Patents by Inventor Peter Eibelshaeuser

Peter Eibelshaeuser 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: 11125101
    Abstract: A sealing ring for a turbomachine, in particular a compressor or turbine stage of a gas turbine is provided, the sealing ring having an, in particular at least partially honeycomb-like and/or integral, seal, in particular an abradable coating (13); a profile cross section of the sealing ring, which is in particular at least partially manufactured by a generative manufacturing process, varying in the circumferential direction, in particular at least in some regions continuously and/or non-continuously at one or more circumferential positions, in particular separation points.
    Type: Grant
    Filed: June 26, 2018
    Date of Patent: September 21, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Christian Scherer, Peter Eibelshaeuser, Steffen Schlothauer, Andreas Jakimov, Juergen Kraus
  • Publication number: 20190010820
    Abstract: A sealing ring for a turbomachine, in particular a compressor or turbine stage of a gas turbine is provided, the sealing ring having an, in particular at least partially honeycomb-like and/or integral, seal, in particular an abradable coating (13); a profile cross section of the sealing ring, which is in particular at least partially manufactured by a generative manufacturing process, varying in the circumferential direction, in particular at least in some regions uniformly and/or non-uniformly at one or more circumferential positions, in particular separation points.
    Type: Application
    Filed: June 26, 2018
    Publication date: January 10, 2019
    Inventors: Christian SCHERER, Peter EIBELSHAEUSER, Steffen SCHLOTHAUER, Andreas JAKIMOV, Juergen KRAUS
  • Patent number: 9605541
    Abstract: A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2).
    Type: Grant
    Filed: July 25, 2013
    Date of Patent: March 28, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Johann Geppert, Peter Eibelshaeuser
  • Patent number: 9435207
    Abstract: A blade for a blade row of a turbomachine having wired sections, in particular a blade of a compressor rotor blade, as well as a method for wiring sections of such a blade, is disclosed. Sections of a blade are wired in such a way that a first central component of a second section is selected according to at least one central component of a first section.
    Type: Grant
    Filed: January 29, 2011
    Date of Patent: September 6, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Sergio Elorza Gomez, Peter Eibelshaeuser
  • Patent number: 9399918
    Abstract: A blade for a continuous-flow machine is disclosed, especially an aircraft engine, whereby, starting from the middle section, the cross section of the blade tip is reduced with respect to the middle section, at least over a front partial section in the direction of the leading edge and over at least a rear section in the direction of the trailing edge, and a continuous-flow machine having at least one row of blades including such blades is also disclosed.
    Type: Grant
    Filed: August 8, 2013
    Date of Patent: July 26, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Johann Geppert, Peter Eibelshaeuser, Heinz Rauschmair
  • Publication number: 20140044553
    Abstract: A blade for a continuous-flow machine is disclosed, especially an aircraft engine, whereby, starting from the middle section, the cross section of the blade tip is reduced with respect to the middle section, at least over a front partial section in the direction of the leading edge and over at least a rear section in the direction of the trailing edge, and a continuous-flow machine having at least one row of blades including such blades is also disclosed.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 13, 2014
    Inventors: Johann GEPPERT, Peter Eibelshaeuser, Heinz Rauschmair
  • Publication number: 20140044546
    Abstract: A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2).
    Type: Application
    Filed: July 25, 2013
    Publication date: February 13, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Johann GEPPERT, Peter Eibelshaeuser
  • Publication number: 20120315148
    Abstract: The invention relates to a method for wiring suctions ((i), (i+1)) of a blade (1) for a blade row of a turbomachine. According to said method, a first central component (formula (II)) of a second section ((i+1)) is selected according to at least one central component ((formula (IV)), xCG(i), rCG(i)) of a first section ((i)), especially according to a formula (I) where: (i) is a variable of the first section; (i+1) is a variable of the second section; (formula (III)) is a central component of a section in the peripheral direction, preferably in the angular or radian measure; xCG is a central component of a section in the axial direction; rCG is a central component of a section in the radial direction; ? is a graduated angle of a section; and (formula (V)) is a peripheral incline, preferably in the angular or radian measure.
    Type: Application
    Filed: January 29, 2011
    Publication date: December 13, 2012
    Applicant: MTU Aero Engines Gmbh
    Inventors: Sergio Elorza Gomez, Peter Eibelshaeuser