Abstract: An injector assembly for a gas turbine for introducing a gaseous fuel, liquid fuel and air into a combustion chamber, includes an injector shaft and an injector main body aligned along an injector longitudinal axis. The injector main body includes a first gas duct arranged centrally on the injector longitudinal axis, for introducing a gas flow into the combustion chamber; an air duct arranged radially around the outside of the first gas duct, and a liquid fuel injection arranged radially around the first gas duct for introducing the liquid fuel into the combustion chamber. The injector assembly introduces the gaseous fuel. The injector assembly is switchable between two configurations during operation: in a first configuration, air flows through the first gas duct, as an air injection; in a second configuration, the gaseous fuel flows through, as a gas fuel injection.

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: A nozzle for feeding air and liquid fuel into a combustion chamber, has a nozzle main body aligned along an axis, and includes a first air duct running on and/or around the axis, a fuel duct, annularly encircling the first air duct and having a downstream end portion running axially-radially in a direction of the axis in a flow direction, and a second air duct, annularly encircling the fuel duct. The fuel duct has a fuel outlet opening at an adjoining substantially axially aligned film applicator surface having a downstream trailing edge, wherein the film applicator surface surrounds the first air duct at the downstream end. Fuel atomization is improved by a length of the film applicator surface between the fuel outlet opening and the trailing edge being between a factor of 5-6 times a height of the end portion of the fuel duct.

Abstract: A pilot arrangement for use in a nozzle device of a gas turbine includes a cavity, extending along a longitudinal axis, for conducting fuel, the narrowest flow cross section of which is larger than the largest flow cross section of a pilot line of a pilot fuel nozzle. The pilot fuel nozzle, adjoining the cavity in a downstream direction includes the pilot line and a pilot fuel outlet arranged at the downstream end of the pilot line. The cavity is arranged in a central body arranged on the axis, and at least one swirling element is arranged circumferentially around the central body. The central body and the swirling element form a swirling arrangement. Manufacturing advantages are achieved in that the pilot arrangement is made up of two components, wherein a first component includes the swirling element and the central body, and a second component includes the pilot fuel nozzle.

Abstract: The invention relates to a nozzle assembly for a combustor of an engine, including at least one nozzle for injecting fuel 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 holder connected to the nozzle main body and having at least one fuel supply line. The nozzle main body comprises a central fuel pipe extending along the nozzle longitudinal axis and sealed against an in-flow of air, in which fuel supplied via the at least one fuel supply line can be guided within the nozzle main body up to a fuel outlet opening of the fuel pipe provided at a nozzle end of the nozzle, via which the fuel can be introduced into the combustion chamber.

Abstract: The invention concerns a combustion chamber assembly, in particular for use in an aircraft engine, including: a peripheral wall which borders a combustion space oriented along a longitudinal axis, and at least one, preferably a plurality of fuel nozzle(s) arranged on the input side of the combustion space for the supply of liquid fuel to the combustion space. An alternative and/or combined optimised operation with fuels of different aggregate states can be achieved with comparatively low structural complexity in that the combustion chamber assembly is configured for operation with liquid and/or gaseous fuel, wherein at least one, preferably a plurality of gas supply openings arranged downstream of the fuel nozzle(s) on the peripheral wall is/are present, by means of which gaseous fuel can be introduced into the combustion space.

Abstract: A combustion chamber assembly for an engine includes a combustion chamber defining a combustion space delineated by a combustion chamber wall and extending in a main flow direction from a combustion chamber head to a combustion chamber outlet. A fuel injection system is joined to the wall at the combustion chamber head and has a fuel feed for fuel and a nozzle head for injecting the fuel into the combustion space. The wall also has an integrated heat exchanger duct via which the fuel is routed within a first duct section of the heat exchanger duct which is connected to the fuel line from the combustion chamber head in the direction of the combustion chamber outlet and, after flowing through a deflection region, in a second duct section of the heat exchanger duct, back in the direction of the combustion chamber head and of the nozzle head.

