Patents by Inventor Roland Matzgeller

Roland Matzgeller 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).

  • ENGINE WITH A COMPRESSOR
    Publication number: 20240011434
    Abstract: The invention is directed to an engine that has a fan, a compressor with a high-pressure compressor, and a combustion chamber. The high-pressure compressor of the engine has a mean stage pressure ratio and an overall pressure ratio formed between the fan and the combustion chamber.
    Type: Application
    Filed: June 30, 2023
    Publication date: January 11, 2024
    Applicant: MTU Aero Engines AG
    Inventors: Sergio Elorza Gomez, Werner Humhauser, Roland Matzgeller
  • COMPRESSOR FOR AN ENGINE
    Publication number: 20240003353
    Abstract: The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.
    Type: Application
    Filed: June 30, 2023
    Publication date: January 4, 2024
    Applicant: MTU Aero Engines AG
    Inventors: Sergio Elorza Gomez, Werner Humhauser, Roland Matzgeller
  • Gas turbine compressor stage
    Patent number: 10280934
    Abstract: The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point ? and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition ?>?1.33·ARax+5.16.
    Type: Grant
    Filed: August 24, 2016
    Date of Patent: May 7, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Werner Humhauser, Roland Matzgeller
  • GAS TURBINE COMPRESSOR STAGE
    Publication number: 20170074271
    Abstract: The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point ? and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition ?>?1.33×ARax+5.16.
    Type: Application
    Filed: August 24, 2016
    Publication date: March 16, 2017
    Inventors: Werner Humhauser, Roland Matzgeller