| Entries |
| Document | Title | Date |
|---|
| 20080229750 | Location ring arrangement - Location rings | 09-25-2008 |
| 20080289338 | High Efficiency 2-Stage Fuel Pump and Control Scheme for Gas Turbines - A two-stage system for delivering fuel to a gas turbine including a first stage variable pump for serving as a primary source of fuel, a second stage fixed pump for selectively supplementing the variable pump, a bypass valve connected to the fixed pump for loading and unloading the fixed pump and a regulator valve assembly connected to the variable pump and the bypass valve for controlling operation of the variable pump and the bypass valve. Preferably, the two-stage system also includes a control valve connected to the regulator valve assembly for setting a pressure differential across the regulator valve assembly and, thereby, loading and unloading the fixed pump. | 11-27-2008 |
| 20080289339 | METHOD AND APPARATUS FOR CONTROLLING THE COMBUSTION IN A GAS TURBINE - A method and apparatus are described for controlling the combustion in a gas turbine. The method includes measuring, by means of one or two calorimeters, the temperature, calorific value and relative density of a gaseous fuel in order to determine the Wobbe index, comparing the Wobbe index value measured with a predefined Wobbe index value for the gaseous fuel and regulating the temperature of the gaseous fuel by means of at least one heat exchanger in order to reach the predefined Wobbe index value. The method may also include using a second gaseous fuel, having a different Wobbe index from the gaseous fuel, or a fuel obtained by mixing the gaseous fuel and the second gaseous fuel, according to arbitrary proportions and variable with time. | 11-27-2008 |
| 20090049838 | TURBINE FUEL DELIVERY APPARATUS AND SYSTEM - A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages. | 02-26-2009 |
| 20090049839 | JET AIRCRAFT ENGINE WITH IONIZED THROUGHFLOW - A jet aircraft engine is ionized to improve its power and efficiency. Various engine components may be electrostatically charged to form positive and negative ions causing the air and the fuel-air mixture to electrostatically accelerate from the engine intake to the exhaust. | 02-26-2009 |
| 20090126367 | SEQUENTIAL COMBUSTION FIRING SYSTEM FOR A FUEL SYSTEM OF A GAS TURBINE ENGINE - 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. | 05-21-2009 |
| 20090133401 | COMBUSTOR FOR TURBINE ENGINE - 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. | 05-28-2009 |
| 20090145131 | FUEL DISTRIBUTION SYSTEM FOR A GAS TURBINE WITH MULTISTAGE BURNER ARRANGEMENT - A fuel distribution system for a gas turbine with multistage burner arrangement is provided having at least one distribution line that branches off from a common fuel feed line and leads to a burner stage, and at least one element is provided in each distribution line for the specific influencing of the fuel mass flow. In such a fuel distribution system simplified controlling is made possible by a control valve being arranged in each case in one section of the distribution lines as an element for the specific influencing of the fuel mass flow, and in that a restrictor, which is preset in a fixed manner, is arranged in each case in the remaining distribution lines as an element for the specific influencing of the fuel mass flow. | 06-11-2009 |
| 20090199561 | Fuel nozzle for a gas turbine engine and method for fabricating the same - A method for fabricating a secondary fuel nozzle assembly includes providing a nozzle portion defining a passageway configured to supply fuel. At least one peg is operatively coupled in fuel flow communication with the passageway. The at least one peg extends radially outward from the nozzle portion and defines at least one opening configured to direct a flow of fuel in a substantially upstream direction. A disc is positioned about the nozzle portion upstream of the at least one peg. The disc is positioned in communication with the at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization. | 08-13-2009 |
| 20090235665 | POSITION SENSORS, METERING VALVE ASSEMBLIES, AND FUEL DELIVERY AND CONTROL SYSTEMS - Position sensors, metering valve assemblies, and fuel delivery and control systems are provided. In an embodiment, by way of example only, a position sensor includes a rotor, a primary winding wound around the rotor, a stator surrounding at least a portion of the rotor and the primary winding, and a secondary winding disposed adjacent to the stator. At least one of the primary winding and the secondary winding comprises copper and nickel. | 09-24-2009 |
| 20090255256 | METHOD OF MANUFACTURING COMBUSTOR COMPONENTS - A method for fabricating a unitary component for a combustor is disclosed, said method comprising the steps of determining three-dimensional information of the unitary component, converting the three-dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary component, and successively forming each layer of the unitary component by fusing a metallic powder using laser energy. A fuel nozzle component is disclosed, comprising a body having a unitary construction wherein the body is made by using a rapid manufacturing process. | 10-15-2009 |
| 20090255257 | FUEL DISTRIBUTOR - A unitary distributor is disclosed, comprising at least one main flow passage located within a distributor ring body, the main flow passage having an arcuate portion oriented in a circumferential direction around a distributor axis. Exemplary embodiments of a unitary distributor having an annular ring located at the axially forward end of the distributor ring body are disclosed. A fuel distributor is disclosed, comprising a fuel conduit and a distributor wherein the fuel distributor has a unitary construction. | 10-15-2009 |
| 20090266078 | Fuel flow anti-interruption - An anti-flow interruption system is configured to provide a supply of fuel in the event of a fuel flow interruption from a fuel tank. The anti-flow interruption system includes a reservoir, a reservoir conduit, and a vapor bleed system. The reservoir conduit has an end disposed at the bottom of the reservoir and another connected to a fuel pump. The vapor bleed system includes a vapor bleed conduit and a vapor bleed restrictor. One end of the vapor bleed conduit is attached to the top of the reservoir and the other end is connected to the fuel pump. The vapor bleed restrictor is disposed in the vapor bleed conduit between the fuel pump and the reservoir. If fuel flow is interrupted and results in vapor being present in the reservoir, liquid fuel remaining in the reservoir continues to be supplied to the fuel pump while the vapor bleed system removes the vapor. | 10-29-2009 |
| 20090301091 | COMPRESSOR-LESS MICRO GAS TURBINE POWER GENERATING SYSTEM - A compressor-less micro gas turbine has a compressed working medium container for maintaining a gas turbine under pressure. A combustion chamber is in fluid communication with the compressed gas container for receiving a gas from the gas container and heating the gas within the combustion chamber to create an expanded gas. A heater heats the combustion chamber to expand the working gas therein. A turbine in fluid communication with the combustion chamber for receiving the expanded gas. The expanded gas drives the turbine. A generator is operatively coupled to the turbine. The turbine provides a mechanical input to the generator causing the generator to produce electricity. | 12-10-2009 |
| 20090320480 | Fuel control arrangement - Fuel control arrangements provide and control fuel flow to injectors through fuel control valves. The injectors are connected to respective fuel control valves which in turn are connected to a first fuel flow path. The injectors are also connected to a second fuel flow path. The fuel paths are associated with a fuel source and generally have a recirculation valve between them. When flow in the flow path is stopped, recirculation of fuel can be provided across the recirculation valve to prevent fuel degradation. By provision of a restrictor valve in the second fuel flow path control of fuel recirculation can be achieved, as well as greater flexibility by presenting fuel flow separately through the second flow path to the injector whilst the first flow path is inhibited. | 12-31-2009 |
