An air intake coupling has at least one noise suppression hole formed therein. A gas-air mixer elbow is fluidly coupled to the air intake coupling. A burner box assembly is fluidly coupled to the gas-air mixer elbow via a gas-air plenum box. A heat-exchange tube has a first end that is fluidly coupled to the burner box assembly. A fan is fluidly coupled to a second end of the heat-exchange tube via a cold-end header box.

An air intake coupling has at least one noise suppression hole formed therein. A gas-air mixer elbow is fluidly coupled to the air intake coupling. A burner box assembly is fluidly coupled to the gas-air mixer elbow via a gas-air plenum box. A heat-exchange tube has a first end that is fluidly coupled to the burner box assembly. A fan is fluidly coupled to a second end of the heat-exchange tube via a cold-end header box.

The invention relates to the field of power engineering and can be used in heating systems, more particularly in water heaters or boilers, in disposal systems fueled by the combustion of associated gas, and in electrical energy generating systems. A pulse combustion apparatus comprises a combustion chamber 14, at least one resonant channel 28 connected to the combustion chamber 14, a device 15 for removing heat which is linked to the combustion chamber and to the resonant channel and which consists of at least one chamber and/or at least one tube for a heat-exchanging agent 16. A device for supplying air and combustible gas, which is connected to the combustion chamber 14, comprises at least one gaseous medium nonreturn valve 17 and at least one guard chamber 18 of said valve 17. The at least one gaseous medium nonreturn valve 17 is directly or indirectly linked to the device 15 for removing heat via a vibration isolator 19, 24.

An acoustic liner includes a first face sheet, a second face sheet spaced from the first face sheet, and a plurality of sidewalls extending between the first face sheet and the second face sheet. The plurality of sidewalls defines a plurality of cells. Each cell of the plurality of cells defines a cavity between the first face sheet and the second face sheet. A bulk absorber is disposed within at least one cell of the plurality of cells. The bulk absorber further defines the cavity of the at least one cell of the plurality of cells. The first face sheet defines a plurality of apertures extending through a thickness of the first face sheet. Each aperture of the plurality of apertures is aligned with a respective cell of the plurality of cells.

A method for operating a gas turbine engine includes receiving data indicative of an operational vibration within a section of the gas turbine engine; and providing electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.

A method for operating a gas turbine engine includes receiving data indicative of an operational vibration within a section of the gas turbine engine; and providing electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.

An acoustic liner includes a first face sheet, a second face sheet spaced from the first face sheet, and a plurality of sidewalls extending between the first face sheet and the second face sheet. The plurality of sidewalls defines a plurality of cells. Each cell of the plurality of cells defines a cavity between the first face sheet and the second face sheet. A bulk absorber is disposed within at least one cell of the plurality of cells. The bulk absorber further defines the cavity of the at least one cell of the plurality of cells. The first face sheet defines a plurality of apertures extending through a thickness of the first face sheet. Each aperture of the plurality of apertures is aligned with a respective cell of the plurality of cells.

A gas turbine engine may include a combustion section having a fuel nozzle, a swirler, and a ferrule configured to mount and center the fuel nozzle with the swirler. The combustion section may further include a damper on a cold side of the combustion section. The damper may have an acoustic cavity, a damper neck, and a cavity feed hole. The damper may operate as Helmholtz cavity to absorb a hydrodynamic or acoustic instability present in a region within the swirler.

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.

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.