Patents by Inventor Jochen Gier

Jochen Gier 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: 11098609
    Abstract: The present invention relates to a rotor blade shroud for a turbomachine, comprising a sealing tip and a support structure that abuts the sealing tip. The support structure has at least one intermediate region in which a structural segment is arranged, wherein the radially outwardly arranged surface of the support structure and of the structural segment forms an essentially planar surface. The present invention further relates to a rotor blade for a turbomachine, comprising a rotor blade shroud as well as two methods of manufacturing a rotor blade shroud and a method of manufacturing a rotor blade.
    Type: Grant
    Filed: January 22, 2019
    Date of Patent: August 24, 2021
    Assignee: MTU Aero Engines AG
    Inventor: Jochen Gier
  • Publication number: 20190226352
    Abstract: The present invention relates to a rotor blade shroud for a turbomachine, comprising a sealing tip and a support structure that abuts the sealing tip. The support structure has at least one intermediate region in which a structural segment is arranged, wherein the radially outwardly arranged surface of the support structure and of the structural segment forms an essentially planar surface. The present invention further relates to a rotor blade for a turbomachine, comprising a rotor blade shroud as well as two methods of manufacturing a rotor blade shroud and a method of manufacturing a rotor blade.
    Type: Application
    Filed: January 22, 2019
    Publication date: July 25, 2019
    Applicant: MTU Aero Engines AG
    Inventor: Jochen Gier
  • Patent number: 10041353
    Abstract: A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.
    Type: Grant
    Filed: August 6, 2014
    Date of Patent: August 7, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Jochen Gier, Yavuz Guendogdu, Karl Engel
  • Patent number: 10001083
    Abstract: A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W1) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W2) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (DF) of the fan to a maximum blade diameter (DL) of the second turbine is at least 3.5, in particular at least 4.
    Type: Grant
    Filed: July 18, 2014
    Date of Patent: June 19, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Klaus Peter Rued, Werner Humhauser, Hermann Klingels, Rudolf Stanka, Eckart Heinrich, Hans-Peter Hackenberg, Stefan Weber, Claus Riegler, Erich Steinhardt, Jochen Gier, Manfred Feldmann, Norbert Huebner, Karl Maar
  • Patent number: 9863251
    Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.
    Type: Grant
    Filed: November 28, 2012
    Date of Patent: January 9, 2018
    Assignee: MTU Aero Engines GmbH
    Inventors: Inga Mahle, Jochen Gier, Kai Koerber, Karl Engel
  • Patent number: 9745850
    Abstract: A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.
    Type: Grant
    Filed: May 23, 2014
    Date of Patent: August 29, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Yavuz Guendogdu, Jochen Gier, Karl Engel
  • Patent number: 9382806
    Abstract: Intermediate housing (14), in particular of turbines (11, 13) of a gas turbine engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24?), having a crossflow channel (33), which is formed by the bounding walls (23, 24, 24?) and within which at least one supporting rib (15) is positioned that has a leading edge (16), a trailing edge (17), as well as side walls (18) extending between the leading edge (16) and the trailing edge (17) that direct a gas flow traversing the crossflow channel (33); the radially outer bounding wall (24) having a contour that changes in the circumferential direction at least in one section upstream of the supporting rib (15).
    Type: Grant
    Filed: January 16, 2012
    Date of Patent: July 5, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Martin Hoeger, Inga Mahle, Jochen Gier
  • Publication number: 20160032826
    Abstract: A turbofan aircraft engine has at least one stage pressure ratio is at least 1.5, and a quotient of the total blade count divided by 110 is less than a difference ([(p1/p2)?1]) of the total pressure ratio minus one, and the total pressure ratio is greater than 4.5, and the turbine has at least two and no more than five turbine stages; and/or a product (An2) of an exit area (AL) of the second turbine and a square of a rotational speed of the second turbine at the design point is at least 4.5·1010 [in2·rpm2], and a blade tip velocity (uTIP) of at least one turbine stage of the second turbine at the design point is at least 400 meters per second. A jet and method are also provided.
    Type: Application
    Filed: August 4, 2014
    Publication date: February 4, 2016
    Inventors: Klaus Peter Rued, Werner Humhauser, Hermann Klingels, Rudolf Stanka, Eckart Heinrich, Hans-Peter Hackenberg, Claus Riegler, Erich Steinhardt, Jochen Gier, Manfred Feldmann, Norbert Huebner, Karl Maar, Stefan Weber
  • Publication number: 20160017797
    Abstract: A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W1) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W2) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (DF) of the fan to a maximum blade diameter (DL) of the second turbine is at least 3.5, in particular at least 4.
    Type: Application
    Filed: July 18, 2014
    Publication date: January 21, 2016
    Inventors: Klaus Peter RUED, Werner Humhauser, Hermann Klingels, Rudolf Stanka, Eckart Heinrich, Hans-Peter Hackenberg, Stefan Weber, Claus Rieger, Erich Steinhardt, Jochen Gier, Manfred Feldmann, Norbert Huebner, Karl Maar
  • Publication number: 20150044038
    Abstract: A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.
    Type: Application
    Filed: August 6, 2014
    Publication date: February 12, 2015
    Inventors: Jochen Gier, Yavuz Guendogdu, Karl Engel
  • Publication number: 20140348660
    Abstract: A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.
    Type: Application
    Filed: May 23, 2014
    Publication date: November 27, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Yavuz GUENDOGDU, Jochen Gier, Karl Engel
  • Patent number: 8814529
    Abstract: A blade construction for a turbo device, preferably a blade array of a low-pressure turbine, is disclosed. On the inlet-side profile surface of the blade a vortex generator is arranged downstream from the speed maximum. The vortex generator is formed by a surface undulation with at least one wave, the wave tail of which runs in the form of a wave trough and/or a wave peak in the blade vertical direction.
    Type: Grant
    Filed: July 17, 2009
    Date of Patent: August 26, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Andreas Fiala, Jochen Gier
  • Publication number: 20130064657
    Abstract: Intermediate housing (14), in particular of turbines (11, 13) of a gas turbine engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24?), having a crossflow channel (33), which is formed by the bounding walls (23, 24, 24?) and within which at least one supporting rib (15) is positioned that has a leading edge (16), a trailing edge (17), as well as side walls (18) extending between the leading edge (16) and the trailing edge (17) that direct a gas flow traversing the crossflow channel (33); the radially outer bounding wall (24) having a contour that changes in the circumferential direction at least in one section upstream of the supporting rib (15).
    Type: Application
    Filed: January 16, 2012
    Publication date: March 14, 2013
    Applicant: MTU Aero Engines GmbH
    Inventors: Martin Hoeger, Inga Mahle, Jochen Gier
  • Publication number: 20110182746
    Abstract: A blade construction for a turbo device, preferably a blade array of a low-pressure turbine, is disclosed. On the inlet-side profile surface of the blade a vortex generator is arranged downstream from the speed maximum. The vortex generator is formed by a surface undulation with at least one wave, the wave tail of which runs in the form of a wave trough and/or a wave peak in the blade vertical direction.
    Type: Application
    Filed: July 17, 2009
    Publication date: July 28, 2011
    Applicant: MTU AERO ENGINES GMBH
    Inventors: Andreas Fiala, Jochen Gier