| 20100024425 | TURBINE ENGINE FUEL NOZZLE - A fuel nozzle for a gas turbine combustor that includes an extended flange. At a first end, the extended flange may be configured to engage an end cover, thereby securing the position of the fuel nozzle within the combustor. At a second end, the extended flange may be configured to engage a swozzle, within which a supply of fuel and compressed air is mixed during the operation of the combustor. The extended flange may be formed as a single piece. | 02-04-2010 |
| 20100031658 | GAS TURBINE FUEL METERING UNIT - 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. | 02-11-2010 |
| 20100031659 | Method and Device for Monitoring the Formation of Deposits of Solid Particles, Particularly in a Fuel Line and in the Fuel Valves of a Gas Turbine - A process is disclosed for monitoring the formation of deposits of solid particles in a fuel line having a valve. A measure for the deposits of solid particles in the fuel line is determined by determining the degree of opening of the valve passage and the quantity of fuel flowing through the valve, and by comparing them with a previously determined control value which characterizes the deposit-free line. Also disclosed is a device for monitoring the formation of deposits of solid particles in a fuel line having a valve, the device having a measurement system for determining the current fuel flow and a measurement system for determining the current valve position, as well as an evaluation system connected to the measurement systems. Also disclosed is a combustion chamber comprising a device and operated by a process according to the invention, and a gas turbine with said combustion chamber. | 02-11-2010 |
| 20100031660 | SYSTEM AND ASSEMBLIES FOR PRE-HEATING FUEL IN A COMBINED CYCLE POWER PLANT - A system and assemblies for pre-heating fuel in a combined cycle power plant are provided. A fuel supply system includes a water heater assembly configured to heat a flow of water using progressively higher grade heat from a multi-stage heat exchanger arrangement. The fuel supply system also includes a fuel heater that includes a first flow path coupled in flow communication with a fuel flow path wherein the fuel heater includes a second flow path coupled in flow communication with a flow path for the flow of water. The fuel heater is configured to transfer heat from the flow of water to the flow of fuel. | 02-11-2010 |
| 20100037612 | FUEL DIVIDER SYSTEM FOR GAS TURBINE ENGINE - A fuel divider system includes a housing assembly and a flow passage network having an inlet, a primary outlet, and a secondary outlet. A fuel divider piston is slidably disposed within the housing assembly and movable between a flow biasing position and a flow equalizing position. A control chamber is fluidly coupled to the flow passage network and fluidly communicates with the piston. An inlet chamber, at least partially defined by the piston and the housing assembly, is fluidly coupled to the inlet. At least one channel is provided through the piston and configured to cooperate with the flow passage network to port the FD control chamber to: (i) the fuel pressure at the secondary outlet when the FD piston is in the flow biasing position, and (ii) the fuel pressure within the inlet chamber when the FD piston is in the flow equalizing position. | 02-18-2010 |
| 20100037613 | FUEL INJECTOR AND METHOD OF ASSEMBLING THE SAME - A fuel injector is provided. The fuel injector includes a nozzle, a cooling assembly, and a tip coupled to the nozzle. The tip includes a base including a cooling channel defined therein, a first transition member extending outwardly from the base and in flow communication with the cooling channel, and a second transition member extending outwardly from the base and in flow communication with the cooling channel, wherein the base, the first transition member, and the second transition member are formed integrally together. The tip is configured to couple to the cooling assembly to channel a flow of cooling fluid through the cooling channel via the first transition member and the second transition member. | 02-18-2010 |
| 20100050640 | THERMALLY COMPLIANT COMBUSTION CAP DEVICE AND SYSTEM - A combustion cap plate is disclosed. The combustion cap plate includes: a plate having a planar surface and configured to be affixed to an assembly connected to a turbine combustion chamber, the plate defining a central axis perpendicular to the planar surface; a plurality of openings through the plate; and a plurality of raised portions formed by the plate. The raised portions each extend away from the planar surface in a direction of the central axis and having a shape conforming to a thermal gradient incident on the plate during a combustion process. | 03-04-2010 |
| 20100064690 | FUEL NOZZLE TIP ASSEMBLY - A system, in one embodiment, includes a fuel nozzle tip retainer that includes a structural member having a geometry that blocks a tip insert from moving axially downstream of a fuel nozzle. | 03-18-2010 |
| 20100071373 | Pilot Burner for Gas Turbine Engine - A pilot burner ( | 03-25-2010 |
| 20100071374 | Spiral Cooled Fuel Nozzle - A fuel nozzle for delivery of fuel to a gas turbine engine. The fuel nozzle includes an outer nozzle wall and a center body located centrally within the nozzle wall. A gap is defined between an inner wall surface of the nozzle wall and an outer body surface of the center body for providing fuel flow in a longitudinal direction from an inlet end to an outlet end of the fuel nozzle. A turbulating feature is defined on at least one of the central body and the inner wall for causing at least a portion of the fuel flow in the gap to flow transverse to the longitudinal direction. The gap is effective to provide a substantially uniform temperature distribution along the nozzle wall in the circumferential direction. | 03-25-2010 |
| 20100077756 | FUEL LANCE FOR A GAS TURBINE ENGINE - A fuel lance ( | 04-01-2010 |
| 20100107639 | FUEL NOZZLE ASSEMBLY FOR USE WITH A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING SAME - A fuel nozzle configured to channel fluid toward a combustion chamber within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a first hollow tube fabricated from a first material that has a first coefficient of thermal expansion and a second tube fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, and the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation. | 05-06-2010 |
| 20100107640 | Air cooling apparatus for a purge valve - A cooling enclosure for a valve includes an elongated housing body having a pair of housing portions and a pair of removable end plates, the pair of housing portions separable along at least one longitudinally-extending seam. Fastener devices are provided for securing the pair of housing portions engaged along the at least one longitudinal extending seam. One or more apertures are provided for accommodating a like number of valve fittings, and cooling air inlet and outlet openings are also provided in the housing body for supplying and removing cooling air to the housing body. | 05-06-2010 |
| 20100115952 | GUM SUBSTANCE MONITORING APPARATUS, GUM SUBSTANCE DETECTING METHOD, AND GAS TURBINE SYSTEM - A gum substance monitoring apparatus ( | 05-13-2010 |
| 20100122535 | FUEL CONTROL SYSTEM FOR GAS TURBINE AND FEED FORWARD CONTROL METHOD - A fuel controller for a combustion system in a gas turbine having a combustion system, a fuel supply, a pressure control valve proximate the combustion system and a first pressure sensor proximate the pressure control valve, the fuel controller including: a proportional-integrated (PI) logic unit generating a control command for the pressure control valve and receiving input signals representing a desired fuel pressure at the pressure control valve and an input signal from the first pressure sensor representing an actual fuel pressure at the pressure control valve, and a plurality of control gains stored in electronic memory of the controller, wherein each control gain is applicable to a predefined operating condition of the gas turbine, and wherein the controller determines which set of control gains is to be applied by the PI logic unit based on an actual operating condition of the gas turbine. | 05-20-2010 |
