zone. The supporting fuel manifold is connected to the aft case. A plurality of fuel nozzles are supported one each in the plurality of fuel nozzle support openings, and a plurality of fuel lines communicate with the plurality of fuel line passages. The plurality of fuel lines deliver fuel to the plurality of fuel nozzles via the plurality of fuel line passages.

Abstract: A mounting system for locating a combustor and a fuel manifold of a gas turbine engine within a gas generator casing thereof is described. The mounting system comprises at least three support pin assemblies which extend radially inwardly from the gas generator casing. The support pin assemblies support both the fuel manifold and at least an upstream end of the combustor and maintaining engagement between the fuel manifold and the combustor during operation of the gas turbine engine.

Abstract: 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.

Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing having a longitudinal axis. The injector housing includes one or more fuel galleries annularly disposed about the longitudinal axis, and a compressed air inlet. The fuel injector also includes a premix barrel having a proximal end and a distal end circumferentially disposed about the longitudinal axis. The premix barrel is fluidly coupled to the fuel galleries and the compressed air inlet at the proximal end and is configured to couple to a combustor of the gas turbine engine at the distal end. The fuel injector also includes a substantially cylindrical pilot assembly disposed radially inwards of the premix barrel having a first end and a second end. The second end is coupled to the injector housing and the first end is located proximate the distal end of the premix barrel.

Abstract: A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.

Abstract: A fuel supply system includes a fuel metering pump and a servo-flow pump that are used to supply fuel to one or more fuel manifolds and one or more fluid-operated actuators, respectively. The fuel metering pump and the servo-flow pump are driven by the same electric motor(s).

Abstract: A fuel system for a turbine engine is provided. The fuel system includes a positive displacement pump driven by an electric motor. The pump is rotated in a first direction to deliver fuel to the turbine engine, and a second direction for evacuating fuel from the turbine engine. A shut-off check valve is open in a first direction in response to a first differential pressure created by the pump in the first direction. The shut-off check valve is biased to a closed position when the pump is rotating in the second direction. An ecology check valve is biased to a closed position in the first direction and open in the second direction in response to a second differential pressure created by the pump. The check valves open and close automatically in response to the pressures generated by the positive displacement pump in each of the first and second rotational directions. In this manner, simple, reliable valves are utilized to regulate the flow of fuel in the fuel system.

Abstract: Integrally formed, multi zone fuel manifolds for gas turbine engines and methods of construction are provided. The fuel manifold includes a plurality of annular channel members positioned adjacent each other, aligned and coupled together at the inner and outer peripheral sides thereof, with each pair of channel members defining a separate fluid conduit or passage within the manifold assembly. The fuel manifold can be constructed of any number of stacked and secured channel members to provide a compact multi zone fuel manifold having the desired number of fluid conduits or passages with a minimum number of sealed joints.

Abstract: A mounting method and system for supporting and positioning an internal fuel manifold relative to a combustor in a fuel injection system for a gas turbine engine. The method includes positioning the fuel manifold within a gas generator casing, applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, and using the heat shield to at least partially support the fuel manifold within the gas generator casing.

Abstract: An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles includes a substantially flat plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel passage extends through the substantially flat plate. A fuel manifold porting block is secured to the opposite side of the flat plate with at least one port aligned with the at least one passage. A fuel restrictor insert formed with multiple flow orifices is located between the flat plate and the fuel manifold porting block in alignment with the at least one fuel passage and the at least one port.

Abstract: A system includes a turbine engine with a fueling system including a valve fluidly coupled to a fuel supply on an upstream side and fluidly coupled to fueling passages on a downstream side. The valve maintains the fuel supply at a pressure greater than an ambient pressure. The system includes nozzle exits corresponding to the fueling passages, and the fueling passages flow fuel from the valve to each of the nozzle exits monotonically downward. The valve is a check valve or a controlled valve. The valve maintains the fuel supply at a pressure such that fuel in the fuel supply is a continuous fluid phase. The fuel leaves the nozzle exits to the combustion chamber of the turbine engine.

