A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

The present disclosure relates to apparatuses and methods that are useful for one or more aspects of a power production plant. More particularly, the disclosure relates to combustor apparatuses and methods for a combustor adapted to utilize different fuel mixtures derived from gasification of a solid fuel. Combustion of the different fuel mixtures within the combustor can be facilitated by arranging elements of the combustor controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel mixtures.

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.

A combustor includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure, and a plurality of inner planks mounted to the inner mesh structure. The outer liner includes an outer mesh structure, and a plurality of outer planks mounted to the outer mesh structure. Each of the plurality of inner planks and outer planks includes an inner wall, an outer wall, and lateral walls defining a cavity to allow circulation of airflow within the cavity to cool down the inner wall.

The present disclosure relates to apparatuses and methods that are useful for one or more aspects of a power production plant. More particularly, the disclosure relates to combustor apparatuses and methods for a combustor adapted to utilize different fuel mixtures derived from gasification of a solid fuel. Combustion of the different fuel mixtures within the combustor can be facilitated by arranging elements of the combustor controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel mixtures.

A combustion chamber assembly for an engine includes a wall element fixed to a combustion chamber structure and a chamber between the wall element and the structure, the chamber being supplied with air through impingement-cooling openings in the structure and connected to the combustion space by film-cooling openings in the wall element. Two cooling-air holes formed in the structure generate a cooling-air flow toward the combustion space and past the wall element. The wall element has a flow guide device for generating at least one scavenging-air flow directed between the two cooling-air holes. A sum of flow cross sections of film-cooling openings in the wall element and of the flow guide device yields a larger area than a sum of flow cross sections of all wall element impingement-cooling openings via which air is guided through the structure into the chamber and to the rear side of the wall element.

An air swirler arrangement comprises a coaxial arrangement of an inner and an outer air swirler passage. Each air swirler passage comprises a radial flow swirler. Air swirler arrangement comprises a coaxial arrangement of first, second and third members. Second member has radially extending upstream portion spaced axially from first member and a convergent portion. Third member has a radially extending upstream portion spaced axially from the upstream portion of second member and a radially inner surface having convergent and divergent downstream portions and a radially outer surface having a divergent downstream portion. First, second and third members the vanes of the radial flow swirlers is a monolithic structure. Plurality of circumferentially spaced passages are provided within the third member and each passage has an inlet in the surface and an outlet arranged to direct fluid onto the divergent portion of the surface or the surface of the third member.

A heat shield panel for a combustor of a gas turbine engine including a panel body having a first surface and a second surface. The second surface being configured to be oriented toward a combustor liner of the combustor. The heat shield further includes a plurality of first pin fins projecting from the second surface of the panel body. Each of the plurality of first pin fins has a rounded top opposite the second surface. The heat shield further includes a plurality of second pin fins projecting from the second surface of the panel body. Each of the plurality of second pin fins has a flat top opposite the second surface. The plurality of second pin fins are intermittently spaced amongst the plurality of first pin fins. The plurality of second pin fins are organized in a uniform distribution across the second surface of the heat shield panel.

A vehicle heater housing (46) has an inlet area (49), an outlet area (51) and an air flow space (47) for air to be heated with a burner chamber assembly unit (30), to be fed with combustion air and fuel. A heat exchanger area (11), including a heat exchanger housing (12), is elongated in the direction of a housing longitudinal axis (L) with an outer side (24) around which air flowing in the air flow space flows. Heat transfer ribs are on a side of the heat exchanger housing. The heater housing has a housing circumferential wall (56) and an outlet front wall area (58). The heat transfer ribs have a longitudinal edge (64) extending along the housing circumferential wall and a radial edge extending along the outlet front wall area. A distance of the radial edge from the outlet front wall area changes from radially outwards to radially inwards.

A combustor having an outer stack placed around a fire tube of the combustor to direct cooler air upwards to envelop an exhaust plume from the fire tube as an air shield or curtain barrier to prevent fugitive gases coming into contact with the exhaust plume and auto-igniting.