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: 11098609Abstract: 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: GrantFiled: January 22, 2019Date of Patent: August 24, 2021Assignee: MTU Aero Engines AGInventor: Jochen Gier
-
Publication number: 20190226352Abstract: 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: ApplicationFiled: January 22, 2019Publication date: July 25, 2019Applicant: MTU Aero Engines AGInventor: Jochen Gier
-
Patent number: 10041353Abstract: 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: GrantFiled: August 6, 2014Date of Patent: August 7, 2018Assignee: MTU Aero Engines AGInventors: Jochen Gier, Yavuz Guendogdu, Karl Engel
-
Patent number: 10001083Abstract: 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: GrantFiled: July 18, 2014Date of Patent: June 19, 2018Assignee: MTU Aero Engines AGInventors: 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: 9863251Abstract: 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: GrantFiled: November 28, 2012Date of Patent: January 9, 2018Assignee: MTU Aero Engines GmbHInventors: Inga Mahle, Jochen Gier, Kai Koerber, Karl Engel
-
Patent number: 9745850Abstract: 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: GrantFiled: May 23, 2014Date of Patent: August 29, 2017Assignee: MTU Aero Engines AGInventors: Yavuz Guendogdu, Jochen Gier, Karl Engel
-
Patent number: 9382806Abstract: 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: GrantFiled: January 16, 2012Date of Patent: July 5, 2016Assignee: MTU Aero Engines GmbHInventors: Martin Hoeger, Inga Mahle, Jochen Gier
-
Publication number: 20160032826Abstract: 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: ApplicationFiled: August 4, 2014Publication date: February 4, 2016Inventors: 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: 20160017797Abstract: 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: ApplicationFiled: July 18, 2014Publication date: January 21, 2016Inventors: 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: 20150044038Abstract: 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: ApplicationFiled: August 6, 2014Publication date: February 12, 2015Inventors: Jochen Gier, Yavuz Guendogdu, Karl Engel
-
Publication number: 20140348660Abstract: 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: ApplicationFiled: May 23, 2014Publication date: November 27, 2014Applicant: MTU Aero Engines AGInventors: Yavuz GUENDOGDU, Jochen Gier, Karl Engel
-
Patent number: 8814529Abstract: 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: GrantFiled: July 17, 2009Date of Patent: August 26, 2014Assignee: MTU Aero Engines GmbHInventors: Andreas Fiala, Jochen Gier
-
Publication number: 20130064657Abstract: 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: ApplicationFiled: January 16, 2012Publication date: March 14, 2013Applicant: MTU Aero Engines GmbHInventors: Martin Hoeger, Inga Mahle, Jochen Gier
-
Publication number: 20110182746Abstract: 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: ApplicationFiled: July 17, 2009Publication date: July 28, 2011Applicant: MTU AERO ENGINES GMBHInventors: Andreas Fiala, Jochen Gier