Abstract: A fuel injector for a combustion engine includes an injector head including a nozzle, a premixer, and a distributor structured to distribute a plurality of different fuels to different sets of fueling orifices in the premixer. A pilot assembly of the fuel injector is coupled to the premixer and includes a first fueling passage for a first fuel and a second fueling passage for a second fuel. Multiple sets of fueling orifices are positioned within the fuel injector, the fueling orifice sets being selectively connectable to a plurality of different fuel supplies, and both located and sized so as to accommodate a wide range of flow rates to enable a combustion engine coupled with the fuel injector to operate on fuels having a range of Wobbe numbers and compositions.

Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes two primary tubes, a secondary tube, a primary gas gallery, and a secondary gas gallery. The two primary tubes are connected in a parallel configuration to provide a main gas fuel to the primary gas gallery. The secondary tube provides the main gas fuel to the secondary gas gallery independent from the two primary tubes and the primary gas gallery. The primary gas gallery and the secondary gas gallery provide the main gas fuel to a premix passage independently allowing for robust control of the gas turbine engine.

Abstract: A center body assembly for a fuel injector is disclosed. The center body assembly defines a primary liquid passage, a liquid gallery, swirl slots, and a prefilm passage. The primary liquid passage supplies liquid fuel to the liquid gallery. The liquid gallery includes a gallery discharge end and a gallery inlet end that aligns with the primary liquid passage. The liquid gallery tapers down from the gallery inlet end to the gallery discharge end. The swirl slots extend from the liquid gallery to the prefilm passage in a helical pattern. The prefilm passage includes an annular shape that turns inward towards an assembly axis of the center body assembly.

Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes a flange assembly with a distribution block, three main gas tubes, and an injector head. The distribution block evenly distributes a main gas fuel to the three main gas tubes. The injector head includes an injector body with a primary gas gallery including an annular shape. The three main gas tubes are connected in a parallel configuration between the distribution block and the primary gas gallery. The three main gas tubes are all in flow communication with the primary gas gallery and provide the main gas fuel from the same main gas fuel source.

Abstract: A method for lean direct injection of a liquid fuel from a fuel injector into a combustion chamber of a gas turbine engine is disclosed. The method includes injecting all of the liquid fuel into the combustion chamber through a pilot liquid fuel circuit during light off and during acceleration towards idle. The method also includes injecting the liquid fuel in two streams including injecting a majority of the liquid fuel as an annular film through a main liquid fuel circuit and injecting a remainder of the liquid fuel through the pilot liquid fuel circuit when the gas turbine engine is at idle and for operating ranges of the gas turbine engine above idle.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas outer tube, a gas inner tube, a liquid tube, and a heat shield. The gas outer tube and the gas inner tube form a gas fuel annulus. The gas inner tube and the liquid tube form a liquid fuel annulus. The liquid tube forms an air cavity. The heat shield extends within the liquid tube forming an insulating gap between the heat shield and the liquid tube.

Abstract: Systems and methods for enhancing the performance of resource state polling are disclosed. According to an aspect, a method includes using at least one processor and memory for transmitting a request and a baseline timestamp for an updated resource state based on a current resource state, wherein the baseline timestamp defines a time period for the updated resource state. The method also includes determining the updated resource state based on the baseline timestamp and the current resource state. The method also includes providing the determined updated resource state and current timestamp of the determined updated resource state. Additionally, the method includes setting a current baseline resource state based on a current timestamp of the determined updated resource state.

Abstract: An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion. The transition end also includes a plurality of wipe passages extending through the transition end. The tip end includes a cylindrical portion with a hollow right circular cylinder shape. The premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface.

Abstract: A system for automatically collecting and analyzing crash dumps to determine if a security exploit was unsuccessful and generating a report.

Abstract: A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an injector of a gas turbine engine while the shroud remains fixed to pilot liquid fuel conduit.

Abstract: A liquid gallery for a fuel injector of a gas turbine engine includes a gallery body, a liquid gallery scroll, a plurality of atomizer inlets, and a plurality of atomizer bosses. The liquid gallery scroll extends into the gallery body spanning from a first end to a second end in a circumferential direction. The liquid gallery scroll includes a taper with a cross-sectional area of the liquid gallery scroll reducing from the first end to the second end. Each atomizer inlet is in flow communication with the liquid gallery scroll. Each atomizer boss is aligned with one of the plurality of atomizer inlets.

Abstract: A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a flange, a fitting boss, a stem, a gas fuel passage, a gas fuel fitting, and a gas heat shield. The fitting boss protrudes from the flange. The stem extends from the flange. The gas fuel passage extends through the stem. The gas fuel fitting is joined to the fitting boss. The gas heat shield extends from the gas fuel fitting at least partially through the gas fuel passage. The gas heat shield is sized to form a gas heat shield gap between the gas heat shield and the stem at the gas fuel passage.

Abstract: A method of saving power in a computing system having a plurality of dial in-line memory modules (DIMMs) and employing a suspend-to-RAM sleep mode includes, when entering suspend-to-RAM sleep mode, consolidating selected information into a subset of DIMMs, and turning off power to all other DIMMs. A DIMM power rail may be coupled to each of the DIMMs, the DIMM power rail being configured to selectively have power being supplied to respective DIMMs turned off in response to enable/disable logic signals.

Abstract: A system for automatically collecting and analyzing crash dumps to determine if a security exploit was unsuccessful and generating a report.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas outer tube, a gas inner tube, a liquid tube, and a heat shield. The gas outer tube and the gas inner tube form a gas fuel annulus. The gas inner tube and the liquid tube form a liquid fuel annulus. The liquid tube forms an air cavity. The heat shield extends within the liquid tube forming an insulating gap between the heat shield and the liquid tube.

Abstract: A method for modifying a gas turbine injector is disclosed herein. The method for modifying a gas turbine injector includes removing a first tubular member from the gas turbine injector, replacing the first tubular member with a second tubular member, the second tubular member having a center axis and including a circumferential lip extending radially from the center axis, aiming a laser beam at the circumferential lip so that the laser beam forms an acute angle with the center axis, and, laser welding the second tubular member to the gas turbine injector at the acute angle, the laser welding forming a resultant weld between the second tubular member and the gas turbine injector, and such that at least a portion of the circumferential lip is consumed to form at least a portion of the resultant weld.

Abstract: A pilot liquid tube having a pilot liquid fuel inlet, a pilot liquid fuel conduit, a pilot liquid fuel nozzle, and a shroud configured to shield the pilot liquid fuel nozzle. The pilot liquid tube may be installed and/or removed from an injector of a gas turbine engine while the shroud remains fixed to pilot liquid fuel conduit.

Abstract: A gas turbine engine outer premix barrel is disclosed. The outer premix barrel includes a body portion, a barrel portion, and a plurality of vanes. The body portion includes vent air inlets. The barrel portion extends axially aft from the body portion. The plurality of vanes extends axially forward from the body portion. Each vane includes an inward surface located at a radially inner end of the vane, and a plurality of vent passages exiting the vane at the inward surface. Each vent passage is in flow communication with at least one vent air inlet.

Abstract: An inner premix tube for a fuel injector of a gas turbine engine includes a transition end, a tip end, and a premix tube inner surface. The transition end includes an annular disk portion with an annular disk shape and a redirection portion extending radially inward and axially from the annular disk portion. The transition end also includes a plurality of wipe passages extending through the transition end. The tip end includes a cylindrical portion with a hollow right circular cylinder shape. The premix tube inner surface is a radially outer surface including the redirection portion outer surface and the cylindrical portion outer surface.