A resonant sound absorbing device of a gas turbine combustor includes a plurality of resonance chambers independently disposed side by side in an axial direction of the gas turbine combustor so as to communicate with a gas passage of the gas turbine combustor via acoustic holes. The plurality of resonance chambers include n related resonance chambers each satisfying:

[00001]$\begin{array}{cc}0.9{.Math.}_{i=1}^n.Math.\frac{F_i}{n}{F}_{i}1.1{.Math.}_{i=1}^n.Math.\frac{F_i}{n}& \left(A\right)\end{array}$

where n is an integer of 2 or more, and Fi is a peak frequency corresponding to a maximum sound absorbing ratio of the ith related resonance chamber of the n related resonance chambers.

Disclosed is a baffle for a mixing region of a furnace burner box, the mixing region being a volume in the burner box defined in a transverse direction between a burner at a front portion of the burner box and an opposing a rear portion of the burner box, a longitudinal direction between opposing side surfaces of the burner box, and a height-wise direction between opposing top and bottom surfaces of the burner box, the baffle having: a first side which is a rear side, a second side which is a front side, the first side and the second side being spaced in the transverse direction, and wherein the baffle defines an indirect fluid passageway between the first side and the second side.

A combustor includes fuel nozzles that extend in an axial direction of a combustor main body and are capable of injecting fuel from injection holes on a combustion chamber side. The combustor includes a phase adjusting unit which partially changes a flow path cross-sectional area of at least one of the fuel nozzles in the axial direction such that phases of flow rate fluctuation of fuel do not match with respect to at least two of the fuel nozzles.

An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include resonator chambers (26) that may be welded in place within resonator chamber (26) receivers (24) but easily replaceable without exposing the resonator housing (18) to damage. In another embodiment, an inner surface (32) of the resonator chamber (26) may be offset radially outward from an inner surface (34) of the resonator housing (18), thereby creating a flow-path discontinuity and reducing heating of the resonator chamber (26). The acoustic damping resonator system (14) may mitigate dynamics thereby increasing an engine operating envelope and decreasing emissions.

A sequential combustor arrangement and method are disclosed which can include a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer can include at least one injection opening in the mixer wall for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber. Further, the mixer can include a damper with a damper volume and a neck connecting the damper volume to the mixer, for modulating and damping pressure pulsations inside the mixer.

A combustor arrangement of a gas turbine engine or power plant is disclosed, having at least one combustion chamber, at least one mixer arrangement for admixing air or gas to the hot gas flow leaving the combustion chamber. The mixer arrangement is configured to guide combustion gases in a hot gas flow path extending downstream of the combustion chamber, wherein the mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer arrangement for admixing air portions to cool at least the hot gas flow leaving combustion chamber. The mixer arrangement is applied to at least one volume of dilution air flowing from a first plenum and at least one volume of cooling air flowing from a second plenum.

A system for attenuating acoustic energy in machines is provided. The system may include an inner tube disposed about a central axis, an outer tube disposed about the inner tube and the central axis, and a middle tube disposed about the central axis and between the inner tube and the outer tube. The system may also include a first annular ring extending radially from the outer tube and configured to couple the outer tube to the middle tube. The system may further include a second annular ring extending radially from the inner tube and configured to couple the inner tube to the outer tube, such that an acoustic resonator may be formed by the first annular ring, the second annular ring, a portion of the inner tube, a portion of the outer tube, and a portion of the middle tube.

An integrated combustor-thermoelectric generator and method for producing electrical power and/or for operating a pneumatic or electric device. The apparatus includes a burner tube, a tubular heat exchanger extending along and around the burner tube, a plurality of thermoelectric generators disposed along sides of the heat exchanger, and a heat sink on an opposite side of the thermoelectric generators from the burner and heat exchanger. The thermoelectric generators can be paired with an electric valve or a DC air compressor for operating a pneumatic device by directing heated gases from the combustor through the heat exchanger to thermoelectric couples and/or modules for powering the air compressor. The thermoelectric generator and DC compressor can be installed to a natural gas source at a well pad for operating a pneumatic device at the well pad.

An integrated combustor-thermoelectric generator and method for producing electrical power and/or for operating a pneumatic or electric device. The apparatus includes a burner tube, a tubular heat exchanger extending along and around the burner tube, a plurality of thermoelectric generators disposed along sides of the heat exchanger, and a heat sink on an opposite side of the thermoelectric generators from the burner and heat exchanger. The thermoelectric generators can be paired with an electric valve or a DC air compressor for operating a pneumatic device by directing heated gases from the combustor through the heat exchanger to thermoelectric couples and/or modules for powering the air compressor. The thermoelectric generator and DC compressor can be installed to a natural gas source at a well pad for operating a pneumatic device at the well pad.

A vascular wall of a combustor that may be for a gas turbine engine includes a first face defining at least in-part a combustion chamber, a second face defining at least in-part a cooling air plenum, and a vascular lattice structure located between the first and second faces for distributing cooling air from the plenum and to the chamber. The vascular lattice structure may be configured to enhance cooling air flow where needed whiling providing structural support. The orientation of the vascular lattice structure may further contribute toward acoustic dampening.