| 20100139279 | FUEL DELIVERY SYSTEM AND METHOD OF ASSEMBLING THE SAME - A method of assembling a fuel delivery system is provided. The method includes providing a base that includes a surface, a receptacle extending into the base from the surface along a longitudinal axis, and a plurality of channels extending into the base from the receptacle. Each of the plurality of channels includes an inlet end and an outlet end, and each of the plurality of channels intersects the receptacle at the outlet end, wherein the receptacle and the plurality of channels are formed integrally within the base such that the plurality of outlet ends are spaced axially from one another. The method further includes securing a fuel nozzle within the receptacle, the fuel nozzle including a plurality of separate flow paths, wherein each of the plurality of channels is in flow communication with one of the plurality of separate flow paths. | 06-10-2010 |
| 20100162708 | METHODS, APPARATUS AND/OR SYSTEMS RELATING TO FUEL DELIVERY SYSTEMS FOR INDUSTRIAL MACHINERY - An assembly for delivering a supply of liquid fuel and a supply of purge air to a gas turbine engine, the assembly comprising: an annular dual-flow check valve for controlling the flow through concentric channels that have a common outlet, the annular dual-flow check valve comprising: an outer body and an inner body that define the concentric channels, which include an outer channel and an inner channel formed therein; a spring activated annular poppet that resides in the outer channel and has a range of motion in the axial direction; and an opening through the inner body that connects the outer channel to the inner channel; wherein the axial movement of the annular poppet is regulated by the pressure of the flow upstream of the annular poppet in the outer channel; and the axial range of motion of the annular poppet includes at least two axial positions. | 07-01-2010 |
| 20100162709 | FUEL SUPPLY SYSTEM - A fuel supply system has valve communicating fuel to fuel nozzles. A fuel manifold supplies fuel to the valve. The valves are controlled by rotary drives extending from an actuator. At least part of the drive lies within the fuel manifold which serves to keep the drive cool and reduce significantly the number of seals required. | 07-01-2010 |
| 20100170249 | METHOD AND APPARATUS TO FACILITATE COOLING OF A DIFFUSION TIP WITHIN A GAS TURBINE ENGINE - A method and apparatus for a diffusion tip for use with a fuel nozzle is described. The diffusion tip has a substantially circular body including an outer surface and an opposite inner surface. The diffusion tip body extends from a discharge end to an inlet end. The diffusion tip includes an inlet surface adjacent to the discharge end and defined within the body. A discharge surface is defined opposite the inlet surface. A plurality of diffusion apertures each extend between the discharge surface and the inlet surface, each aperture is oriented relative to the body to discharge a diffusion flow outward therefrom at an angle γ (gamma) measured in an X-Z plane between a centerline of the aperture and an X-axis extending tangentially to the outer surface, and at an angle θ (theta) measured in a Y-Z plane between the centerline of the aperture and a Y-axis extending radially outward from the centerline. | 07-08-2010 |
| 20100175380 | 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. | 07-15-2010 |
| 20100180598 | Burner and method for operating a burner - A method for operating a burner including a burner outlet opening with at least two sectors, each sector is assigned at least one fuel nozzle, is provided. The method is characterized in that fuel is supplied separately to the fuel nozzles of different sectors. Also described is a burner which includes at least two sectors wherein each sector is assigned at least one fuel nozzle. The burner includes at least two separate fuel supply lines and a device for adjusting the fuel mass flow which flows through the respective fuel supply line. The fuel supply lines supply fuel to the fuel nozzles of different sectors. Also described is a gas turbine which is fitted with at least one burner. | 07-22-2010 |
| 20100205970 | Systems, Methods, and Apparatus Providing a Secondary Fuel Nozzle Assembly - Provided are systems, methods, and apparatus providing secondary fuel nozzle assemblies. For example, a secondary fuel nozzle assembly can include a central portion having a proximal end and distal end, and defining a central passage therethrough, which can include at least one coiled tube extending through the central passage from the proximal end to the distal end; a flange having at least one main secondary fuel orifice in fluid communication with the central passage at the proximal end and at least one pilot orifice in fluid communication with the at least one coiled tube at the proximal end; and a tip portion having a proximal end and distal end, and defining at least one passage therethrough, which can be in fluid communication with the distal end of the at least one coiled tube and at least one orifice formed in the distal end of the tip portion. | 08-19-2010 |
| 20100229555 | Fuel manifold with reduced losses - 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. | 09-16-2010 |
| 20100229556 | TURBINE FUEL NOZZLE HAVING HEAT CONTROL - In one embodiment, a system includes a turbine engine fuel nozzle having an air path, a fuel path, and a surface along the air path. The fuel path may be directed toward the surface. The turbine engine fuel nozzle also may include a heating element configured to heat the surface. | 09-16-2010 |
| 20100269504 | Coating system and method for reducing coking and fuel system fouling - A fuel system for delivering fuel to an engine includes a fuel tank, a hot section in fluid communication with the fuel tank for delivering fuel for combustion by the engine, and a coating applied to at least a portion of the hot section for reducing fuel coking. The coating includes a fluorine functional group and a silane functional group. | 10-28-2010 |
| 20100269505 | SYSTEM AND METHOD FOR CONTROLLING COMBUSTION DYNAMICS - A tunable fluid flow control system for controlling combustion dynamics in a combustor is disclosed. The control system includes a fuel supply path having an inlet portion, a first diverted portion, a second diverted portion, and an exit portion. A first diverted portion has a first length and a first diameter. A second diverted portion has a second length and a second diameter and spaced apart from the first diverted portion. The first and second diverted portions converge at a merging location. The exit portion is coupled to the merging location of the first and second diverted portions. At least one flow regulation device is coupled to the inlet portion and configured to divert fuel flow to the first and second diverted portions alternately to generate fuel flow perturbations at the merging location. | 10-28-2010 |
| 20100281869 | Airblown Syngas Fuel Nozzle With Diluent Openings - A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone. | 11-11-2010 |
| 20100326077 | SYSTEM FOR MITIGATING A FUEL SYSTEM TRANSIENT - The present invention takes the form of a system that may reduce the effect of a transient of a fuel system. Essentially, an embodiment of the present invention incorporates a pressure control cell (PCC) with the fuel system. The PCC may be considered an additional volume that removes some of the fuel remaining in the fuel system during a transient event. During a transient event, when a rapid reduction of fuel is required for a fuel circuit, fuel may be allowed to exit a manifold of the fuel system and enter the PCC. This fuel may now be stored within the PCC and may no longer be available to the combustion can. A benefit of the present invention may be a reduced possibility of an undesired increase in rotor speed, and a lean blowout event. | 12-30-2010 |
