Abstract: A system for reducing combustion dynamics in a combustor includes an end cap that extends radially across the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap, and tubes extend from the upstream surface through the downstream surface. Each tube provides fluid communication through the end cap to the combustion chamber. The system further includes means for reducing combustion dynamics in the combustor. A method for reducing combustion dynamics in a combustor includes flowing a working fluid through tubes that extend axially through an end cap that extends radially across the combustor and obstructing at least a portion of the working fluid flowing through a first set of the tubes.

Abstract: Certain embodiments herein relate to systems and methods for managing a combustor of a gas turbine engine. In one embodiment, a system can include at least one memory configured to store computer-executable instructions and at least one controller configured to access the at least one memory and execute the computer-executable instructions. The instructions may be configured to monitor the dynamic and static pressures of the combustor by a single sensor. The instructions may be further configured to generate a signal based at least in part on the dynamic and static pressures. Furthermore, the instructions may be configured to facilitate in the execution of at least combustor control event based at least in part on the signal.

Abstract: Systems, methods and apparatus for providing an electromagnetic flow controller. In one embodiment, an electromagnetic flow controller can have two substrates, a permanent magnet, and two electrical traces. One of the substrates may deflect away from the other substrate upon applying an electrical signal to at least one of the two electrical traces.

Abstract: A combustion dynamics control system for an aviation based or land based gas turbine engine employs an acoustic driver that is configured to drive pressure perturbations across a premixed fuel injection orifice to substantially zero in response to a control signal such that fuel flow perturbations across the fuel injection orifice are substantially zero.

Abstract: A combustor cap for use with a number fuel nozzles, the combustor cap including a cold side plate, a hot side plate, and a cap cavity extending between the cold side plate and the hot side plate with the number of fuel nozzles extending therethrough. A resonator tube may extend from the cold side plate into the cap cavity.

Abstract: In one embodiment, a system includes a variable geometry resonator configured to couple to a fluid path upstream from a combustor of a turbine engine. The variable geometry resonator is configured to dampen pressure oscillations in the fluid path and the combustor.

Abstract: Systems, methods and apparatus for providing an electromagnetic flow controller. In one embodiment, an electromagnetic flow controller can have two substrates, a permanent magnet, and two electrical traces. One of the substrates may deflect away from the other substrate upon applying an electrical signal to at least one of the two electrical traces.

Abstract: A combustor for a gas turbine engine and related method is provided in which a plurality of combustor cans are selectively adapted with corresponding resonators. The resonators may, for example, be attached to every can in the consecutive arrangement of combustor cans, every other can, every third can or the like, and may be tuned to the same or first, second, third, etc. frequencies of operation. Such selective tuning is configured to suppress one or more of out-of-phase and in-phase dynamic interaction of streams discharged from adjacent combustor cans by changing the frequencies of pressure oscillation instabilities across the arrangement of consecutive cans.

Abstract: 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.

Abstract: A system for reducing combustion dynamics in a combustor includes an end cap that extends radially across the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap, and tubes extend from the upstream surface through the downstream surface. Each tube provides fluid communication through the end cap to the combustion chamber. The system further includes means for reducing combustion dynamics in the combustor. A method for reducing combustion dynamics in a combustor includes flowing a working fluid through tubes that extend axially through an end cap that extends radially across the combustor and obstructing at least a portion of the working fluid flowing through a first set of the tubes.

Abstract: A gas turbine engine control system comprises a data acquisition and analysis system for receiving a signal from a combustion dynamics sensor and providing an output signal and a combustion dynamics control system for controlling combustion dynamics based on the output signal. The control system is associated with a purge-air flow and comprises an acoustic driver, or a flow-manipulating device, or both to perturb the purge-air flow entering the combustor can for controlling combustion dynamics.

Abstract: 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.

Abstract: A combustion dynamics control system for an aviation based or land based gas turbine engine employs an acoustic driver that is configured to drive pressure perturbations across a premixed fuel injection orifice to substantially zero in response to a control signal such that fuel flow perturbations across the fuel injection orifice are substantially zero.

Abstract: The present application provides a fuel nozzle system. The fuel nozzle system may include a pre-orifice for a first pressure drop, a captured response volume in communication with the pre-orifice, a post-orifice in communication with the captured response volume for a second pressure drop, and a secondary fuel passage downstream of the post-orifice for a third pressure drop. The second pressure drop is less than the first pressure drop and the third pressure drop is less than the second pressure drop.

Abstract: A combustor cap is cooperable with an impingement plate in a turbine fuel nozzle and includes a plurality of cap segments independently securable to the impingement plate. The plurality of cap segments are radially and tangentially movable relative to the impingement plate.

Abstract: 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.

Abstract: A system comprises a gas turbine combustor having a plurality of combustor cans, crossfire tubes for connecting combustor cans, and a tubular connection system connecting the combustor cans to control combustion dynamics. The tubular connection system comprises tubes for connecting at least a pair of the combustor cans.

Abstract: A combustor minimizes combustion emissions at a lower level of combustion dynamics during combustor even fuel-split conditions by varying the fuel impedance through geometrical changes or inert addition in various nozzle groups than that achievable during combustor even fuel-split conditions with a multi-fuel nozzle combustor using a nozzle fuel impedance that is common to all nozzles while emitting substantially the same level of combustion emissions.

Abstract: In one embodiment, a system includes a variable geometry resonator configured to couple to a fluid path upstream from a combustor of a turbine engine. The variable geometry resonator is configured to dampen pressure oscillations in the fluid path and the combustor.

Abstract: A gas turbine engine control system comprises a data acquisition and analysis system for receiving a signal from a combustion dynamics sensor and providing an output signal and a combustion dynamics control system for controlling combustion dynamics based on the output signal. The control system is associated with a purge-air flow and comprises an acoustic driver, or a flow-manipulating device, or both to perturb the purge-air flow entering the combustor can for controlling combustion dynamics.