Patents by Inventor Carsten Clemen

Carsten Clemen has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20240053015
    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.
    Type: Application
    Filed: July 25, 2023
    Publication date: February 15, 2024
    Inventors: Carsten CLEMEN, Thomas DÖRR
  • Publication number: 20240053014
    Abstract: 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.
    Type: Application
    Filed: July 21, 2023
    Publication date: February 15, 2024
    Inventor: Carsten CLEMEN
  • Publication number: 20240027067
    Abstract: 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.
    Type: Application
    Filed: July 17, 2023
    Publication date: January 25, 2024
    Inventors: Carsten CLEMEN, Gregor Christoffer GEBEL
  • Publication number: 20240027070
    Abstract: A nozzle device for feeding a gaseous fuel and a liquid fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the gaseous and/or liquid fuels into the combustion chamber, a liquid fuel line for the fluidic connection between a liquid supply line system and the nozzle openings, and at least one gas fuel line for the fluidic connection between a gas supply line system and the nozzle openings. An optimized operation is achieved in that at least partly the gas fuel line is configured to be correlated with the liquid fuel line, wherein a flow cross section AiH2 of the gas fuel line is proportional to a flow cross section AiK of the liquid fuel line by a factor F, where: AiH2=F*Aik, F being 2.4-3, preferably 2.6-2.8, e.g. 2.7.
    Type: Application
    Filed: July 17, 2023
    Publication date: January 25, 2024
    Inventor: Carsten CLEMEN
  • Publication number: 20240026823
    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.
    Type: Application
    Filed: July 17, 2023
    Publication date: January 25, 2024
    Inventor: Carsten CLEMEN
  • Patent number: 11549862
    Abstract: 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° before the measuring fluid exits the fluid channel at the at least one outlet.
    Type: Grant
    Filed: May 22, 2019
    Date of Patent: January 10, 2023
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten Clemen, Miklos Gerendas
  • Publication number: 20210285640
    Abstract: The proposed solution relates to a nozzle for a combustion chamber of an engine for the purposes of providing a fuel-air mixture at a nozzle exit opening of the nozzle. The nozzle is, at a nozzle exit opening, formed with at least one guiding element for guiding a resulting fuel-air mixture radially outward with respect to the nozzle longitudinal axis and a center of the nozzle exit opening, and has, on the nozzle main body, at least one jet generator duct for generating at least one fuel jet which is directed radially inward and/or in the direction of a center of the nozzle exit opening.
    Type: Application
    Filed: March 8, 2021
    Publication date: September 16, 2021
    Inventors: Max STAUFER, Carsten CLEMEN
  • Patent number: 10837646
    Abstract: 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.
    Type: Grant
    Filed: February 26, 2018
    Date of Patent: November 17, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten Clemen, Michael Ebel, Kay Heinze, Stefan Penz
  • Patent number: 10808557
    Abstract: 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.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: October 20, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten Clemen, Thomas Doerr
  • Patent number: 10712006
    Abstract: 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?D1)/C2 is 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.
    Type: Grant
    Filed: October 5, 2017
    Date of Patent: July 14, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten Clemen, Torsten Voigt, Thomas Doerr
  • Patent number: 10670270
    Abstract: 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.
    Type: Grant
    Filed: December 15, 2016
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Carsten Clemen
  • Publication number: 20200103113
    Abstract: A combustion chamber assembly for an engine, with a combustion chamber which extends in a circumferential direction, and with several heat shields and/or burner seals arranged next to each other in the circumferential direction, to each of which at least one fuel nozzle is assigned for introduction of fuel into the combustion chamber. At least two different types of heat shield and/or burner seal are provided along the circumferential direction, which differ depending on whether or not a spark plug is provided downstream of an assigned fuel nozzle.
    Type: Application
    Filed: September 19, 2019
    Publication date: April 2, 2020
    Inventor: Carsten CLEMEN
  • Patent number: 10591162
    Abstract: 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.
    Type: Grant
    Filed: November 12, 2014
    Date of Patent: March 17, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Carsten Clemen
  • Patent number: 10544942
    Abstract: A method for mounting a combustion chamber of a gas turbine engine, wherein an annular outer combustion chamber wall and an annular inner combustion chamber wall are brought in position with respect to one another and are connected to a head plate, and wherein subsequently a combustion chamber head is mounted, characterized in that the head plate is connected to the outer combustion chamber wall and the inner combustion chamber wall by means of rivets that are arranged in a circumferentially distributed manner, and that subsequently the combustion chamber head is brought in position and is screwed together by means of threaded bolts and nuts to the arrangement of head plate, outer combustion chamber wall and inner combustion chamber wall, which is pre-mounted by means of the rivet.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: January 28, 2020
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Carsten Clemen, Kay Heinze, Volker Herzog
  • Publication number: 20190360895
    Abstract: 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 comprises 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° before the measuring fluid exits the fluid channel at the at least one outlet.
    Type: Application
    Filed: May 22, 2019
    Publication date: November 28, 2019
    Inventors: Carsten CLEMEN, Miklos GERENDAS
  • Patent number: 10465708
    Abstract: A diffuser component for a gas turbine is provided, where a fluid flow in the direction of a combustion chamber of the gas turbine can be slowed down by the diffuser component, and a flow cross-section of the diffuser component, which is defined by a diffuser wall is widened to do so. The diffuser wall is at least locally braced, in that at least one stiffening element with a lattice-type structure is provided on the diffuser wall.
    Type: Grant
    Filed: July 18, 2016
    Date of Patent: November 5, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten Clemen, Ivo Szarvasy
  • Patent number: 10330204
    Abstract: A burner seal of a gas turbine with a substantially tubular base body, which has a ring-shaped inlet lip on the inflow side and a funnel at its outflow side, wherein an inner diameter of the inflow side is embodied to be larger than an inner diameter of a sealing surface that is arranged axially in front of the funnel, wherein cooling channels are formed in the base body distributed about the circumference, wherein the cooling channels are formed respectively in the base body in the area of the sealing surface and of the funnel, and respectively open into an end area of the funnel in an exit hole.
    Type: Grant
    Filed: November 10, 2017
    Date of Patent: June 25, 2019
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Publication number: 20190145524
    Abstract: A burner seal of a gas turbine with a substantially tubular base body, which has a ring-shaped inlet lip on the inflow side and a funnel at its outflow side, wherein an inner diameter of the inflow side is embodied to be larger than an inner diameter of a sealing surface that is arranged axially in front of the funnel, wherein cooling channels are formed in the base body distributed about the circumference, wherein the cooling channels are formed respectively in the base body in the area of the sealing surface and of the funnel, and respectively open into an end area of the funnel in an exit hole.
    Type: Application
    Filed: November 10, 2017
    Publication date: May 16, 2019
    Inventor: Carsten CLEMEN
  • Publication number: 20190093896
    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).
    Type: Application
    Filed: August 30, 2018
    Publication date: March 28, 2019
    Inventors: Carsten CLEMEN, Benno WURM, Ruud EGGELS
  • Publication number: 20190093893
    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.
    Type: Application
    Filed: September 25, 2018
    Publication date: March 28, 2019
    Inventors: Carsten CLEMEN, Ruud EGGELS