| 20110000214 | METHODS AND SYSTEMS TO THERMALLY PROTECT FUEL NOZZLES IN COMBUSTION SYSTEMS - A method of assembling a gas turbine engine is provided. The method includes coupling a combustor in flow communication with a compressor such that the combustor receives at least some of the air discharged by the compressor. A fuel nozzle assembly is coupled to the combustor and includes at least one fuel nozzle that includes a plurality of interior surfaces, wherein a thermal barrier coating is applied across at least one of the plurality of interior surfaces to facilitate shielding the interior surfaces from combustion gases. | 01-06-2011 |
| 20110056204 | Self-Contained Oil Feed Heat Shield for a Gas Turbine Engine - A gas turbine engine fuel heat shield configured to shield fuel from high temperatures of surrounding turbine components to prevent coking of the fuel is disclosed. The gas turbine engine fuel heat shield may be formed from a generally elongated member having a first collar at a first end and a second collar at a second end opposite to the first end. One or more recesses may be positioned in an outer surface of the generally elongated member between the first and second collars. A sleeve is positioned around the generally elongated member and radially outward of the recess to form one or more sealed chambers. The sleeve may be sealed to prevent fuel from entering the recess and coking. Such design, therefore, prevents the formation of carbon particles from the fuel that could clog the fuel injectors. | 03-10-2011 |
| 20110072822 | HOSE ARRANGEMENT FOR A GAS TURBINE ENGINE - An example gas turbine engine hose arrangement includes a hose configured to communicate fluid and a thermal blanket directly adjacent the hose. A section of the hose is radially closer to a centerline of the gas turbine engine than the thermal blanket. An example method of limiting hose exposure to thermal energy includes routing a hose near a combustor housing of a gas turbine engine and covering the hose with thermal blanket to limit thermal energy communicated radially inwardly toward an axial center of the combustor housing. | 03-31-2011 |
| 20110088400 | GAS FUEL SUPPLY APPARATUS - A gas fuel supply apparatus is constructed to be capable of supplying any one of propane gas and butane gas to a gas engine while switching between the propane gas and the butane gas. A check valve is provided in a gas fuel supply passages corresponding to a gas canister containing the gas fuel of a low working pressure (propane gas). The check valve prevents the gas fuel of a higher working pressure (butane gas) from flowing from a downstream side of the check valve to an upstream side of the check valve. | 04-21-2011 |
| 20110094232 | APPARATUS FOR CONDITIONING AIRFLOW THROUGH A NOZZLE - A nozzle includes a center body and a shroud surrounding the center body to define an annular passage. An arcuate annular guide extending from a point radially inward of the shroud to a point radially outward of the shroud defines a first airflow between the arcuate annular guide and the shroud and a second airflow between the arcuate annular guide and the center body. | 04-28-2011 |
| 20110162370 | FUEL SYSTEM ACOUSTIC FEATURE TO MITIGATE COMBUSTION DYNAMICS FOR MULTI-NOZZLE DRY LOW Nox COMBUSTION SYSTEM AND METHOD - A dry low NOx (DLN) fuel nozzle of a fuel system is provided and includes one or more downstream orifices formed to define a first fluid path along which fluid is directed to flow, an upstream orifice, located upstream from the one or more downstream orifices, formed to define a second fluid path along which the fluid is directed to flow and connecting passages disposed to fluidly couple the first and second fluid paths of the downstream and upstream orifices, respectively, to one another. At least one of a radial size and an axial location of the upstream orifice is set to cooperatively detune an acoustic impedance of the fuel system. | 07-07-2011 |
| 20110219773 | SYSTEMS AND METHODS FOR PRODUCING HYDROGEN FROM CELLULOSIC AND/OR GRAIN FEEDSTOCKS FOR USE AS A VEHICLE FUEL, USE IN THE PRODUCTION OF ANHYDROUS AMMONIA, AND TO GENERATE ELECTRICITY - Systems and methods for producing hydrogen from cellulosic and/or grain feedstocks for use as a vehicle fuel, use in the production of anhydrous ammonia, and to generate electricity. In at least one exemplary embodiment of a system for producing ammonia, the system comprises a fuel source containing fuel, a burn chamber coupled to the fuel source for burning the fuel to create energy, an electricity generator coupled to the burn chamber to generate electricity from the energy from the burn chamber, an electrolysis tank coupled to the electricity generator wherein electricity from the electricity generator facilitates the electrolysis of water present within the electrolysis tank to form hydrogen and oxygen, an ammonia reaction chamber coupled to the electrolysis tank, and a compressed air source coupled to the ammonia reaction chamber, wherein the hydrogen and nitrogen from the compressed air source react within the ammonia reaction chamber to generate ammonia. | 09-15-2011 |
| 20110271679 | Liquid Fuel System and Method - The present application provides a liquid fuel system for use with a flow of a liquid fuel and a combustor of a gas turbine engine. The liquid fuel system may include a number of fuel lines in communication with the combustor, a purge air inlet positioned about each of the fuel lines, a number of drain lines with each drain line in communication with a respective fuel line, and a number of drain valves with each drain valve in communication with a respective drain line so as to drain the flow of liquid fuel in the fuel lines via a flow of purge air through the purge air inlet and opening the drain valves. | 11-10-2011 |
| 20110277480 | SYSTEM AND METHOD FOR WASHING AND PURGING THE LIQUID FUEL SYSTEM OF A TURBINE WITH WATER - This system for supplying a turbine with liquid fuel comprises a liquid fuel inlet ( | 11-17-2011 |
| 20110289925 | FUEL PUMPING SYSTEM FOR A GAS TURBINE ENGINE - A fuel supply system for a gas turbine engine has a first pump for delivering fuel to a first use on a gas turbine engine, and a second pump for delivering fuel to a second use on the gas turbine engine. A valve allows flow from the first pump to be delivered to the first use, but also routes some flow from the first pump to supplement fuel flow from the second pump until a pressure downstream of the second pump increases. The valve then allows flow from the second pump to flow to the first use to supplement the flow from the first pump. | 12-01-2011 |
| 20110289926 | EXTRUDED FLUID MANIFOLD FOR GAS TURBOMACHINE COMBUSTOR CASING - A turbomachine includes a compressor, a turbine, and a combustor operatively coupled to the compressor and the turbine. The combustor includes a combustor casing having a flange, an outer surface and an inner surface that defines an internal passage. The combustor casing includes an extruded fluid manifold mounted to the outer surface. The extruded fluid manifold includes first and second walls integrally formed with a third, connecting, wall. The first wall includes a first mounting element and the second wall includes a second mounting element. The first mounting element extends axially along the combustor casing away from the first wall and the second mounting element extends axially along the combustor casing away from the second wall and the first mounting element. The extruded fluid manifold is joined to the outer surface of the combustor casing through the first and second mounting elements. | 12-01-2011 |
| 20110289927 | Method for Flushing a Section of a Fuel System of a Gas Turbine - A fuel system of a burner of a gas turbine and to a method for flushing a section of a fuel system of a burner of a gas turbine is provided. The method includes providing a feed line for feeding liquid fuel from a fuel source to the burner, providing a first and a second connection point to the feed line, providing a medium at the first connection point and generating a vacuum at the second connection point such that the fuel which is situated in the section between the two connection points is sucked out through the second connection point. | 12-01-2011 |
| 20120137691 | Gas turbine assembly and method therefor - An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange. | 06-07-2012 |
