Patents by Inventor Yavuz Guendogdu
Yavuz Guendogdu 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).
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Patent number: 11371370Abstract: The invention relates to a flow arrangement for placing in the hot gas duct of a turbomachine, having a first surrounding-flow structure and a second surrounding-flow structure, the surrounding-flow structures each having, in reference to the surrounding flow in the hot gas duct, a leading edge and, downstream thereof, a trailing edge, wherein the second surrounding-flow structure is provided as a deflecting blade with a suction side and a pressure side and has a lesser profile thickness than the first surrounding-flow structure, which is arranged on the suction side of the second surrounding-flow structure, and wherein, although the second surrounding-flow structure has a partial axial overlap with the first surrounding-flow structure referred to a longitudinal axis of the turbomachine, the trailing edge of the second surrounding-flow structure is, at the same time, displaced axially downstream relative to the trailing edge of the first surrounding-flow structure.Type: GrantFiled: July 17, 2018Date of Patent: June 28, 2022Assignee: MTU Aero Engines AGInventors: Martin Hoeger, Fadi Maatouk, Guenter Ramm, Yavuz Guendogdu, Irene Raab
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Patent number: 10837285Abstract: A blade (10) for a turbomachine is provided. In at least one cross section disposed orthogonally to a longitudinal blade axis, an outer surface of the blade forms a curve (?) that runs continuously on the inflow side along an at least approximate ellipse (E) between a first separation point (P1) and a second separation point (P2). On the pressure side 12, the curve (?) has an inflection point W. A distance of the second separation point (P2) from the inflection point W along the curve is at least exactly equal, at least twice as great, at least three times as great, or even at least five times as great as a distance of the second separation point (P2) from the first separation point (P1) along the at least approximate ellipse (E). Also described is a blade ring having at least one blade of this kind, as well as a turbomachine.Type: GrantFiled: July 18, 2018Date of Patent: November 17, 2020Assignee: MTU Aero Engines AGInventors: Guenter Ramm, Yavuz Guendogdu
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Patent number: 10746131Abstract: The present invention relates to a turbine module for a turbomachine, comprising a first flow bypass structure and a second flow bypass structure, said flow bypass structures being arranged in a hot gas duct, which is bounded by the turbine module and is designed to convey a hot gas and, namely, being arranged in succession in relation to a longitudinal axis of the turbine module in a direction of rotation, wherein, in relation to the bypass flow in the hot gas duct, the flow bypass structures each have a leading edge, and, downstream thereto, a trailing edge, and the second flow bypass structure is provided as a deflecting blade, wherein the second flow bypass structure has a smaller profile thickness than the first flow bypass structure, and wherein the hot gas duct is enclosed by a radial width.Type: GrantFiled: December 13, 2018Date of Patent: August 18, 2020Assignee: MTU Aero Engines AGInventors: Guenter Ramm, Martin Hoeger, Irene Raab, Yavuz Guendogdu
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Publication number: 20190186417Abstract: The present invention relates to a turbine module for a turbomachine, comprising a first flow bypass structure and a second flow bypass structure, said flow bypass structures being arranged in a hot gas duct, which is bounded by the turbine module and is designed to convey a hot gas and, namely, being arranged in succession in relation to a longitudinal axis of the turbine module in a direction of rotation, wherein, in relation to the bypass flow in the hot gas duct, the flow bypass structures each have a leading edge, and, downstream thereto, a trailing edge, and the second flow bypass structure is provided as a deflecting blade, wherein the second flow bypass structure has a smaller profile thickness than the first flow bypass structure, and wherein the hot gas duct is enclosed by a radial width.Type: ApplicationFiled: December 13, 2018Publication date: June 20, 2019Applicant: MTU Aero Engines AGInventors: Guenter Ramm, Martin Hoeger, Irene Raab, Yavuz Guendogdu
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Publication number: 20190048725Abstract: A blade (10) for a turbomachine is provided. In at least one cross section disposed orthogonally to a longitudinal blade axis, an outer surface of the blade forms a curve (?) that runs continuously on the inflow side along an at least approximate ellipse (E) between a first separation point (P1) and a second separation point (P2). On the pressure side 12, the curve (?) has an inflection point W. A distance of the second separation point (P2) from the inflection point W along the curve is at least exactly equal, at least twice as great, at least three times as great, or even at least five times as great as a distance of the second separation point (P2) from the first separation point (P1) along the at least approximate ellipse (E). Also described is a blade ring having at least one blade of this kind, as well as a turbomachine.Type: ApplicationFiled: July 18, 2018Publication date: February 14, 2019Inventors: Guenter RAMM, Yavuz GUENDOGDU
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Publication number: 20190024521Abstract: The invention relates to a flow arrangement for placing in the hot gas duct of a turbomachine, having a first surrounding-flow structure and a second surrounding-flow structure, the surrounding-flow structures each having, in reference to the surrounding flow in the hot gas duct, a leading edge and, downstream thereof, a trailing edge, wherein the second surrounding-flow structure is provided as a deflecting blade with a suction side and a pressure side and has a lesser profile thickness than the first surrounding-flow structure, which is arranged on the suction side of the second surrounding-flow structure, and wherein, although the second surrounding-flow structure has a partial axial overlap with the first surrounding-flow structure referred to a longitudinal axis of the turbomachine, the trailing edge of the second surrounding-flow structure is, at the same time, displaced axially downstream relative to the trailing edge of the first surrounding-flow structure.Type: ApplicationFiled: July 17, 2018Publication date: January 24, 2019Applicant: MTU Aero Engines AGInventors: Martin Hoeger, Fadi Maatouk, Guenter Ramm, Yavuz Guendogdu, Irene Raab
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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
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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
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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
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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
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Publication number: 20130330180Abstract: A transition duct for a turbomachine, in particular an aircraft engine, for forming a flow channel between an upstream flow cross section and a downstream flow cross section, including supporting ribs which extend between a radially inner duct wall and a radially outer duct wall and each of which has a profile for deflecting a flow from an inlet area to an outlet area of the transition duct, the supporting ribs each having a profile variation in the area of their trailing edge and/or at least one blow-out opening for blowing out a fluid; also disclosed is a turbomachine having a transition duct of this type.Type: ApplicationFiled: May 29, 2013Publication date: December 12, 2013Inventors: Yavuz Guendogdu, Karl Engel