Abstract: An injector assembly for a gas turbine for introducing a gaseous fuel, liquid fuel and air into a combustion chamber, includes an injector shaft and an injector main body aligned along an injector longitudinal axis. The injector main body includes a first gas duct arranged centrally on the injector longitudinal axis, for introducing a gas flow into the combustion chamber; an air duct arranged radially around the outside of the first gas duct, and a liquid fuel injection arranged radially around the first gas duct for introducing the liquid fuel into the combustion chamber. The injector assembly introduces the gaseous fuel. The injector assembly is switchable between two configurations during operation: in a first configuration, air flows through the first gas duct, as an air injection; in a second configuration, the gaseous fuel flows through, as a gas fuel injection.

Abstract: The invention relates to a method for operating an aircraft with a gaseous fuel, in particular hydrogen, and a liquid fuel, in particular a sustainable alternative fuel and/or kerosene, wherein the gaseous fuel and the liquid fuel are supplied in parallel or alternatively to each other to a combustion chamber of at least one engine of the aircraft. An optimized method with regard to efficiency and pollutant emissions is provided in that the aircraft is operated at least temporarily with a constant flow of gaseous fuel, while the liquid fuel flow is varied.

Abstract: A valve unit includes a in a housing which is subdivided, by an adjustable obturator in a fluid-tight manner in the valve space into first and second chambers separated from one another and through which fuel flows. The valve space has a first inlet for main fuel, a second inlet for pilot fuel, a first outlet for supplying fuel to an engine main stage, and a second outlet, for supplying fuel to an engine pilot stage. An elastic restoring element interacting with a fuel pressure difference between the chambers supplies an adjustment force, for positioning the obturator such that the obturator is adjustable into a closing position blocking the second outlet. The second chamber includes a further inlet for feeding a further fuel portion and a further outlet for discharging fuel from the second chamber and which remains open when the obturator is in the closing position.

Abstract: A nozzle assembly for a combustion chamber of an engine has a nozzle for injecting fuel into a combustion space of the combustion chamber. The nozzle includes a main body, extending along a nozzle longitudinal axis, a nozzle head, and a nozzle bracket, connected to the main body and having a fuel feed line. The main body includes a central fuel pipe, extending along the longitudinal axis and a fuel outlet opening, and at the nozzle head, at least one air-guiding duct, spaced apart radially from the fuel pipe, with an air outlet opening. The nozzle assembly has a burner seal for sealing with respect to a combustion chamber head, the burner seal formed separately from the main body. The air-guiding duct is formed in the burner seal.

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: The invention relates to a nozzle assembly for a combustor of an engine, including at least one nozzle for injecting fuel 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 holder connected to the nozzle main body and having at least one fuel supply line. The nozzle main body comprises a central fuel pipe extending along the nozzle longitudinal axis and sealed against an in-flow of air, in which fuel supplied via the at least one fuel supply line can be guided within the nozzle main body up to a fuel outlet opening of the fuel pipe provided at a nozzle end of the nozzle, via which the fuel can be introduced into the combustion chamber.

Abstract: A pilot arrangement for a nozzle of a gas turbine, in particular of an aircraft engine, including: a cavity extending along a longitudinal axis for conducting fuel, a narrowest flow cross section of which is larger than a flow cross section of a pilot fuel nozzle, in particular a pilot line. The pilot fuel nozzle, which adjoins the cavity in a downstream direction includes the pilot line and a pilot fuel outlet arranged at the downstream end of the pilot line, the narrowest flow cross section of which is configured to be smaller than that of the cavity. Reliable operation is made possible by virtue of an air opening arranged on the pilot arrangement in flow connection with the cavity so there can be an at least occasional flow of air through at least the cavity and the pilot fuel nozzle during the operation of the gas turbine.