| 20120137692 | Combustion Apparatus - A gas turbine engine is provided. The gas turbine engine includes an air inlet, a combustor, an exhaust and first and second measurement devices. A plurality of fuel supply lines is provided to the at least one combustor. The first measurement device measures an amount of a gas in the air inlet. The second measurement device measures an amount of the gas in the exhaust. A control unit varies the fuel supply in the plurality of fuel supply lines so as to control the amount of the gas in the exhaust. The variation is made in dependence upon both the measured amount of the gas in the air inlet and the measured amount of the gas in the exhaust. | 06-07-2012 |
| 20120159953 | Fuel Staging System - A fuel staging system is described which comprises a staging valve | 06-28-2012 |
| 20120167569 | GAS TURBINE COMBUSTION BURNER - Provided is a gas turbine combustion burner capable of uniformly ejecting fuel from ejection holes for reduced NO | 07-05-2012 |
| 20120174587 | FUEL FLOWMETER HAVING AN IMPROVED REGULATOR DEVICE - A fuel flowmeter for being fed by a pump including an inlet and an outlet, including: a metering valve including an inlet and an outlet, and arranged downstream from the outlet of the pump; a return circuit connecting the inlet of the metering valve to the inlet of the pump; and a pressure regulator device including: a movable valve member to close and open the return circuit, a pressure difference detection surface fastened to the valve member and axially separating a first chamber in communication with the inlet of the metering valve from a second chamber in communication with the outlet from the metering valve, a piston axially separating the second chamber from a third chamber connected to the outlet of the metering valve, and a channel putting the second chamber in communication with the third chamber. | 07-12-2012 |
| 20120186255 | SYSTEM FOR PRE-MIXING IN A FUEL NOZZLE - A system includes a fuel nozzle. The fuel nozzle includes a hub having an axis, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple vanes extending between the hub and the shroud, and a first fuel path leading to multiple first fuel outlets disposed on the multiple vanes. The fuel nozzle also includes a second fuel path leading to multiple second fuel outlets disposed on at least one of the hub and/or the shroud, wherein the multiple second fuel outlets are disposed at an axial distance upstream from a downstream end of the hub. | 07-26-2012 |
| 20120210716 | Pumping Arrangement - An aircraft fuel pumping arrangement comprises a first fuel pump, an electrically powered motor operable to drive the first fuel pump to deliver fuel to an outlet, a second fuel pump, a gas driven turbine operable to drive the second fuel pump to deliver fuel to the outlet, and a controller operable to control the operation of the gas driven turbine to determine the rate at which the second fuel pump is driven. | 08-23-2012 |
| 20120260658 | FUEL FEED CIRCUIT FOR AN AEROENGINE - A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other. | 10-18-2012 |
| 20120266600 | FUEL FEED CIRCUIT FOR AN AEROENGINE - A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator. | 10-25-2012 |
| 20120312022 | COALESCING FILTER - A fuel system comprising a liquid fuel tank, an engine, and a coalescing filter adapted to separate water from fuel, the filter having an inlet fluidically connected to the fuel tank, a first outlet fluidically connected to a fuel feed system for the engine, and a second outlet fluidically connected to the fuel tank, wherein the coalescing filter is adapted to discharge fuel filtrate from the second outlet and filtrand from the first outlet. Also, a method of removing water or ice from a fuel tank, the method comprising directing a flow of fuel from a fuel tank to a coalescing filter adapted to separate water from fuel, discharging filtrand from a first outlet of the coalescing filter to a fuel feed system for consumption by an engine, and discharging fuel filtrate from a second outlet of the coalescing filter and returning the fuel filtrate to the fuel tank. | 12-13-2012 |
| 20120324895 | FUEL SUPPLY DEVICE OF GAS TURBINE ENGINE - A fuel supply device of a gas turbine engine is provided. The fuel supply device includes a fuel divider which divides fuel supplied from a collecting fuel passage to feed the fuel to a pilot fuel passage and to a main fuel passage. The fuel divider includes a movable member which is movable according to fuel pressure at the fuel entrance and opens and closes pilot ports and main ports according to a distance of the movement of the movable member. When the fuel pressure at the fuel entrance is not higher than a predetermined value, the fuel is supplied only to the pilot fuel passage, while when the fuel pressure at the fuel entrance is higher than the predetermined value, the fuel is supplied to the pilot fuel passage and to the main fuel passage. | 12-27-2012 |
| 20130036738 | TURBOMACHINE FUELING SYSTEM WITH JET PUMP - A fuel supply assembly supplying a combustion chamber of a turbomachine with fuel and pressurizing the fuel, including: a first pump that pressurizes fuel drawn from tanks of an aircraft; a second pump that raises pressure beyond an outlet pressure of the first pump, and that provides constant fuel delivery, some of fuel leaving the second pump being sent to the combustion chamber via a direct circuit, the part of fuel not sent to the combustion chamber being recirculated, via a recirculation circuit, to upstream of the second pump; a hydraulic unit metering delivery to be injected into the combustion chamber of the turbomachine by a metering device on the direct circuit and at least one heat exchanger through which the fuel passes. The exchanger is positioned in a direct circuit downstream of the point at which the recirculation circuit branches off and upstream of the fuel metering device. | 02-14-2013 |
| 20130042620 | METHOD FOR REPAIRING FUEL NOZZLE GUIDES FOR GAS TURBINE ENGINE COMBUSTORS USING COLD METAL TRANSFER WELD TECHNOLOGY - A fuel nozzle guide for a combustor of a turbine engine includes an annular base with a hub section, the hub section at least partially formed of a Cold Metal Transfer (CMT) weld and a method and system therefor. | 02-21-2013 |
| 20130067919 | FUEL SUPPLY DEVICE OF GAS TURBINE ENGINE - A fuel divider included in a fuel supply device of a gas turbine engine includes a movable member which is movable according to a fuel pressure at a fuel entrance, opens only a pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and opens both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure. In addition, the fuel divider includes an adjusting means which adjusts a value of the first pressure in such a manner that it applies to the movable member a counter force in a direction opposite to a direction in which the movable member moves according to the fuel pressure at the fuel entrance, and adjusts the counter force. | 03-21-2013 |
| 20130098040 | SYSTEM FOR TURBINE COMBUSTOR FUEL ASSEMBLY - A system includes a gas turbine engine having a combustor, a liquid fuel supply coupled to the combustor, and a water supply coupled to the liquid fuel supply. The water supply is configured to flow water through the liquid fuel supply while the liquid fuel supply is not in use to flow a liquid fuel. | 04-25-2013 |
| 20130098041 | SYSTEM FOR TURBINE COMBUSTOR FUEL MIXING - A system includes a plurality of interconnected mixing assemblies configured to mix a first fuel and water to generate a first mixture, and mix a second fuel and the water to generate a second mixture. The first and second fuel mixtures are configured to combust in a plurality of combustors of a gas turbine. The interconnected mixing assemblies include first and second fuel passages, a water passage, first and second mixers, first and second fuel valves, and first and second water valves disposed in an integrated housing. The first fuel valve has a first fuel flow coefficient between approximately 1.0 to 1.5, the second fuel valve has a second fuel flow coefficient between approximately 3.0 to 5.0, the first water valve has a first water flow coefficient between approximately 0.4 to 0.55, and the second water valve has a second water flow coefficient between approximately 3.5 to 5.0. | 04-25-2013 |
