Patents by Inventor Karl-Hermann Richter

Karl-Hermann Richter 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).

  • Patent number: 11002140
    Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: May 11, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Publication number: 20200190986
    Abstract: The present invention relates to an impulse body module group with at least two impulse body modules, which, in particular, are identical in construction, for a gas turbine blade, wherein each of the impulse body modules comprises a housing, which, in particular, is of one piece and which has a first cavity, which is closed, in particular in an airtight manner, by a first cover, which is joined to the housing, in particular in a material-bonded manner, and in which a single, in particular spherical or cylindrical, first impulse body is accommodated with play of movement in at least one first direction of impact, wherein the housing has no additional cavity or a single additional cavity, in which a single, in particular spherical or cylindrical, additional impulse body is accommodated with play of movement in at least one direction of impact.
    Type: Application
    Filed: December 12, 2019
    Publication date: June 18, 2020
    Applicant: MTU Aero Engines AG
    Inventors: Karl-Hermann Richter, Herbert Hanrieder, Steffen Gerloff
  • Patent number: 10646962
    Abstract: The invention relates to a method for producing a low-pressure turbine blade from a TiAl material by means of a selective laser melting process, wherein during production in the selective laser melting process the already partially manufactured low-pressure turbine blade is preheated by inductive heating, and wherein the selective laser melting process is carried out under protective gas, the protective gas atmosphere containing contaminants of oxygen, nitrogen, and water vapor in each case of less than or equal to 10 ppm.
    Type: Grant
    Filed: March 28, 2013
    Date of Patent: May 12, 2020
    Assignee: MTU AERO ENGINES AG
    Inventors: Karl-Hermann Richter, Herbert Hanrieder
  • Patent number: 10634008
    Abstract: The invention relates to a method for manufacturing a housing of a turbomachine, in particular a gas turbine. The method comprises at least the steps: providing a housing blank, manufacturing a housing element, producing an assembly opening corresponding to the housing element in the housing blank, arranging the housing element in the assembly opening, and joining the housing element to the housing blank by means of a welding method. In addition, the invention relates to a turbomachine housing.
    Type: Grant
    Filed: March 10, 2017
    Date of Patent: April 28, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Karl-Hermann Richter
  • Patent number: 10583521
    Abstract: Disclosed is a method for producing a blade comprising a blade airfoil and a blade root for a turbomachine. The method comprises providing a first workpiece based on a first material and a second workpiece based on a second material which is different from the first material and has a higher temperature resistance than the first material; and connecting the first workpiece and the second workpiece by friction welding to form a composite component having a first region of the first material, and a second region of the second material. Optionally upon material-subtracting further processing, the first region forms the blade root, and the second region forms the blade airfoil.
    Type: Grant
    Filed: December 6, 2017
    Date of Patent: March 10, 2020
    Assignee: MTU AERO ENGINES AG
    Inventor: Karl-Hermann Richter
  • Patent number: 10550720
    Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: February 4, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Patent number: 10451089
    Abstract: A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (A) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element (31) is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.
    Type: Grant
    Filed: September 6, 2016
    Date of Patent: October 22, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder, Manfred Schill
  • Patent number: 10415425
    Abstract: The invention relates to a turbomachine including: a guide baffle, whose sv guide blades are situated on c guide blade carriers; and an adjacent moving baffle including sb moving blades; the guide baffle nv including impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nb including impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient ? i = 1 n v ? ? m i s v - c of sum ? i = 1 n v ? ? m i of the masses of all impulse bodies of the guide baffle divided by the difference (sv?c) of the number sv of all guide blades minus the number c of all guide blade carriers amounts to at least 1.
    Type: Grant
    Filed: January 17, 2017
    Date of Patent: September 17, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Patent number: 10144062
    Abstract: A method for producing a component of a turbomachine is disclosed. The method includes a) layer-by-layer deposition of a powder component material onto a component platform in a region of a buildup and joining zone, where the deposition takes place in accordance with layer information of the component to be produced; b) local layer-by-layer fusion or sintering of the powder component material by energy supplied in the region of the buildup and joining zone, where the buildup and joining zone is heated to a temperature just below a melting point of the powder component material; c) layer-by-layer lowering of the component platform by a predefined layer thickness; and d) repetition of steps a) to c) until the component is finished. A device for producing a component of a turbomachine is also disclosed.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: December 4, 2018
    Assignee: MTU Aero Engines GmbH
    Inventors: Erwin Bayer, Karl-Hermann Richter
  • Patent number: 10119408
    Abstract: The present invention provides a method for connecting a turbine blade or vane to a turbine disk or to a turbine ring. First, a connecting body is formed on the turbine blade or vane by supplying an additive suitable for fusion welding to a surface of the turbine blade or vane, melting the additive on the surface, with incipient melting of the surface, and allowing the additive and the surface to solidify. Then, the connecting body is connected to the turbine disk or to the turbine ring by means of a fusion welding process.
