Rolls-royce Deutschland Ltd & Co. Kg

Carsten Clemen

Thomas Doerr

Michael Ebel

Thomas Dörr

Stefan Penz

Kay Heinze

Miklós Gerendás

Sebastian Bake

Henner Schrapp

Gregor Christoffer Gebel

Miklos Gerendas

Ivo Szarvasy

Waldemar Lazik

Volker Herzog

Igor Sikorski

Enrique Sielaff

Christoffer Gregor Gebel

Ruud Eggels

Torsten Voigt

Tobias Mellentien

Thomas DÖRR

The invention concerns a combustion chamber assembly, in particular for use in an aircraft engine, including: 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.

Combustion chamber assembly for operation with liquid and/or gaseous fuel, gas turbine assembly and method

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.

Combustion chamber assembly for an engine with at least one heat exchanger channel for fuel to be injected

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.

Combustion chamber module having an annular combustion chamber

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.

Drive system for an aircraft, aircraft having a drive system and method for operating an aircraft

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.

Piloting arrangement, nozzle device, gas turbine arrangement and method

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.

Connecting apparatus for the flow connection between a fuel feed line system and a nozzle apparatus, nozzle apparatus and gas turbine arrangement

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 () 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.

Fuel nozzle having different first and second discharge orifices for providing a hydrogen-air mixture

A nozzle device for feeding fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the fuel into the combustion chamber; a nozzle bracket having a fuel line for fluidic connection between a manifold fuel line and the main body, wherein at least a portion of the fuel line is aligned along, a central longitudinal axis; and a throttle element disposed downstream of the manifold fuel line for throttling the fuel flow to a pre-specified target quantity. The throttle element includes two stages which are fluidically disposed in series, each stage having a line portion aligned along a central longitudinal axis and a flow cross section. A relaxation chamber is disposed between the stages, the flow cross section of the relaxation chamber being larger than the flow cross section of the upstream stage.

Nozzle device for feeding fuel into a combustion chamber of a gas turbine assembly, and gas turbine assembly

A pilot arrangement for a nozzle 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 a flow cross section of a pilot fuel nozzle, and the pilot fuel nozzle, which adjoins the cavity downstream and includes a pilot line and a pilot fuel outlet arranged downstream of the pilot line, the narrowest flow cross section of which is smaller than that of the cavity. A compact configuration is achieved in that the cavity is arranged in a central body arranged on the longitudinal axis, a swirling element is arranged in a circumferential manner around the central body, wherein the central body and the swirling element form a swirling arrangement, and the swirling element, the central body and the pilot fuel nozzle are configured as a continuous, integral component.

Pilot arrangement, nozzle device, method and gas turbine arrangement

A measuring device with at least one fluid channel for conveying a measuring fluid, wherein the fluid channel includes at least one inlet for the entry of the measuring fluid into the fluid channel and at least one outlet for the exit of the measuring fluid from the fluid channel. The fluid channel includes a diamond-shaped cross-section and includes a course from the at least one inlet to the at least one outlet over which the measuring fluid entering the fluid channel is deflected by at least 90&#xb0; before the measuring fluid exits the fluid channel at the at least one outlet.

Measuring device comprising at least one fluid channel for guiding a measurement fluid

A combustion chamber shingle arrangement of a gas turbine, including a combustion chamber shingle, at least one threaded bolt configured for attaching the combustion chamber shingle, and a base body connecting the threaded bolt to the combustion chamber shingle, wherein the base body comprises a platform and a connection area that connects the platform to the combustion chamber shingle, wherein the threaded bolt is arranged at the platform, and wherein a hollow space is embodied between the platform and the combustion chamber shingle.

Combustion chamber shingle arrangement of a gas turbine

A nozzle assembly group for a combustion chamber of an engine, with multiple nozzles for introducing fuel into the combustion chamber that are arranged next to each other, wherein each nozzle has a nozzle outlet opening and a fuel channel for conveying fuel in the direction of the nozzle outlet opening. According to the invention, it is provided that at least two different types of nozzles are provided, wherein the nozzles of different types have nozzle outlet openings with an identical cross section, and for predetermining different flow rates of fuel through the fuel channels of the nozzles of different types, a cross section of a fuel channel of one type of nozzle is different from a cross section of a fuel channel of another type of nozzle.

Nozzle assembly for a combustion chamber of an engine

A gas turbine combustion chamber includes first admixing air holes having first inner and outer center points, and second admixing air holes having second inner and outer center points. The first and second inner center points respectively lie on a side of the first and second admixing air holes oriented towards the combustion chamber. The first and second outer center points lie on a side of the first and second admixing air holes facing away from the combustion chamber. An equation L=D2/D1*(D2&#x2212;D1)/Cis fulfilled, with L being a distance between the first and second inner center points and/or the first and second outer center points; D1 and D2 being flow diameters of the first and second admixing air holes respectively at an entry and/or exit side to the combustion chamber and C being an average flow rate coefficient of the first and second admixing holes.

Combustion chamber arrangement of a gas turbine and aircraft gas turbine

A gas turbine combustion chamber with an inner combustion chamber wall and an outer combustion chamber wall, which form an annular combustor, is provided. Mixing air holes are formed in the inner combustion chamber wall and the outer combustion chamber wall in a circumferentially distributed manner. The respective combustion chamber wall is bulged in the area of the mixing air holes towards the interior space of the combustion chamber wall and the mixing air hole is arranged inside the bulge. The mixing air hole is formed at an inflow surface of the bulge with respect to the through-flow direction of the combustion chamber.

Gas turbine combustion chamber with wall contouring

The present invention relates to a combustion chamber heat-shielding element of a gas-turbine, having a bolt for mounting the combustion chamber heat-shielding element on a combustion chamber wall or a combustion chamber head, where the combustion chamber heat-shielding element is designed substantially plate-like and where on one side at least one bolt, which is designed as a separate component, is anchored on it by means of a bonded connection.

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Mittenwalde, Germany

Carsten Clemen