| 20130098042 | DETECTION OF THE OVERSPEED OF A FREE TURBINE BY MEASURING USING A TORQUE METER - An overspeed protection device includes at least one torque measurement unit supported by an output shaft coupled mechanically to a free turbine of a turbine engine and a signal processing unit able to transmit to a turbine engine regulating system a command to reduce a flow of fuel injected if it is detected that the torque has dropped below a first datum value. The signal processing unit is shaped to command a reduction of the flow if it is detected that the torque has dropped below a first datum value, the torque measurement used to trigger the reduction being taken during a rotation corresponding to a fraction of a revolution of the output shaft. | 04-25-2013 |
| 20130104551 | FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME | 05-02-2013 |
| 20130167538 | Apparatus for mixing fuel and air in a combustion system - A fuel shroud assembly ( | 07-04-2013 |
| 20130174558 | SYSTEM FOR INJECTING FUEL IN A GAS TURBINE ENGINE - Embodiments of the present disclosure provide a turbine combustor having a primary fuel injection system, a first wall portion disposed about a primary combustion zone downstream from the primary fuel injection system, and a second wall portion disposed downstream from the first wall portion. The turbine combustor also has a secondary fuel injection system disposed between the first wall portion and the second wall portion, where the secondary fuel injection system is removable form the first and second wall portions. | 07-11-2013 |
| 20130192232 | Annular combustion chamber of a gas turbine - The present invention relates to an annular combustion chamber of a gas turbine with—relative to the engine axis—a radially outer combustion chamber wall and a radially inner combustion chamber wall, with the combustion chamber walls forming an annular combustion space, with a combustion chamber head having a plurality of fuel nozzles and air inlet openings, with the respective central axes of the fuel nozzles forming an envelope rotationally symmetrical to the engine axis, the envelope dividing the combustion chamber into an annular and radially outer area and an annular and radially inner area, with the radially outer area and the radially inner area having the same volumes. | 08-01-2013 |
| 20130213044 | ARCHITECTURE FOR FEEDING FUEL TO A POWER PLANT FOR DRIVING A ROTARY WING OF A ROTORCRAFT - An architecture for feeding fuel to a power plant ( | 08-22-2013 |
| 20130232976 | GAS TURBINE FUEL FLOW MEASUREMENT USING INERT GAS - The fuel flow rate to a gas turbine is measured using an inert gas. The inert gas is injected into the fuel flow and the concentration of the inert gas in the fuel/inert gas mixture is later measured. The concentration of the inert gas in the fuel/inert gas mixture is then used to calculate the mass flow rate of the fuel. | 09-12-2013 |
| 20130247574 | FUEL MANIFOLD HEAT SHIELD FOR A GAS TURBINE ENGINE - A fuel manifold assembly for a gas turbine engine is described and includes an annular manifold body and an annular heat shield assembly mounted to and surrounding the manifold body. The heat shield assembly has an inner surface facing the manifold body and spaced apart therefrom by an inner air gap, which substantially surrounds the manifold body, defined therebetween. The heat shield assembly has an outer surface facing away from the manifold body and spaced apart from the inner surface by an outer air gap substantially surrounding the inner air gap. At least the outer air gap is formed by a double wall configuration of the heat shield assembly. | 09-26-2013 |
| 20130255261 | SWIRLER FOR COMBUSTION CHAMBERS - A combustion swirler is provided. The combustion swirler includes multiple vanes axially extending from an annular first body portion of the combustion swirler. The combustion swirler also includes an annular second body portion enclosing the multiple vanes for directing a flow of combustion fluid. Each of the vanes comprises an aerodynamic blade body comprising a leading edge with a plurality of first tubercles and a trailing edge with a plurality of second tubercles. | 10-03-2013 |
| 20130255262 | Combustor with Non-Circular Head End - The present application provides a combustor for use with a gas turbine engine. The combustor may include a head end with a non-circular configuration, a number of fuel nozzles positioned about the head end, and a transition piece extending downstream of the head end. | 10-03-2013 |
| 20130269349 | SYSTEM AND METHOD FOR RECIRCULATING A VENTED FUEL TO A FUEL DELIVERY SYSTEM - A system for recirculating a vented fuel to a fuel delivery system of a gas turbine generally includes a vented fuel conduit in fluid communication with the fuel delivery system and a container in fluid communication with the vented fuel conduit. A pump is disposed downstream from the container and a fuel conduit is disposed downstream from the pump. The fuel conduit may provide fluid communication from the pump to the fuel delivery system. | 10-17-2013 |
| 20130291544 | GAS TURBINE ENGINE COMBUSTOR SURGE RETENTION - A combustor assembly for a gas turbine engine includes a static structure and an annular combustor extending around a central axis and located radially inwards of the static structure. The annular combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber there between. The annular combustor is free of any rigid attachments directly between the static structure and the annular outer shell. The annular outer shell includes a radially-outwardly extending flange. A stop member is rigidly connected with the static structure and is located adjacent the radially-outwardly extending flange such that axial-forward movement of the annular combustor is limited. | 11-07-2013 |
| 20130291545 | METHOD AND APPARATUS FOR ISOLATING INACTIVE FUEL PASSAGES - A system includes a turbine engine having a fuel injector. The fuel injector includes fluid ducts, each having a fuel inlet coupled to a distinct fuel source. The system includes a compressed air source that provides compressed air simultaneously to the fluid ducts, and a convergence point where combined fuel and air streams from the ducts are mixed. The fuel inlets are in a parallel flow arrangement such that no fuel from one fuel injector is present at another fuel injector. | 11-07-2013 |
| 20130327044 | FUEL METERING VALVE FAIL-FIXED AND BACK-UP CONTROL SYSTEM - A system provides “fail fixed” functionality and allows a user to manually manipulate fuel flow to a gas turbine engine in the unlikely event the primary control means is unavailable. The fuel metering unit includes a fuel metering valve, a flow increase valve, and a flow decrease valve. The flow increase valve and flow decrease valves are both in fluid communication with the fuel metering valve and are each adapted to selectively receive fuel flow commands from a primary fuel flow command source and from a secondary fuel flow command source. The flow increase and decrease valves are responsive to the fuel flow commands to selectively control the position of the fuel metering valve. | 12-12-2013 |
| 20130327045 | GAS TURBINE COMBUSTION CHAMBER WITH FUEL NOZZLE, BURNER WITH SUCH A FUEL NOZZLE AND FUEL NOZZLE - A gas turbine combustion chamber includes a fuel nozzle with a cylindrical nozzle tube, in which a fluid flows, and a convexly formed nozzle cover, which is arranged downstream of the nozzle tube. The nozzle cover has a central point and a plurality of through-openings through which the fluid leaves the nozzle tube. The through-openings are arranged at different radial distances from the central point at two circular lines. | 12-12-2013 |
| 20140013758 | SYSTEM FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a plurality of fuel injectors circumferentially arranged around the combustion chamber. The plurality of fuel injectors provide fluid communication into the combustion chamber, and a separate cap for each fuel injector defines a separate volume around a different fuel injector outside of the combustion chamber. | 01-16-2014 |
