Patents by Inventor Martin Stadlbauer

Martin Stadlbauer 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).

  • Turbomachine stage and method for determining a seal gap and/or an axial position of such a turbomachine stage
    Patent number: 9957833
    Abstract: A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange. The sealing flange has a recess arrangement with at least one radial recess in which, centrally in particular, a radial projection is arranged. There is arranged on the housing a sensor arrangement with at least one capacitive sensor for detecting a radial clearance to a peripheral surface of the sealing flange.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: May 1, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Florian Gerbl, Juergen Gruendmayer, Martin Stadlbauer, Ernst Trassl
  • METHOD FOR DETERMING A TRANSITION POINT AND/OR FOR DETERMINING WALL SHEAR STRESSES ON SURFACES AROUND WHICH SURFACES A FLOW CIRCULATES, AND MEASURING DEVICE
    Publication number: 20160258827
    Abstract: The invention relates to a method for determining a transition point and/or for determining wall shear stresses on surfaces (1) around which surfaces a flow circulates by means of thermography, wherein the method comprises the following steps: providing a surface with a heat insulation layer (3) on the surface (1) around which a flow is to circulate, circulating a flow around the surface (1) around which a flow is to circulate, heating the surface (1) around which a flow circulates, contactless measuring of the emitted flow intensity of the surface (1) around which a flow circulates by means of a camera system (7), determining at least one temperature decay coefficient on the surface (1) around which a flow circulates and ascertaining the transition point and/or the wall shear stresses on the surface (1) around which a flow circulates.
    Type: Application
    Filed: June 10, 2014
    Publication date: September 8, 2016
    Applicant: MTU Aero Engines AG
    Inventors: Martin Stadlbauer, Jurgen Grundmayer, Felix Von Plehwe
  • TURBOMACHINE STAGE AND METHOD FOR DETERMINING A SEAL GAP AND/OR AN AXIAL POSITION OF SUCH A TURBOMACHINE STAGE
    Publication number: 20140348631
    Abstract: A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange. The sealing flange has a recess arrangement with at least one radial recess in which, centrally in particular, a radial projection is arranged. There is arranged on the housing a sensor arrangement with at least one capacitive sensor for detecting a radial clearance to a peripheral surface of the sealing flange.
    Type: Application
    Filed: May 21, 2014
    Publication date: November 27, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Florian GERBL, Juergen Gruendmayer, Martin Stadlbauer, Ernst Trassl