    Type: Grant
    Filed: August 6, 2011
    Date of Patent: November 6, 2018
    Assignee: MTU AERO ENGINES AG
    Inventor: Karl-Hermann Richter
  • Patent number: 10006300
    Abstract: A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material.
    Type: Grant
    Filed: November 6, 2012
    Date of Patent: June 26, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Bernd Daniels, Karl-Hermann Richter
  • Publication number: 20180154479
    Abstract: Disclosed is a method for producing a blade comprising a blade airfoil and a blade root for a turbomachine. The method comprises providing a first workpiece based on a first material and a second workpiece based on a second material which is different from the first material and has a higher temperature resistance than the first material; and connecting the first workpiece and the second workpiece by friction welding to form a composite component having a first region of the first material, and a second region of the second material. Optionally upon material-subtracting further processing, the first region forms the blade root, and the second region forms the blade airfoil.
    Type: Application
    Filed: December 6, 2017
    Publication date: June 7, 2018
    Inventor: Karl-Hermann RICHTER
  • Publication number: 20170292403
    Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.
    Type: Application
    Filed: April 10, 2017
    Publication date: October 12, 2017
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Publication number: 20170292387
    Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.
    Type: Application
    Filed: April 10, 2017
    Publication date: October 12, 2017
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Publication number: 20170276023
    Abstract: The invention relates to a method for manufacturing a housing of a turbomachine, in particular a gas turbine. The method comprises at least the steps: providing a housing blank (10), manufacturing a housing element (14), producing an assembly opening (12) corresponding to the housing element (14) in the housing blank (10), arranging the housing element (14) in the assembly opening (12), and joining the housing element (14) to the housing blank (10) by means of a welding method. In addition, the invention relates to a turbomachine housing.
    Type: Application
    Filed: March 10, 2017
    Publication date: September 28, 2017
    Inventor: Karl-Hermann Richter
  • Publication number: 20170266745
    Abstract: The invention relates to a method for producing a mistuning component. The method comprises the following steps: a) producing a container (34) having at least one chamber (36); b) producing a lid (32, 32?); c) inserting at least one impulse element into the chamber (36); d) joining the lid (32, 32?) and the container (36), wherein joining is carried out by soldering/brazing.
    Type: Application
    Filed: March 15, 2017
    Publication date: September 21, 2017
    Inventor: Karl-Hermann RICHTER
  • Patent number: 9765632
    Abstract: Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising: forging at least two blanks made of a TiAl material, joining the blanks to form a blade or vane ring by means of an integral connection process, and remachining of the blank composite by material-removing processes.
    Type: Grant
    Filed: August 8, 2013
    Date of Patent: September 19, 2017
    Assignee: MTU AERO ENGINES AG
    Inventor: Karl-Hermann Richter
  • Publication number: 20170204740
    Abstract: The invention relates to a turbomachine including: a guide baffle, whose sv guide blades are situated on c guide blade carriers; and an adjacent moving baffle including sb moving blades; the guide baffle nv including impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nb including impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient ? i = 1 n v ? ? m i s v - c of sum ? i = 1 n v ? ? m i of the masses of all impulse bodies of the guide baffle divided by the difference (sv?c) of the number sv of all guide blades minus the number c of all guide blade carriers amounts to at least 1.
    Type: Application
    Filed: January 17, 2017
    Publication date: July 20, 2017
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Publication number: 20170087669
    Abstract: An apparatus and a method for producing and/or repairing a component. The method comprises: a. providing a component and/or a starting platform, b. placing the component and/or the starting platform on a sample table, c. preheating the component and/or the starting platform by a heating source to a temperature from about 300° C. below to about 50° C. above the brittle-ductile transition temperature of the material of the component, d. applying a wire-shaped and/or rod-shaped filler material comprising TiAl to the component and/or starting platform by build-up welding, an energy source melting the filler material.
    Type: Application
    Filed: September 22, 2016
    Publication date: March 30, 2017
    Inventors: Martin SCHLOFFER, Karl-Hermann RICHTER
  • Publication number: 20170067487
    Abstract: A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (A) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element (31) is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.
    Type: Application
    Filed: September 6, 2016
    Publication date: March 9, 2017
    Inventors: Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder, Manfred Schill