| 20140033721 | 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 that is configured to channel at least a first type of fuel through the turbine engine. A flow member includes a first end portion and a second end portion that is removably coupled to the tube such that the flow member is severally removable from the tube 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 |
| 20140041388 | Aircraft Fuel System Test Unit - This aircraft maintenance equipment is a fuel system leak test unit, designed to insure installation integrity of fuel system lines and hoses and to insure that the system is free from any debris generated during the assembly and maintenance process for an aircraft. The unit is designed to check for leaks using vacuum or pressure while monitoring for fuel leaks or bubbles through a clear tube section. | 02-13-2014 |
| 20140053561 | AIRCRAFT FUEL CELL SYSTEM, AIRCRAFT AND USE OF A SYNTHETIC FUEL - An aircraft fuel cell system is provided. The system includes a fuel tank, a reactor for generating hydrogen gas from a fuel, a heating apparatus and a fuel cell. The reactor can process a synthetic fuel produced from biomass. The use, in an aircraft, of a synthetic fuel, produced from biomass, for generating a gas that contains hydrogen is also provided. | 02-27-2014 |
| 20140069102 | GAS TURBINE ENGINE FUEL SYSTEM METERING VALVE - A metering valve for a gas turbine engine fuel system includes a sleeve including first, second, third, fourth, fifth and sixth ports respectively axially spaced apart from one another. A spool is slidably received in the sleeve and includes first, second and third seal lands. The first seal land selectively connects the first and second ports to one another, and the third seal land selectively connects the third and fourth ports to one another and the fifth and sixth ports to one another. | 03-13-2014 |
| 20140096526 | SYSTEM FOR OPERATING A COMBUSTOR OF A GAS TURBINE - An end cover for a gas turbine combustor includes a main body configured to connect to a casing that at least partially surrounds a portion of the gas turbine. A fuel circuit extends within the main body of the end cover. An orifice extends through the main body. The orifice is in fluid communication with the fuel circuit. The end cover further includes a linear actuator. The linear actuator includes a flow control member that extends the fuel circuit and at least partially through the orifice. | 04-10-2014 |
| 20140130502 | GAS TURBINE ASSEMBLY AND METHOD THEREFOR - An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange. | 05-15-2014 |
| 20140144140 | FUEL BOOST MODULE - A fuel boost module for a gas turbine engine having a base, a fuel inlet configured to receive fuel from a fuel supply, a fuel outlet configured to deliver fuel to the gas turbine engine, a filter assembly configured to filter the fuel, a fuel controller configured to regulate pressure of the fuel that will be delivered to the gas turbine engine, a boost pump configured to pressurize the fuel, and a main pump configured to pressurize the fuel. | 05-29-2014 |
| 20140165571 | FUEL CIRCUIT OF A TURBINE ENGINE - A fuel circuit for a turbine engine, the fuel circuit comprising:
| 06-19-2014 |
| 20140196459 | HIGH PRESSURE, MULTIPLE METERING ZONE GAS TURBINE ENGINE FUEL SUPPLY SYSTEM AND METHOD - A gas turbine engine fuel supply system includes a primary gear pump, a secondary gear pump, and a pump bypass valve. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The pump bypass valve is configured to regulate fuel pressure at the primary gear pump outlet to one of a plurality of preset differential pressures above one of a plurality of fuel load pressures and prevents reverse pressurization of the gear pumps. | 07-17-2014 |
| 20140216037 | ENGINE FUEL CONTROL SYSTEM - An engine fuel control system includes a metering valve to control fuel flow between the supply and delivery line with a pressure drop control regulating the pressure across the valve and maintain a substantially constant pressure across the valve. The fuel control system includes a backup system controllable by a pullback signal to operate the pressure control, thus increasing the pullback signal reducing the fuel flow between the supply and delivery line. The fuel control system detects a start of an engine overthrust event, and when the upward runaway is caused by the arrested overthrust event. The fuel control system's controller which (i) determines the overthrust detection, the pullback signal increase rate and the pullback signal offset, (ii) sends the pullback signal to the backup system at the rate of increase, and (iii), reduces the pullback signal to the backup system when the upward runaway is arrested by the offset. | 08-07-2014 |
| 20140245739 | FUEL SYSTEM OF GAS TURBINE ENGINES - A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source. | 09-04-2014 |
| 20140260260 | COMBUSTOR FOR GAS TURBINE ENGINE - A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber. | 09-18-2014 |
| 20140260261 | TURBOMACHINE WITH TRANSITION PIECE HAVING DILUTION HOLES AND FUEL INJECTION SYSTEM COUPLED TO TRANSITION PIECE - A turbomachine is provided and includes a combustor in which fuel and air are combusted, a turbine disposed for reception of products of combustion from the combustor, a transition piece fluidly interposed between the combustor and the turbine and including a body formed to define dilution holes configured to allow air to enter the combustor and for enabling steam injection toward a main flow of the products of the combustion proceeding from the combustor to the turbine and a fuel injection system supportively coupled to the transition piece and configured to inject fuel toward the main flow of the products of the combustion to thereby restore a flame temperature of the main flow of the products of the combustion reduced by steam injection enabled by the dilution holes. | 09-18-2014 |
| 20140260262 | SYSTEMS AND APPARATUS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES - A gas turbine that includes: a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a primary air and fuel injection system that defines a forward end, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end; and a downstream injection system that includes two injection stages, a first stage and a second stage, that are axially spaced along the longitudinal axis of the interior flowpath. The first stage and the second stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath. | 09-18-2014 |
| 20140260263 | FUEL INJECTION INSERT FOR A TURBINE NOZZLE SEGMENT - One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit. | 09-18-2014 |
| 20140260264 | SYSTEM FOR CONTROLLING A FLOW RATE OF A COMPRESSED WORKING FLUID TO A COMBUSTOR FUEL INJECTOR - A system for controlling air flow rate of a compressed working fluid to a fuel injector of a combustor includes an outer casing that defines a high pressure plenum around a portion of the combustor, an extraction port in fluid communication with the high pressure plenum and an inlet port. The combustor includes a plurality of fuel injectors arranged around a combustion liner, an inner flow sleeve, an outer air shield that surrounds the plurality of fuel injectors and the inner flow sleeve. The outer air shield defines an injection an air plenum between the outer air shield and the inner flow sleeve and an inlet to the injection air plenum. An external fluid circuit provides fluid communication between the extraction port and the inlet port. A baffle extends between the outer casing and the outer air shield to provide flow separation between the inlet and the high pressure plenum. | 09-18-2014 |
| 20140260265 | COMBUSTION CHAMBER FOR A GAS TURBINE AND BURNER ARRANGEMENT - A combustion chamber ( | 09-18-2014 |
| 20140305126 | FLOW VELOCITY DISTRIBUTION EQUALIZING APPARATUS - An apparatus for equalizing flow velocity distribution of a fuel gas supplied into a catalytic combustor includes a rectification vane and a rectification plate in an inlet chamber of the catalyst combustor. The inlet chamber has a round transverse sectional shape and includes an inflow port that allows the fuel gas to inflow radially, and an outflow port for discarding the fuel gas axially. The rectification vane has a front edge oriented towards the inflow port, and a rectifying surface ramified from the front edge so as to extend towards a cylindrical inner wall surface of the inlet chamber such that swirling flow of the fuel gas flown into the inlet chamber, that flows towards the inflow port along the cylindrical inner wall surface, is generated. The rectification plate is located at the outflow port and has openings for allowing the fuel gas to flow therethrough. | 10-16-2014 |
