Abstract: A system and method operable to facilitate thermal wall plug sensing and control may include an ability to control current drawn by a charging system or other load according to a temperature determined at an interface between the charging system and an energy source used to provided energy to the charging system. A temperature sensed with a temperature sensor included in a plug assembly or other housing or cord used to connect the charging system to the energy source may be used to implement the temperature regulated current control.

Abstract: A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.

Abstract: A method for assembling a gas turbine engine combustor is provided. The method includes providing a heat shield defined by a perimeter. The perimeter includes a radially inner edge, a radially outer edge, an axially inner edge, an axially outer edge, and an opening that extends from an upstream side of the heat shield to a downstream side of the heat shield. The method further includes coupling the heat shield to a domeplate such that the perimeter of the heat shield is positioned a distance downstream from an edge of the heat shield defining the opening. The method additionally includes coupling at least one fuel injector to the domeplate such that a portion of the fuel injector extends through the heat shield opening.

Abstract: An apparatus for attenuating acoustic oscillations of a gas flow contained in part by a combustor wall of a gas turbine engine combustor, wherein the combustor includes at least one air/fuel mixer, includes at least one resonating tube with a closed end and an open end and a single cavity between the ends. The tube is located on the combustor wall downstream of the air/fuel mixer.

Abstract: An acoustic dampener comprises a first wall, orifice plate, and second wall. The first wall separates a first fluid source from a second fluid source. The first wall has a hole for allowing fluid communication between the first fluid source and a first cavity of the acoustic dampener. The office plate separates the first cavity of the acoustic dampener from a second cavity of the acoustic dampener. The second wall has a hole for allowing fluid communication between the first cavity of the acoustic dampener in the second cavity of the acoustic dampener. The second wall separates the second cavity of the acoustic dampener from the second fluid source. The second wall has a hole for allowing fluid communication between the second cavity of the acoustic dampener and the second fluid source. In one embodiment, the acoustic dampener is formed in a combustion chamber liner of a gas turbine engine.

Abstract: A system and method for flame stabilization is provided that forestalls incipient lean blow out by improving flame stabilization. A combustor profile is selected that maintains desired levels of power output while minimizing or eliminating overboard air bleed and minimizing emissions. The selected combustor profile maintains average shaft power in a range of from approximately 50% up to full power while eliminating overboard air bleed in maintaining such power settings. Embodiments allow for a combustor to operate with acceptable emissions at lower flame temperature. Because the combustor can operate at lower bulk flame temperatures during part power operation, the usage of inefficient overboard bleed can be reduced or even eliminated.

Abstract: An acoustic dampener comprises a first wall, orifice plate, and second wall. The first wall separates a first fluid source from a second fluid source. The first wall has a hole for allowing fluid communication between the first fluid source and a first cavity of the acoustic dampener. The office plate separates the first cavity of the acoustic dampener from a second cavity of the acoustic dampener. The second wall has a hole for allowing fluid communication between the first cavity of the acoustic dampener in the second cavity of the acoustic dampener. The second wall separates the second cavity of the acoustic dampener from the second fluid source. The second wall has a hole for allowing fluid communication between the second cavity of the acoustic dampener and the second fluid source. In one embodiment, the acoustic dampener is formed in a combustion chamber liner of a gas turbine engine.

Abstract: A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.

Abstract: In at least one embodiment, a device for balancing a flow of electrical energy from a vehicle to an external power source is provided. The device comprises a balance circuit being configured to receive an input current signal from the power source and to transmit an output current signal to the external power source for charging a element in a vehicle. A differential resistance causes the input current signal and the output current signal to be different. A current measuring device is configured to generate an output differential signal indicating a difference between the input and output current signals. A current generating device is configured to generate a compensated current signal in response to the output differential signal and to adjust the output current signal with the compensated current signal such that the input and output current signals are generally similar to one another.

Abstract: A system and method operable to facilitate thermal wall plug sensing and control may include an ability to control current drawn by a charging system or other load according to a temperature determined at an interface between the charging system and an energy source used to provided energy to the charging system. A temperature sensed with a temperature sensor included in a plug assembly or other housing or cord used to connect the charging system to the energy source may be used to implement the temperature regulated current control.

Abstract: A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow.

Abstract: An apparatus for attenuating acoustic oscillations of a gas flow contained in part by a combustor wall of a gas turbine engine combustor, wherein the combustor includes at least one air/fuel mixer, includes at least one resonating tube with a closed end and an open end and a single cavity between the ends. The tube is located on the combustor wall downstream of the air/fuel mixer.

Abstract: In at least one embodiment, a device for balancing a flow of electrical energy from a vehicle to an external power source is provided. The device comprises a balance circuit being configured to receive an input current signal from the power source and to transmit an output current signal to the external power source for charging a element in a vehicle. A differential resistance causes the input current signal and the output current signal to be different. A current measuring device is configured to generate an output differential signal indicating a difference between the input and output current signals. A current generating device is configured to generate a compensated current signal in response to the output differential signal and to adjust the output current signal with the compensated current signal such that the input and output current signals are generally similar to one another.

Abstract: A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.

Abstract: A method for operating a combustion system is provided. The method includes coupling the main swirler to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler, supplying fuel to a first fuel circuit defined in the main swirler, and inducing swirling to the supplied fuel via a first set of swirler vanes positioned within the main swirler. The method also includes supplying fuel to a second fuel circuit defined in the main swirler, inducing swirling to the supplied fuel via a second set of swirler vanes positioned within the main swirler, each of the second set of swirler vanes comprising at least one second fuel passage defined therein, and coupling a shroud in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud comprising at least one third fuel passage defined therein.

Abstract: A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.

Abstract: A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow.

Abstract: A method for operating a combustion system is provided. The method includes coupling the main swirler to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler, supplying fuel to a first fuel circuit defined in the main swirler, and inducing swirling to the supplied fuel via a first set of swirler vanes positioned within the main swirler. The method also includes supplying fuel to a second fuel circuit defined in the main swirler, inducing swirling to the supplied fuel via a second set of swirler vanes positioned within the main swirler, each of the second set of swirler vanes comprising at least one second fuel passage defined therein, and coupling a shroud in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud comprising at least one third fuel passage defined 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 an annular centerbody extending therebetween. The method comprises injecting at least one of fuel and airflow into the combustor through at least one swirler positioned within the pilot mixer, and injecting fuel into the combustor through at least one swirler positioned within the main mixer, such that the fuel is directed into a combustion chamber downstream from the main 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 an annular centerbody extending therebetween. The method comprises injecting at least one of fuel and airflow into the combustor through at least one swirler positioned within the pilot mixer, and injecting fuel into the combustor through at least one swirler positioned within the main mixer, such that the fuel is directed into a combustion chamber downstream from the main mixer.