Provided is a heating device exhaust gas arrangement with an integrated sound suppressor, having: a rigid exhaust gas pipe (1) which is made by bending and longitudinally welding a perforated metal sheet and which has an un-perforated, curved first pipe section (2), an un-perforated second pipe section (3) and, formed integrally with the first pipe section (2) and the second pipe section (3), a perforated sound suppressor section (4) between the first pipe section (2) and the second pipe section (3), and a sound suppressor housing (5) which externally covers the perforated sound suppressor section (4) and which is arranged such that the first pipe section (2) and the second pipe section (3) both extend at least predominantly outside the sound suppressor housing (5).

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.

Disclosed is a heat storage type waste gas purification apparatus which comprises: a combustion chamber configured to combust and decompose a component contained in waste gas; a plurality of heat storage chambers each having one end communicating with the combustion chamber and each comprising a heat storage body; a plurality of supply inlets each equipped with an on-off valve and each provided at the other end of a respective one of the heat storage chambers to selectively supply waste gas thereto; a plurality of discharge outlets each equipped with an on-off valve and each provided at the other end of a respective one of the heat storage chambers to selectively discharge treated waste gas therefrom; a discharge passage connected to the discharge outlets to discharge the treated waste gas to an outside of the apparatus therethrough; a plurality of bypass passages each connecting between the combustion chamber and the discharge passage, wherein each of the bypass passages is connected to the combustion chamber at a position directly above a respective one of the heat storage chambers, and equipped with an on-off valve; and a control section operable, when a temperature of one of the heat storage chambers becomes equal to or greater than a given value, to open one or more of the on-off valves of the bypass passages so as to discharge a part of waste gas in the combustion chamber via the opened one or more bypass passages.

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.

In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system 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 one or more resonator chambers (18) that provide enhanced cooling with reduced risk of cracking and other damage. The resonator housing (18) may include resonator exhaust orifices (26) that are positioned closer to an area of maximum temperature within the combustor (12), thereby enabling the resonator (16) to reduce the temperature gradient within the combustor (12). The resonator housing (18) may be sized and configured to reduce stress found in conventional systems by increasing distances between resonator exhaust orifices (26) and between resonator inlet impingement orifices (30), among others.

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.

A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.

The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

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: $\begin{array}{cc}0.9\times {.Math.}_{i=1}^n\frac{F_i}{n}\le F_i\le 1.1\times {.Math.}_{i=1}^n\frac{F_i}{n}& \left(A\right)\end{array}$
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.