An injector device for an engine device for introducing a fluidic, in particular a liquid, fuel and a fluid, in particular liquid, oxidizing agent into a combustion chamber of the engine device is provided. The injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber. At least one first resonator element is associated with the at least one first injection element and/or at least one second resonator element is associated with the at least one second injection element.

A fluid manifold assembly for a gas turbine engine, the fluid manifold assembly including a walled conduit assembly defining a fluid passage therewithin. The fluid passage defines a pair of ends separated by a length. A connecting conduit is coupled to the end of the fluid passage and to the length of the fluid passage.

A combustor component according to at least one embodiment of the present invention includes a cylindrical body which internally includes a combustion chamber, and includes a weld part where a plurality of through holes opening to the combustion chamber are formed, and a housing which is disposed on an outer circumferential side of the cylindrical body to cover a part of the weld part, and defines an acoustic damping space communicating with the combustion chamber via at least one of the through holes. The plurality of through holes in the weld part has a formation density which is higher in a first region of the weld part covered with the housing than in a second region of the weld part positioned outside the housing.

A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.

A rotor shaft cap for a gas turbine has a disk-shaped body defining a first axial face, a second axial face, and an outer radial face. The disk-shaped body has a first annular jaw provided on the first axial face. The first annular jaw includes a plurality of teeth projecting from the first axial face. A plurality of apertures are defined by the disk-shaped body, each aperture of the plurality of apertures extends through the disk-shaped body along an axial direction.

Turbomachines and methods of operating turbomachines are provided. The turbomachine may include a compressor, a turbine, and a plurality of combustors downstream from the compressor and upstream from the turbine. The turbomachine may also include a plurality of igniters. Methods of operating a turbomachine may include rotating a shaft of the turbomachine at a first speed and rotating the shaft of the turbomachine at a second speed different from the first speed after rotating the shaft of the turbomachine at the first speed. The methods may also include firing at least one igniter of the plurality of igniters repeatedly throughout the period of time at a regular interval and/or when the rotational speed reaches at least one predetermined speed threshold during the period of time.

Methods and systems for resonance suppression, can involve measuring signals with one or more sensors, wherein the signals are produced by a combustor associated with an actuator, and receiving at a controller the signals measured by the sensor or sensors. The controller can calculate a damping rate of the combustor. Based on the damping rate, the controller can modulate the actuator if the damping rate falls below a predefined threshold and can continue to modulate the actuator until the damping rate is adjusted and the resonance is suppressed. The sensor can be an acoustic sensor, an optical sensor, or another type of sensor.

A gas turbine combustor includes a burner composed of a fuel nozzle group having a plurality of fuel nozzles for fuel supply, a fuel nozzle plate structurally supporting the fuel nozzles and serving to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate located downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle group includes outer circumferential fuel nozzles and inner circumferential fuel nozzles. Each outer diameter of at least a proximal end of the outer circumferential fuel nozzles is larger than that of the inner circumferential fuel nozzles.

A mixer assembly group for a turbofan engine, having a primary flow channel extending along a central axis of the turbofan engine and a secondary flow channel. The mixer assembly group includes a mixer for guiding a first fluid flow from the primary flow channel and a second fluid flow from the secondary flow channel in the direction of an exhaust of the turbofan engine, as well as for intermixing the first and second fluid flows, and a connection appliance, which has at least one connection component that is fixated at the mixer and by means of which the mixer assembly group is to be fixated at two different first and second engine components of the turbofan engine, with are subject to operating temperatures of different heights during operation of the turbofan engine.

A system for early detection of onset of oscillatory instabilities in practical devices is described. The system consists of a measuring device (102), an instability detection unit (104) and a control unit (106). The measuring device (102) is configured to generate signals corresponding to the dynamics happening inside the practical device. The instability detection unit (104) along with an amplitude estimation unit (130) is configured to diagnose the stability of the practical device from the signals that are generated by the measuring device (102). Further, the control unit (106) is configured to control various operating parameters in the practical device based on the information obtained from the instability detection unit (104).