Abstract: An engine injector assembly for introducing a gaseous fuel, a liquid fuel and air into a combustion chamber, has a stem and main body oriented along an axis. The main body includes: a central air duct on the axis, having an outlet for directing a central air flow, an outer air duct running radially outside around the central air duct, having an outlet for directing an external air flow, a liquid fuel supply radially between the central and outer air ducts, having a liquid fuel duct and an outlet for introducing the liquid fuel, and a gas fuel supply radially between the liquid fuel supply and the outer air duct, having a gas fuel duct and an outlet for introducing the gaseous fuel. The outer air duct has, at its downstream end, a radially outwardly oriented end portion for directing radially outward the outer air flow.

Abstract: A combustion chamber for a gas turbine is in annularly encircling form, having an outer wall and an inner wall arranged on a longitudinal axis extending therebetween. A front plate extends on an inlet side between the outer and inner walls, orthogonally to the axis. The outer and inner walls and the front plate delimit an annularly encircling combustion space. The combustion space extends over a length from an injector-side inlet side, with an inlet-side height, to a downstream outlet opening, with an outlet-side height. An optimized emission characteristic during operation is achievable in that, in a longitudinal section through the combustion chamber, the outer wall and/or the inner wall extend(s) to approach the longitudinal axis in a continuous and strictly monotonic manner in the flow direction, wherein the approach is configured to be steeper on the inlet side than on the outlet side.

Abstract: The proposed solution relates to a nozzle assembly for a combustor of an engine, having at least one nozzle for injecting hydrogen into a combustion chamber of the combustor, wherein the nozzle has a nozzle main body which extends along a nozzle longitudinal axis and a nozzle head at one end of the nozzle main body and comprises a first air conduit, a fuel duct for the hydrogen to be injected, and a second air conduit. The fuel duct is arranged with a fuel exit opening for the hydrogen to be injected into the combustion chamber between the first and second air conduits with their first and second air exit openings, in relation to a radial direction running perpendicularly to the nozzle longitudinal axis.

Abstract: The invention relates to an injector assembly for a gas turbine, in particular an engine of an aircraft, for introducing a gaseous fuel and a liquid fuel, and also air, into a combustion chamber, having an injector shaft and an injector main body oriented along an injector longitudinal axis, wherein the injector main body includes: a first gas duct, which is arranged centrally on the injector longitudinal axis and has a downstream outlet opening, for introducing a gas flow, at least one air duct arranged in radially outwardly encircling fashion around the first gas duct, as second gas duct, and a liquid fuel injection means, which is arranged radially around the first gas duct, for introducing the liquid fuel into the combustion chamber. An advantageous emission characteristic can be achieved by the first gas duct being designed exclusively to introduce the gaseous fuel into the combustion chamber.

Abstract: An engine injector assembly for introducing a gaseous fuel, a liquid fuel and air into a combustion chamber, has a stem and main body oriented along an axis. The main body includes: a central air duct on the axis, having an outlet for directing a central air flow, an outer air duct running radially outside around the central air duct, having an outlet for directing an external air flow, a liquid fuel supply radially between the central and outer air ducts, having a liquid fuel duct and an outlet for introducing the liquid fuel, and a gas fuel supply radially between the liquid fuel supply and the outer air duct, having a gas fuel duct and an outlet for introducing the gaseous fuel. The outer air duct has, at its downstream end, a radially outwardly oriented end portion for directing radially outward the outer air flow.

Abstract: The proposed solution relates to a nozzle assembly for a combustor of an engine, having at least one nozzle for injecting hydrogen into a combustion chamber of the combustor, wherein the nozzle has a nozzle main body which extends along a nozzle longitudinal axis and a nozzle head at one end of the nozzle main body and comprises a first air conduit, a fuel duct for the hydrogen to be injected, and a second air conduit. The fuel duct is arranged with a fuel exit opening for the hydrogen to be injected into the combustion chamber between the first and second air conduits with their first and second air exit openings, in relation to a radial direction running perpendicularly to the nozzle longitudinal axis.

Abstract: The invention relates to a nozzle assembly for a combustor (103) of an engine (T), comprising at least one nozzle (D) for injecting fuel into a combustion chamber (1030) of the combustor (103), wherein the nozzle (D) comprises a nozzle main body (DR) extending along a nozzle longitudinal axis (L) and having a nozzle head (DK), and a nozzle holder (DH) connected to the nozzle main body (DR) and having at least one fuel supply line (1). The nozzle main body (DR) comprises a central fuel pipe (3) extending along the nozzle longitudinal axis (L) and at least two radially spaced-apart air guide channels (4, 5) on the nozzle head with a respective at least one air outlet opening.

Abstract: A combustion chamber assembly group includes a nozzle providing a fuel-air mixture at a nozzle exit opening. An end of a fuel guiding channel is bordered at the nozzle exit opening by a flow-off edge located radially outside, and an air guiding element of an air guiding channel of the nozzle located radially outside projects with respect to this flow-off edge in the axial direction with respect to a nozzle longitudinal axis such that: a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and tangentially to the axially projecting air guiding element, and/or a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and a point of the air guiding element that projects maximally beyond the flow-off edge in the axial direction is ?50°.

Abstract: The present invention relates to a nozzle for a combustion chamber (3) of an engine (T) for providing a fuel-air mixture at a nozzle exit opening of the nozzle (2). According to the invention, an extension (5) for guiding the fuel-air mixture extending in the axial direction with respect to a nozzle longitudinal axis (DM) is provided at an air guide element (271b) of a radially outwardly located air channel (27b) of the nozzle (2).

Abstract: A combustion chamber assembly group includes a burner seal with a bearing section that extends along a longitudinal axis and has a passage hole for positioning a fuel nozzle at a combustion chamber of an engine, and a heat shield which, when mounted according to the intended use at the combustion chamber of the engine, is located inside the combustion space of the combustion chamber and has a passage hole through which the bearing section of the burner seal extends. The burner seal that is manufactured in an additive manner and the heat shield form a constructional unit in which the heat shield is received at least partially between a radially outwardly pointing opening edge of the burner seal and a radially outwardly extending web of the burner seal, so that any separation of the heat shield from the burner seal along the longitudinal axis is excluded.

Abstract: A combustion chamber assembly group includes a nozzle providing a fuel-air mixture at a nozzle exit opening. An end of a fuel guiding channel is bordered at the nozzle exit opening by a flow-off edge located radially outside, and an air guiding element of an air guiding channel of the nozzle located radially outside projects with respect to this flow-off edge in the axial direction with respect to a nozzle longitudinal axis such that: a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and tangentially to the axially projecting air guiding element, and/or a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and a point of the air guiding element that projects maximally beyond the flow-off edge in the axial direction is ?50°.