The damper arrangement include two concentric hollow shapes, each having a wall, wherein the walls form an annular volume therebetween. The damper arrangement further includes one or more necks for connecting to a combustion chamber at corresponding one or more contact points. The one or more necks are connected to the annular volume.

Heat-exchange and noise-reduction panel for a propulsion assembly, in particular for an aircraft, the panel comprising: a perforated plate comprising a plurality of through-openings; a cellular structure comprising longitudinally oriented structural walls covered by said perforated plate and comprising, between said walls, cavities that define Helmholtz resonators, said through-openings forming necks of said resonators; and means for the circulation of fluid, for example oil, at said perforated plate, wherein said fluid circulation means comprise channels that are formed at least in part in thickened ends of said walls on the same side as said perforated plate, and/or at least in part in regions of the perforated plate situated in the longitudinal extension of said thickened ends.

A burner arrangement having a combustion chamber, a multiplicity of mixing ducts discharging into the combustion chamber, in which ducts combustion air and fuel introduced during proper operation are mixed, and at least one resonator which has a defined resonator volume and resonator openings. The mixing ducts have mixing tubes which extend axially through an annular space defined between a tubular outer wall, a tubular inner wall arranged with the radial separation from the outer wall, an annular end plate arranged upstream and an annular end plate arranged downstream, wherein the end plates are provided with through openings which receive and/or prolong the mixing tubes. The resonator openings of the at least one resonator are designed as air ducts that extend through the downstream end plate, and the resonator volume of the at least one resonator is formed by at least one part of the annular space.

An apparatus for dampening acoustic pressure oscillations of a gas flow contained in part by a combustor wall of a gas turbine engine combustor. The apparatus includes at least one resonating tube with a closed end, an open end, and a cavity therebetween. The cavity is in fluid communication with an interior of the combustor such that the gas flow may flow into and out of the cavity. The apparatus further includes a perforated plate positioned at the open end and including a plurality of apertures. The gas flow flowing into and out of the cavity travels through the apertures.

A gas turbine combustor provided with: a combustion cylinder having a combustion chamber and a plurality of through-holes that open to the combustion chamber; a housing disposed peripherally outwards of the combustion cylinder and defining an acoustic attenuation space that communicates with the combustion chamber via the through-holes; an air hole plate having a plurality of air holes and being positioned upstream of the combustion cylinder; a plurality of fuel nozzles respectively corresponding to the air holes; an air passage provided between the inner peripheral surface of the combustion cylinder and the outer peripheral surface of the air hole plate and extending in the axial direction of the combustion cylinder; and an air supply flow path for supplying air flowing outside the combustion cylinder to the acoustic attenuation space. At least one of the through holes is provided directly below the air hole plate in the axial direction.

The present disclosure generally relates to the introduction of a liquid biomass in heating systems such as commercial boilers in order to reduce dependence on petroleum-based heating fuel oils as a source of combustion fuel. More specifically, the present disclosure is directed to systems, methods, and apparatuses utilizing a liquid thermally produced from biomass into commercial and industrial boiler or thermal systems such as boilers, furnaces, and kilns, and methods for generating renewable identification numbers (RINs), alternative energy credits (AECs) and renewable energy credits (RECs).

The present disclosure is directed to a burner assembly for generating a heat source. The burner assembly may include a combustion plate having a first surface and a second surface. The combustion plate may include a first plurality of holes extending from the first surface to the second surface arranged in a first circle and a second plurality of holes extending from the first surface to the second surface arranged in a second circle. The first circle and second circle may be arranged in concentric circles. The burner assembly may further be configured to have at least one of the holes having a longitudinal axis extending at a first acute angle from a plane of the combustion plate. The burner assembly may further be configured to have at least one of the holes having the longitudinal axis extending at a second acute angle from a tangent line of one of the concentric circles on the plane of the combustion plate.

The invention relates to a damping device for a gas turbine combustor with significantly reduced cooling air mass flow requirements. The damping device includes a wall with a first inner wall and a second outer wall, arranged in a distance to each other. The inner wall is subjected to high temperatures on a side with a hot gas flow. A plurality of cooling channels extend essentially parallel between the first inner wall and the second outer wall, and at least one damping volume bordered by cooling channels. Furthermore, the damping device includes a first passage for supplying a cooling medium from a cooling channel into the damping volume and a second passage for connecting the damping volume to the combustion chamber. An end plate, fixed to the inner wall, separates the damping volume from the combustion chamber.

A gas turbine engine combustion system including a mixing duct that separates into at least two branch passages for the delivery of a fuel and working fluid to distinct locations within a combustion chamber. The residence time for the fuel and working fluid within each of the two branch passages is distinct.

A hydrogen chloride loop fuel reaction is designed and configured for turbine/generator combination which can be used for automotive propulsion or as a standalone electrical generation or for auxiliary equipment. A method for providing a hydrogen chloride loop fuel reaction includes creating hydrogen chloride fuel in a sealed furnace vessel, wherein at start up, the sealed furnace vessel is vacuumed out and hydrogen and chlorine are injected into a burner and ignited resulting in the hydrogen chloride fuel in an exhaust stream of the sealed furnace vessel; and looping the hydrogen chloride fuel leaving the sealed furnace vessel in the exhaust stream of the sealed furnace vessel.