Patents by Inventor Gerhard-Heinz Roesele

Gerhard-Heinz Roesele 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: 10689983
    Abstract: An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: June 23, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Gerhard-Heinz Roesele, Martin Pernleitner, Manfred Schill, Manfred Feldmann, Adrian Ehrenberg
  • Patent number: 10570752
    Abstract: An impulse element module for a turbomachine, in particular a turbine stage of a gas turbine, preferably an aircraft gas turbine, including a single-unit receptacle component having a base and side walls that extend peripherally thereon, the side walls and the base bounding a receiving space; a single-unit insert component having a form that is inserted into receiving space of receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element, in particular a sphere, being accommodated in each cavity; and a single-unit sealing component that is joined in a material-to-material bond to the receptacle component in a way that allows the receiving space to be sealed and the insert component to be surrounded by the receptacle component and the sealing component.
    Type: Grant
    Filed: May 5, 2017
    Date of Patent: February 25, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Gerhard-Heinz Roesele, Markus Schlemmer, Andreas Hartung
  • Patent number: 10526901
    Abstract: A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).
    Type: Grant
    Filed: March 14, 2017
    Date of Patent: January 7, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Gerhard-Heinz Roesele, Andreas Hartung
  • Patent number: 10247005
    Abstract: A blade or vane arrangement for a turbomachine includes a turbomachine blade or vane and at least one tuning element guide housing with at least one cavity, in which at least one tuning element, which is provided for impact contact with the tuning element guide housing is taken up, the tuning element guide housing being arranged in a recess of the turbomachine blade or vane, wherein the cavity of the tuning element guide housing in which the tuning element is taken up, is closed in a gas-tight manner.
    Type: Grant
    Filed: November 6, 2015
    Date of Patent: April 2, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Andreas Hartung, Manfred Schill, Gerhard-Heinz Roesele
  • Publication number: 20180119552
    Abstract: An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.
    Type: Application
    Filed: October 25, 2017
    Publication date: May 3, 2018
    Applicant: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Gerhard-Heinz Roesele, Martin Pernleitner, Manfred Schill, Manfred Feldmann, Adrian Ehrenberg
  • Publication number: 20170335695
    Abstract: A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).
    Type: Application
    Filed: March 14, 2017
    Publication date: November 23, 2017
    Inventors: Markus Schlemmer, Gerhard-Heinz Roesele, Andreas Hartung
  • Publication number: 20170321557
    Abstract: An impulse element module for a turbomachine, in particular a turbine stage of a gas turbine, preferably an aircraft gas turbine, including a single-unit receptacle component having a base and side walls that extend peripherally thereon, the side walls and the base bounding a receiving space; a single-unit insert component having a form that is inserted into receiving space of receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element, in particular a sphere, being accommodated in each cavity; and a single-unit sealing component that is joined in a material-to-material bond to the receptacle component in a way that allows the receiving space to be sealed and the insert component to be surrounded by the receptacle component and the sealing component.
    Type: Application
    Filed: May 5, 2017
    Publication date: November 9, 2017
    Inventors: Gerhard-Heinz ROESELE, Markus Schlemmer, Andreas Hartung
  • Publication number: 20160138401
    Abstract: The present invention relates to a blade or vane arrangement for a turbomachine having a turbomachine blade or vane (10) and at least one tuning element guide housing (21, 22) with at least one cavity (11), in which at least one tuning element (3), which is provided for impact contact with the tuning element guide housing is taken up, the tuning element guide housing being arranged in a recess (12) of the turbomachine blade or vane, wherein the cavity (11) of the tuning element guide housing (21, 22) in which the tuning element (3) is taken up, is closed in a gas-tight manner.
    Type: Application
    Filed: November 6, 2015
    Publication date: May 19, 2016
    Inventors: Andreas Hartung, Manfred Schill, Gerhard-Heinz Roesele