The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck. With the solution of the present invention, as a damper according to embodiments of the present invention operates, flow field hence damping characteristic in the second cavity constant regardless the adjustment of the spacer plate in the enclosure.

The gas turbine engine includes a fluid system fluidly connecting at least two components of the gas turbine engine, and a tunable resonator in fluid flow communication with the fluid system. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.

A burner device (190) comprising an air intake, a burner head (192) including an ignition device, a body section (196) defining a fluid flow channel between said air intake and said burner head (192), and a gas injector (205) for injecting combustible gas into said fluid flow channel. The burner head (192) is oriented such that its longitudinal axis is substantially perpendicular to the plane in which the channel is defined and in which fluid flows, in use, along said channel.

The present invention generally relates to a gas turbine and more in particular it is related to a damper assembly for a combustion chamber of a gas turbine. According to preferred embodiments, the present solution provides a damper assembly including protrusions on a wall of the neck. These protrusions result in a side wall reactance to the acoustic field that has the effect of decreasing the effective speed of sound in the neck. The decrease of the effective speed of sound in the neck is equivalent to an increase of the effective neck length.

A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.

An acoustic damping device is provided that includes a resonating tube defining a resonating cavity with a predetermined characteristic length and a tube end defining a cavity opening, as well as a case configured to reversibly secure the tube end in fluidic communication with a fluid volume enclosed by a liner. The cavity opening is connected with the resonating cavity. The case includes a vented ferrule adpressed over a perforated region of the liner. The vented ferrule defines a ferrule opening that is aligned with the perforated region of the liner and the cavity opening to form the fluidic communication between the fluid volume and the resonating cavity.

In a burner in which fuel and gaseous oxidant are fed into the burner and combusted to produce a flame that extends out of an end of the burner, the noise produced by the burner is lessened by incorporating into the burner a baffle composed of a metal plate having a certain distribution of holes through the plate and a layer of metal filaments, and optionally a second metal plate.

The gas turbine engine including, in serial flow communication, a compressor, a combustor, a turbine, and a fluid system fluidly connecting at least two components of the gas turbine engine, also includes a tunable resonator in fluid flow communication with the fluid system, the tunable resonator. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.

A combustor and a rocket engine include an injection device that injects an oxidizing agent and fuel from an injecting surface, a combustion chamber that generates combustion gas by burning the oxidizing agent and the fuel injected from the injection device, a resonator communicatively connected with the combustion chamber via a communication passage, and a perforated plate provided in the communication passage.

Disclosed herein is a combustion oscillation estimating apparatus which estimates combustion oscillation in a combustion chamber connected with a burner so that a flame is injected by the burner, the combustion oscillation estimating apparatus including an input unit which receives data including an inlet pressure of the burner, and a control unit which detects a pressure in the combustion chamber based on a shape from the burner to the combustion chamber, a temperature distribution in the combustion chamber, and a shape of the flame. The combustion oscillation estimating apparatus may improve estimation accuracy of the combustion oscillation in the combustion chamber.