Abstract: A thermally diluted exothermic reactor system is comprised of numerous orifices distributed within a combustor by distributed perforated contactor tubes or ducts. The perforated contactors deliver and mix diluent fluid and one or more reactant fluids with an oxidant fluid. Numerous micro-jets about the perforated tubes deliver, mix and control the composition of reactant fluid, oxidant fluid and diluent fluid. The reactor controls one or more of composition profiles, composition ratio profiles and temperature profiles in one or more of the axial direction and one or two transverse directions, reduces temperature gradients and improves power, efficiency and emissions.

Abstract: A combustor, in which a flame holding region is formed at a location distant from a pilot burner to avoid burnout of the pilot burner and in which flame holding capability is increased to use a lean pre-mix gas for reducing NOx emission, is provided. The combustor includes a combustion liner having a cylindrical side wall that defines a combustion chamber; and a main burner positioned at a top portion of the combustion liner for injecting an annular pre-mix gas into the combustion chamber to form a reverse flow region at a downstream portion thereof, which region is oriented towards the top portion of the combustion chamber along a longitudinal axis. In this combustor, a pilot burner is arranged at the top portion for injecting a mixture of fuel and air only in a direction confronting the reverse flow region.

Abstract: A mixer for a gas turbine engine combustor includes: (a) a primary fuel injector with upstream and downstream ends, the primary fuel injector including: (1) a hollow central portion configured to pass a first air stream; (2) an annular fuel passage at the downstream end, configured to discharge an annular first fuel stream surrounding the first air stream; (b) an annular splitter surrounding the primary fuel injector, configured to pass a second air stream surrounding the first fuel stream; (c) an annular first housing surrounding the splitter, and having an exit positioned axially downstream of the primary fuel injector and the splitter; and (d) fuel injection ports disposed in an array outside the first housing, and disposed in communication with a fuel supply and positioned to discharge a second fuel stream into a third air stream at a position axially upstream of the exit of the first housing.

Abstract: An apparatus for internally mounting a fuel manifold within a surrounding casing in a gas turbine engine which includes a fuel manifold and support pins which are displaceable relative to mounting portions on the fuel manifold between a retracted position, wherein the fuel manifold is able to be inserted within a casing of the engine, and an extended position, wherein the support pins project outwardly from the fuel manifold for engagement with the casing.

Abstract: A mounting system supporting and positioning an internal fuel manifold of a gas turbine engine includes at least a heat shield surrounding a fuel inlet of the fuel manifold, the heat shield bearing at least a portion of a load to support the fuel manifold.

Abstract: There is provided an injector assembly having two or more oxidizer manifolds and/or two or more fuel manifolds for delivery of liquid propellants to a combustion chamber such that combustion instability is reduced or eliminated during throttling. Delivery of the oxidizer to the oxidizer manifolds is controlled by an oxidizer valve, which may comprise an integral valve. The oxidizer passes from the oxidizer manifolds into the oxidizer element and then into the combustion chamber. The multiple oxidizer manifolds allow the oxidizer to be provided through selective openings of the oxidizer element thus reducing the change in pressure drop across the oxidizer element to thereby reduce or eliminate combustion instability and other problems. Additionally, the injector assembly may also include a lift-off seal or a filler fluid source to fill any temporarily unused oxidizer manifolds with an oxidizer or filler fluid.

Abstract: A burner assembly is provided. The burner assembly includes a support housing with a supply manifold, the supply manifold includes a fuel passage system, and fuel nozzles extending from the supply manifold and being supplied with fuel through the fuel passage system of the supply manifold. The supply manifold is sandwiched using at least two subparts.

Abstract: A combustion system for an engine, such as a gas turbine engine is provided. The combustion system has a ceramic component, such as ceramic combustor liner, and at least one metal support component, such as a metal ring or a plurality of metal cones, for providing radial and axial support to the ceramic component. The at least one metal support component includes a structure, such as axial slots or radial slots, for minimizing stress and for increasing compliance of the metal support component with respect to the ceramic component.