| 20140318134 | BACKUP FUEL SUPPLY FOR A GAS TURBINE - A system for supplying a gaseous fuel to a gas turbine includes a liquefied fuel source for supplying a liquefied fuel to a liquid fuel pump that is disposed downstream from the liquefied fuel source. The liquid fuel pump is sufficient to raise the pressure of the liquefied fuel to a substantially supercritical pressure. A supercritical liquefied fuel vaporizer is disposed downstream from the liquid fuel pump. A heat recovery system is in thermal communication with the liquefied fuel. The heat recovery system is positioned between the liquid fuel source and the supercritical liquefied fuel vaporizer. | 10-30-2014 |
| 20140331674 | WAKE REDUCING STRUCTURE FOR A TURBINE SYSTEM AND METHOD OF REDUCING WAKE - A wake reducing structure for a turbine system includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is an airfoil at least partially disposed in the wake region, the airfoil comprising at least one airfoil hole. | 11-13-2014 |
| 20140360195 | Low Calorific Fule Combustor For Gas Turbine - A low calorific value fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the-liner also defining inner primary and intermediate regions of a combustion zone and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A nozzle assembly disposed at the closed housing end includes an air blast nozzle and surrounding swirl vanes. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner impingement cools the portion of the liner defining the combustion zone. A portion of the combustor air is introduced directly into the intermediate region. | 12-11-2014 |
| 20140366541 | SYSTEMS AND APPARATUS RELATING TO FUEL INJECTION IN GAS TURBINES - A gas turbine engine having a combustor that includes: an inner radial wall defining a first interior chamber and a second interior chamber, wherein the first interior chamber extends axially from an end cover to a primary fuel injector, and the second interior chamber extends axially from the primary fuel injector to the turbine; an outer radial wall formed about the inner radial wall so that a flow annulus is formed therebetween; upstream fuel nozzles jutting into the flow annulus from the outer radial wall. The upstream fuel nozzles may include non-uniform circumferential spacing about the inner radial wall. | 12-18-2014 |
| 20150082795 | INTERNALLY COOLED TRANSITION DUCT AFT FRAME - An aft frame for a transition duct of a gas turbine combustor includes a main body having an outer rail, an inner rail, a first side rail circumferentially separated from an opposing second side rail, a forward portion, an aft portion and an outer surface. An inlet port extends through the outer surface and an exhaust port extends through the forward portion. A serpentine cooling passage is defined within the main body beneath the outer surface. The serpentine cooling passage is in fluid communication with the inlet port and the exhaust port. A conduit may be connected to the exhaust port for routing a compressed working fluid away from aft frame. | 03-26-2015 |
| 20150128599 | CONTINUOUS DETONATION COMBUSTION ENGINE AND SYSTEM - One embodiment of the present disclosure is a gas turbine engine. Another embodiment is a unique combustion system. Another embodiment is a unique engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for employing continuous detonation combustion processes. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 05-14-2015 |
| 20150337736 | TURBOMACHINE FUEL CIRCUIT - A fuel circuit of a turbomachine, this circuit including a fuel return valve connected to the main fuel circuit and to a tank, the valve being able to take a first and a second open position, separate from one another, and a closed position, two primary hydraulic lines connecting the valve to the main circuit and including, respectively, first and second filters through which the fuel passes when the valve is in its first open position, two secondary hydraulic lines which connect the valve to the main circuit and which are positioned in relation to the first and second filters in such a way that the circulation of fuel in these secondary lines contributes, respectively, to the cleaning of the first and second filters, the fuel circulating in the secondary lines when the valve is in its second open position. | 11-26-2015 |
| 20160017817 | METERING DEVICE FOR A FUEL FEED CIRCUIT OF AN ENGINE - A metering device for an engine fuel feed circuit, the device including a metering valve, and a pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve, wherein the metering valve includes a seat provided with an inlet orifice and an outlet orifice, a shutter arranged within the seat, and an actuator controlling the position of the shutter, and wherein, between the inlet orifice and the outlet orifice the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position. | 01-21-2016 |
| 20160053689 | ENGINE OVERSPEED PROTECTION WITH THRUST CONTROL - A fuel pump system having a servo controlled pump bypass is utilized. The servo controlled bypass around the fuel pump provides the capability for the fuel flow rate to be adjusted and controlled independent of the fuel metering system. | 02-25-2016 |
| 20160076452 | GAS TURBINE ENGINE MECHANICAL-ELECTRICAL HYBRID FUEL DELIVERY SYSTEM - A gas turbine engine fuel delivery system includes a mechanically-driven fuel pump, an electrically-driven fuel pump, and an engine control. The mechanically-driven fuel pump is adapted to receive a drive torque from a gas turbine engine draw fuel into its fuel inlet and discharge the fuel from its fuel outlet. The electrically-driven fuel pump has a first fuel inlet/outlet that is in fluid communication with the mechanically-driven fuel pump fuel inlet, and also has a second fuel inlet/outlet. The engine control is responsive to an engine start signal to cause the electrically-driven fuel pump to be temporarily energized to pump fuel from the first fuel inlet/outlet to the second fuel inlet/outlet, and is responsive to an engine shutdown signal to cause the electrically-driven pump to be temporarily energized to pump fuel from the second fuel inlet/outlet to the first fuel inlet/outlet. | 03-17-2016 |
| 20160090913 | GAS TURBINE SYSTEM WITH COOLING FLUID GENERATOR - A gas turbine system ( | 03-31-2016 |
| 20160131042 | SYSTEMS AND METHODS FOR CONTROLLING FUEL PATH AVAILABILITY FOR AN AIRCRAFT - A fuel system which includes a fuel return system. The fuel return system includes a fuel return valve arranged on a return line, and the return line is intended to be mounted between an engine of an aircraft and a fuel tank of the aircraft. The return valve is configured to allow a return of fuel from the engine to the fuel tank when the engine is in operation. The fuel return system also includes a bypass valve assembly mounted in parallel to the return valve, and is configured to allow a return of fuel from the engine to the fuel tank when the engine is not in operation. | 05-12-2016 |
| 20160138808 | DEVICE FOR DETERMINING A FUEL SPLIT, AS GAS TURBINE OR AN AIRCRAFT ENGINE COMPRISING SUCH A DEVICE AND APPLICATION OF THE SAME - A device for determining a fuel split, and particularly a final fuel split in at least one staged combustion chamber of a gas turbine or an aircraft engine is provided. The device comprises a first control device for determining a preselected fuel split demand for the staged combustion chamber, wherein this determination can be performed based on the detection of a steady state or the detection of a transient state. The detection can in particular be performed based on a combustion chamber exit temperature, a turbine input temperature and/or a value for the fuel/air ratio. | 05-19-2016 |
| 20160201574 | DIRECT METERING USING A VARIABLE DISPLACEMENT VANE PUMP | 07-14-2016 |
