Abstract: A method of repairing a fuel nozzle is disclosed comprising the steps of preparing a damaged component for repair; directing thermal energy towards a substrate; directing a stream of powder material; and depositing the powder material onto the substrate.

Abstract: A repairable fuel nozzle is disclosed, comprising an adaptor configured to direct a fuel flow from at least one flow passage in a fuel distributor to a pilot assembly comprising a fuel swirler.

Abstract: A mixer assembly for a gas turbine engine, including: a primary fuel injector having a central axis for injecting a primary fuel spray into a primary air stream, wherein fuel is provided at a desired rate and droplets of the fuel spray are within a desired size range; a secondary fuel injector positioned radially outwardly of the primary fuel injector for injecting a secondary fuel spray into a secondary air stream spaced radially outwardly of and surrounding the primary air stream; and, a primary air jet positioned between the primary fuel injector and the secondary fuel injector to direct a portion of an incoming air stream between the primary air stream and the secondary air stream.

Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including a fan section at a forward end of the gas turbine engine for producing a first compressed air flow; a first compressor positioned downstream of the fan section and in flow communication with at least a portion of the first compressed air flow, wherein the first compressor produces a second compressed air flow having a designated pressure; a combustor positioned downstream of the first compressor and in flow communication with second compressed air flow, wherein the combustor produces combustion products from a mixture of fuel and air; a first turbine positioned downstream of the combustor and in flow communication with combustion products, wherein the first turbine powers the first compressor by means of a first rotatable drive shaft connected therebetween; and, a second turbine positioned downstream of the first turbine and in flow communication with the combustion products exiting the first turbine, wherein the second turbine

Abstract: A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

Abstract: A multi-staged gas turbine engine fuel supply fuel injector includes at least first and second staged fuel injection circuits having first and second fuel injection points. At least first and second fuel nozzle valves operable to open at different first and second crack open pressures are controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector includes a valve housing containing the fuel nozzle valves.

Abstract: A multi-staged gas turbine engine fuel supply system includes a plurality of fuel injectors and at least first and second staged fuel injection circuits in each of the fuel injectors. Each of the first and second staged fuel injection circuits includes first and second fuel injection points and at least first and second fuel nozzle valves operable to open at different first and second crack open pressures and controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector may have a valve housing with one of the first fuel nozzle valves and one of the second fuel nozzle valves contained therein.

Abstract: A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

Abstract: A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

Abstract: A coating system and method for reducing the tendency for hydrocarbon fluids, such as fuels and oils, to form carbonaceous deposits that adhere to a wall of a containment article. Of particular concern are carbonaceous deposits that form at temperatures below about 650° F. (about 345° C.). The coating system combines an outermost layer of platinum with a ceramic barrier layer. The coating system significantly reduces the formation of carbonaceous deposits and the adhesion of such deposits. To further reduce wall and hydrocarbon fluid temperatures and formation of carbonaceous deposits, the coating system is preferably applied to the surface of the wall wetted by the fluid, as well as the opposite surface of the wall exposed to a surrounding environment. The outermost layers serve as radiation shields to reduce heat transfer from the surrounding environment to the wall, and from the wall to the hydrocarbon fluid.

Abstract: A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

Abstract: A fuel injector nozzle for dispensing fuel in the combustion chamber of a gas turbine engine, includes an elongated, multi-layered, convoluted nozzle feed strip having an internal passage for directing fuel through the length of the strip from the inlet end to an outlet end; and a cylindrical, multi-layered fuel dispensing nozzle unitary with the feed strip and fluidly connected to the outlet end of the feed strip for dispensing the fuel. The multi-layered feed strip and nozzle allows complex porting of fuel circuits through the injector. The internal fluid passages through the feed strip and nozzle are formed by etching.

Abstract: A fuel injector has at least two generally parallel feed strips. Each of the feed strips is constructed from a single bonded together pair of lengthwise extending plates, each plate having a single row of widthwise spaced apart and lengthwise extending parallel grooves. The plates in each strip are bonded together such that opposing grooves in each of the plates are aligned forming internal fuel flow passages through the length of the strip from an inlet end to an outlet end of the strip. The inlet ends are spaced apart from each other and the outlet ends are spaced apart from each other. Each of the feed strips has one or more convolutions along a length of the strip and the feed strips are not bonded together along the convolutions. The feed strips may be spaced apart from each other or may be in contact with each other.

Abstract: A fuel injector nozzle for dispensing fuel in the combustion chamber of a gas turbine engine, includes an elongated, multi-layered, convoluted nozzle feed strip having an internal passage for directing fuel through the length of the strip from the inlet end to an outlet end; and a cylindrical, multi-layered fuel dispensing nozzle unitary with the feed strip and fluidly connected to the outlet end of the feed strip for dispensing the fuel. The multi-layered feed strip and nozzle allows complex porting of fuel circuits through the injector. The internal fluid passages through the feed strip and nozzle are formed by etching.

Abstract: A fuel injection system for use with a gas turbine engine includes a plurality of thermally compatible fuel nozzles. Each fuel nozzle includes a delivery system to deliver a fluid supply to the gas turbine engine and a support system for supporting the delivery system. The delivery system is disposed within the support system and is subjected to lower operating temperatures than the support system. The delivery system is fabricated from a material having a coefficient of expansion approximately twice a coefficient of expansion for the material used in fabricating the support system.

Abstract: A phase meter and method of providing a voltage indicative of a phase difference between a reference signal and an input signal in which the amplitudes of the two signals are made approximately the same to cancel potential phase errors caused by different amplitudes, and the two signals are provided to two matched comparators, one receiving the input signal and the other receiving the reference signal. The two matched comparators are connected together so as to provide an output logic signal in accordance with a prescribed, unconventional, truth table. The output logic signal is a pulse whose duration is proportional to the phase difference. The output logic signal is converted to a voltage indicative of the phase difference between the reference signal and the input signal. The phase meter is relatively simple to make and a preferred embodiment measures phase shift directly with a 10 mV/degree output at up to 10 MHz.

Abstract: A combustor dome assembly is provided with a single continuous annular dome plate having at least one circumferential row of spaced openings therethrough, a swirl cup assembly attached to each of the dome plate openings, and inner and outer cowls connected to the radially inner and outer ends of the dome plate. A ferrule located immediately upstream of the swirl cup assembly acts as an interface between a fuel nozzle and the swirl cup assembly. An integral cowl plate/ferrule retainer is located immediately upstream of and connected to the swirl cup assembly, where the ferrule retainer portion retains the ferrule while allowing it to float radially therewithin and the cowl plate portion includes flanges which extend beyond the outer diameter of the swirl cup to provide blockage in addition to that provided by the inner and outer cowls.

Abstract: Coking of the hot external face of fuel nozzles operating in the combustor of a gas turbine engine is reduced by controlling air discharging from the nozzle face in a manner to provide a recirculation zone spaced away from the nozzle face a distance effective to substantially reduce coking and yet maintain a stable flame front in the combustor.

Abstract: Apparatus for converting the revolutions of a shaft into pulses including a disc having devices such as slots or reflectors radially spaced around its periphery and light-transmitting and light-receiving fiber optic cables aligned for sensing the devices as the disc rotates. A light source, such as a light-emitting diode, is positioned at the outer end of a light-transmitting cable for providing light, and at least one phototransistor at the outer end of a light-receiving cable converts the light signals into electric pulses. Preferably, the light-transmitting and light-receiving cables are paired, giving successive signals as a slot or reflector is sensed for activating a counting circuit. A single light-transmitting cable is preferably split near the disc to provide two light sources from a single light-emitting diode.