Abstract: A burner with a burner head is provided. The burner includes a mixing tube for premixing combustion air and fuel. The mixing tube is provided with a pilot burner system in its downstream part. The pilot burner system includes an annular mixing cavity with an entrance for assist air and pilot fuel and outlet nozzles. The mixing cavity is provided with at least two swirler wings arranged in the vicinity of each outlet nozzle.

Abstract: A fuel injector for a secondary fuel nozzle in a gas turbine includes axially oriented air slots and a plurality of fuel injection holes disposed between the air slots. The plurality of fuel injection holes include axially oriented injection holes and radially oriented injection holes such that fuel input through the plurality of fuel injection holes is injected in both a radial direction and an axial direction to mix with air flowing through the air slots.

Abstract: A method of operating a power generation system is provided. The system includes a first gas turbine engine that uses at least one of a primary fuel and a secondary fuel, and at least one second gas turbine engine that operates using at least one of a primary and secondary fuel. The method includes supplying primary fuel to at least one of the first and second engines from a common fuel source coupled to the first and second engines, and selectively operating the first engine between a first operational position and a second operational position. The first engine using only secondary fuel in the first operational position and operates using only primary fuel in the second operational position. The method includes supplying the second engine with primary fuel from the common fuel source without flaring the primary fuel.

Abstract: A gas turbine engine fuel conveying member in fluid flow communication with at least one fuel nozzle, the fuel conveying member having at least first and second member portions sealingly engaged to one another, and means for conveying fuel defined at a junction between the first and second member portions. The means for conveying fuel is defined by at least part of two different walls of each of the first and second member portions.

Abstract: An inlet tube within a gas turbine engine which includes a primary fuel channel and a secondary fuel channel formed in a cylindrical tube body. The secondary channel has a substantially crescent shaped cross-sectional area which is complementary in shape to the primary fuel channel, such as to maximize the combined fuel flow area through the primary and secondary fuel channels relative to an outer diameter of the cylindrical tube body.

Abstract: A fuel distribution manifold system for a gas turbine engine is disclosed that includes a plurality of interconnected manifold segments, each manifold segment extending between a pair of fittings, each manifold segment including at least one fuel transfer tube and a sealing tube that surrounds the at least one fuel transfer tube, wherein opposed end portions of the at least one fuel transfer tube are dynamically connected to the fittings and opposed end portions of the sealing tube are statically connected to the fittings.

Abstract: A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at least a first discrete conduit and a second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets.

Abstract: A system for mounting an internal fuel manifold within a gas generator case of a gas turbine engine includes at least one fastener support assembly having a fastener pin and at least one receiving element, respectively engaged to either the internal fuel manifold or the gas generator case. A biasing member is located between the fastener pin and the receiving element to axially preload the joint between the fastener pin and the receiving element, such as to constrain relative movement between the two parts in an axial direction while allowing relative movement in a radial direction.

Abstract: The present invention relates to an annular combustion chamber of a gas turbine engine comprising a casing with at least one air tapping outlet situated at the chamber inlet, a fuel supply device with a plurality of fuel injectors in the chamber distributed annularly of which at least one is situated close to said tapping outlet. The chamber is characterized in that the fuel supply device comprises a means for reducing the fuel flow rate in said injector situated close to the tapping outlet relative to the other fuel injectors. Thanks to the invention, the hot spots downstream of the combustion chamber caused by the tappings are reduced.

Abstract: A method for controlling a temperature distribution within a combustor having a plurality of chamber sections comprising controlling a fuel-to-air ratio in the chamber sections. At least two chamber sections have different fuel-to-air ratios to create a non-uniform temperature distribution within the combustor to reduce thermoacoustic instabilities.

Abstract: A fuel manifold for a gas turbine engine comprises manifold adaptors each supporting a nozzle for outputting fuel from a fuel supply. The manifold adaptors have a primary conduit and a secondary conduit extending between connection ends of the manifold adaptor. The primary conduit and the secondary conduit are in fluid communication with the nozzle to supply fuel thereto. Transfer units are between adjacent manifold adaptors, and each comprises a primary transfer tube matingly connected at opposite ends to the primary conduits of the adjacent manifold adaptors for fuel circulation between the primary conduits. A secondary transfer tube in each transfer unit is matingly connected at opposite ends to the secondary conduits of the adjacent manifold adaptors for fuel circulation between the secondary conduits. A drain sleeve in each transfer unit is connected at opposite ends to the adjacent manifold adaptors.