Abstract: A drive system for an aircraft which is constructed for operation with a liquid fuel and a gaseous fuel, includes: at least one engine having a combustion chamber for operation with the liquid fuel and/or the gaseous fuel; and per fuel at least one separate tank chamber which is or can be brought into connection in flow terms with the combustion chamber via a fuel line for supplying it with the corresponding fuel. A drive system which is optimized in terms of emissions and efficiency is provided in that the drive system is constructed in such a manner that, in the event of firing at a great height, exclusively gaseous fuel is or can be used in the at least one engine during a firing operation at a great height.

Abstract: The invention relates to a fluid supply assembly having a line assembly from a fluid reservoir to a target location for supplying a fluid mass flow in a variable supply quantity, in particular for supplying fuel from a fuel reservoir to a combustion chamber, having a primary mass flow supplied or able to be supplied via a primary line and a secondary mass flow supplied or able to be supplied via a secondary line. An advantageous adaptation of the fluid mass flow, in particular fuel mass flow, to variable operating conditions is achieved in that disposed in the primary line and/or the secondary line is a passively operating restrictor which is invariable in its geometry and is without moving parts, by which the mass flow ratio of primary mass flow and secondary mass flow is altered as a function of the fluid mass flow supplied via the line assembly.

Abstract: A combustion chamber assembly for an engine includes a combustion chamber defining a combustion space delineated by a combustion chamber wall and extending in a main flow direction from a combustion chamber head to a combustion chamber outlet. A fuel injection system is joined to the wall at the combustion chamber head and has a fuel feed for fuel and a nozzle head for injecting the fuel into the combustion space. The wall also has an integrated heat exchanger duct via which the fuel is routed within a first duct section of the heat exchanger duct which is connected to the fuel line from the combustion chamber head in the direction of the combustion chamber outlet and, after flowing through a deflection region, in a second duct section of the heat exchanger duct, back in the direction of the combustion chamber head and of the nozzle head.

Abstract: The invention relates to a fluid supply assembly having a line assembly from a fluid reservoir to a target location for supplying a fluid mass flow in a variable supply quantity, in particular for supplying fuel from a fuel reservoir to a combustion chamber, having a primary mass flow supplied or able to be supplied via a primary line and a secondary mass flow supplied or able to be supplied via a secondary line. An advantageous adaptation of the fluid mass flow, in particular fuel mass flow, to variable operating conditions is achieved in that disposed in the primary line and/or the secondary line is a passively operating restrictor which is invariable in its geometry and is without moving parts, by which the mass flow ratio of primary mass flow and secondary mass flow is altered as a function of the fluid mass flow supplied via the line assembly.

Abstract: The proposed solution relates to a fuel nozzle for the injection of hydrogen into a combustion chamber of an engine, the fuel nozzle including, for provision of a hydrogen-air mixture, a nozzle head having outflow openings (19, 21) at an end face of the nozzle head. Multiple first outflow openings for hydrogen to be injected and at least one second outflow opening for air to be injected are present at the end face for the provision of the hydrogen-air mixture, where the at least one second outflow opening has a polygonal cross section and the multiple first outflow openings at the end face are arranged around the at least one second outflow opening.

Abstract: A connecting apparatus for fluid connection between a fuel feed line system and a nozzle apparatus of a gas turbine arrangement, includes a gas fuel line which is surrounded by a wall for conducting a gaseous fuel, and a liquid fuel line which is surrounded by a wall for conducting a liquid fuel. Optimized operation is achieved by the connecting apparatus having at least one separate gas line portion arranged on the inlet side of the gas fuel line and a gas/liquid line portion which is arranged downstream of the separate gas line portion and within which the gas fuel line and the liquid fuel line are arranged to form a line arrangement for connection to the nozzle apparatus. The flow cross section of the gas fuel line is of at least substantially identically large configuration within the separate gas line portion and the gas/liquid line portion.