Abstract: A fuel injection system comprises a fuel conveying member and a nozzle tip assembly threadably engaged thereto. A pair of sealing elements is engaged in a fuel passage between the fuel conveying member and the nozzle tip for sealing the junction therebetween. The pair of sealing elements includes a first and a second sealing element located proximate each other and having different cross-sectional shape.

Abstract: A turbine engine includes an annular combustor having a combustion chamber defined between an annular outer wall and an annular inner wall. A diffuser case substantially encloses the annular outer and inner walls. A fuel nozzle extends through the diffuser case to an outlet that provides fuel to an interior chamber of the combustor. In one embodiment, front portions of the inner and outer walls curve toward one another and overlap to form an annular gap or manifold through which fuel is distributed to the combustion chamber.

Abstract: An annular fluid distribution device (20) for distributing fluid into a gaseous flow (14), that includes: a first fluid distribution manifold (30) having a first fluid inlet and first fluid outlets (24), wherein the first fluid outlets inject a first fluid into the gaseous flow; and a second fluid distribution manifold (32), having a second fluid inlet and second fluid outlets (26), wherein the second fluid outlets inject a second fluid into the gaseous flow. The second fluid manifold is isolated from the first fluid distribution manifold, and the first fluid outlets and the second fluid outlets are disposed on a common fluid outlet plane (43).

Abstract: A fuel manifold of a gas turbine engine includes a tube assembly having substantially rigid inner tubes disposed inside of substantially rigid outer tubes in pairs, concentrically spaced apart by a spacer apparatus. The inner tubes form a primary fuel passage for directing a primary fuel flow and the outer tubes form a secondary fuel passage for directing a secondary fuel flow, the secondary flow being greater than the primary flow.

Abstract: A fuel conveying member for a gas turbine engine, the fuel conveying member including a fuel manifold having a plurality of fuel nozzles extending therefrom. The fuel manifold is mounted within the engine by a support system, including integral attachment lugs on the fuel manifold for mounting the fuel manifold within the gas turbine engine. The attachment lugs re adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.

Abstract: A fluid manifold apparatus includes: (a) an array of spaced-apart manifold fittings, each manifold fitting aligned in a predetermined angular orientation. Each manifold fitting includes: (i) a tubular neck; (ii) a pair of spaced-apart tubular arms extending away from a first end of the neck; and (iii) a coupling connected to a second end of the neck; and (b) a plurality of curved tubes, each tube being coupled to one arm of each of two adjacent manifold fittings.

Abstract: A gas turbine combustion system for a turbine engine is disclosed. The gas turbine combustion system may include a plurality of combustor baskets positioned circumferentially about a longitudinal axis of the turbine engine, at least one firing nozzle extending into each of the plurality of combustor baskets and a fuel delivery system in communication with each of the at least one firing nozzles and in communication with at least one fuel source. Each combustor basket may include a fuel flow control device of the fuel delivery system inline with each of the at least one firing nozzles in that combustor basket such that fuel flow to some of the combustor baskets can be shut off while fuel flow to firing nozzles in other combustor baskets remains unobstructed, thereby permitting some combustor baskets to remain non-fired while other combustor baskets are firing to reduce CO emissions.

Abstract: A gas turbine engine fuel nozzle system having a fuel conveying member with a channel formed in a surface thereof defined between a pair of facing spaced apart walls, and at least one sealing member disposed within the channel and sealingly fastened to the spaced apart walls.

Abstract: A fuel conveying member for an engine, the fuel conveying member having heating means integrated therein to permit pyrolysis of carbonaceous deposits.

Abstract: A fuel injection system for a gas turbine engine having a manifold ring, a plurality of spray tip assemblies and a heat shield including at least two heat shield segments cooperating to at least substantially surround a cross-section of the manifold ring around a circumference of the manifold ring, and detachably retained around the manifold ring through a plurality of removable fasteners.

Abstract: In exemplary embodiments, a gas turbine system is provided. The gas turbine system can include a compressor configured to compress air and combustor cans in flow communication with the compressor, the combustor cans being configured to receive compressed air from the compressor and to combust a fuel stream. The gas turbine system can also include a multi-circuit manifold coupled to the combustor cans and configured to provide a split fuel stream from the fuel stream to the combustor cans.

Abstract: A mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener engaging the receiving element to constrain a relative movement between the fuel manifold and the gas generator case in an axial direction while allowing the relative movement in a radial direction and a secondary fastener in position to passively and automatically engage the receiving element upon failure of the primary fastener.

Abstract: A fuel conveying member of a gas turbine engine fuel system conducting pressurized fluid flow is provided. The fuel conveying member comprises a body defining an L-shaped fuel flow passage therein, the L-shaped passage including an elbow. The elbow portion provides a substantially smooth fluid-dynamic transition between portions of the passage upstream and downstream thereof.

Abstract: A power generation system. The exemplary system shown in FIGS. 1 and 2 includes a gas turbine (28), a gasifier (10) for generating gaseous fuel and a gas combustor (26) configured to receive the fuel and power the gas turbine (28). A drain collection and separation system (5) is positioned to collect gaseous fuel entrained in liquid and to separate the gaseous fuel from the liquid so the gaseous fuel can be cycled or disposed of separately from the liquid.

Abstract: A method for assembling a fuel nozzle for a turbine engine is provided. The method includes coupling a one-piece housing to a one-piece venturi wherein the housing defines an annular fuel nozzle tip and the venturi defines a fuel chamber within the fuel nozzle tip. The method further includes coupling a one-piece swirler to the venturi such that the swirler extends radially inward from the venturi.

Abstract: A heat shield for a fuel member of a gas turbine engine having at least one heat shield segment having a connection edge with at least one joint receiving portion defined therealong for receiving a welded joint attaching the heat shield segment to a fuel member, each joint receiving portion including a stress relieving feature defined along at least one end thereof.

Abstract: An object is to provide a low cost gas turbine combustor. The gas turbine combustor has a plurality of main nozzles annularly supported on a nozzle pipe base (11), and the main nozzles each have an oil fuel path for supplying oil fuel and a gas fuel path for supplying gas fuel. A plurality of the oil fuel paths are provided to penetrate the nozzle pipe base (11), and a plurality of lengths of upright piping (21) are provided to be connected to the oil fuel paths, respectively, and be erected on the nozzle pipe base (11). A plurality of lengths of connection piping (22) for interconnecting the lengths of the upright piping (21) in a polygonal shape at a minimum distance are provided outside the nozzle pipe base (11). An oil fuel supply section (14) is connected to one of the lengths of the connection piping (22) to distribute oil fuel to each of the oil fuel paths.

Abstract: A fuel manifold assembly for a gas turbine engine includes an annular fuel manifold having at least one fuel conveying passage and defining at least one slow fuel flowing location. A heat shield at least partly encloses the fuel manifold and a plurality of intermittent joints attach the heat shield to the fuel manifold. The joints are circumferentially distributed about the fuel manifold as far away from the slow flowing location as possible while maintaining the fuel manifold dynamically balanced.

Abstract: A mixer assembly for use in a combustion chamber of a gas turbine engine includes a pilot mixer, a main mixer, and a fuel manifold. The pilot mixer includes: an annular pilot housing having a hollow interior, a primary fuel injector mounted in the pilot housing, a plurality of axial swirlers positioned upstream from the primary fuel injector, and a plurality of secondary fuel injection ports for introducing fuel into the hollow interior of the pilot housing. The main mixer includes: a main housing surrounding the pilot housing and defining an annular cavity, a plurality of fuel injection ports, and at least one swirler positioned upstream from the plurality of fuel injection ports. The fuel manifold is in flow communication with the plurality of secondary fuel injection ports in the pilot mixer and the plurality of fuel injection ports in the main mixer.