Patents by Inventor Inga Mahle
Inga Mahle 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: 10934849Abstract: Described are an airfoil array segment (100, 200, 300) having at least two airfoils (20, 30) and a platform (10) that features an axis asymmetrical platform surface (12). This platform surface features an elevation (110, 210, 310) that extends from the pressure side (21) of the first to the suction side (32) of the second airfoil (30). A highest point (111, 211, 311) of the elevation is more proximate to the suction side 32 of the second airfoil (30) than to the pressure side (21) of the first airfoil (20). Also described are an airfoil, a platform, an airfoil passage and a turbomachine.Type: GrantFiled: May 14, 2018Date of Patent: March 2, 2021Assignee: MTU Aero Engines AGInventors: Markus Brettschneider, Inga Mahle, Fadi Maatouk
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Patent number: 10876410Abstract: An airfoil array for a turbomachine, in particular a turbine or compressor stage of a gas turbine.Type: GrantFiled: July 11, 2018Date of Patent: December 29, 2020Assignee: MTU Aero Engines AGInventors: Inga Mahle, Markus Brettschneider, Fadi Maatouk
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Patent number: 10753206Abstract: A blade/vane cascade segment of a blade/vane cascade for a turbomachine is disclosed, which comprises a stage with a stage surface as well as a first blade/vane element and a second blade/vane element. The stage surface comprises a first elevation reaching as far as the pressure side of the first blade/vane element and a second elevation reaching as far as the suction side of the second blade/vane element. A furthest downstream point of a boundary of the second elevation has an axial position which differs from the axial position of at least one highest point of the first elevation by a maximum of 10% of an axial cascade span. Furthermore, a blade/vane cascade, a blade/vane channel, a stage, a turbomachine and an aircraft engine are disclosed.Type: GrantFiled: April 9, 2018Date of Patent: August 25, 2020Assignee: MTU Aero Engines AGInventors: Markus Brettschneider, Inga Mahle, Fadi Maatouk
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Patent number: 10704393Abstract: Disclosed is an airfoil array segment (110, 120, 130, 140, 150) of an airfoil array for a turbomachine, the airfoil array segment including a platform (10) having a platform surface, as well as at least two airfoils (20, 30). The platform surface has a depression (111, 121, 131, 141, 151) which extends up to the first airfoil and contacts the pressure side (21) of the first airfoil downstream of 80% of the axial chord (g) downstream of the leading edges (23, 33) and which contacts the pressure side (21) of the first airfoil downstream up to no more than 80% of the axial chord (g) downstream of the leading edges (23, 33). At least one lowest point (112, 122) of the depression is located at least 90% of the axial chord (g) downstream of the leading edges (23, 33). Also disclosed are an airfoil array, an airfoil passage, a platform, a turbomachine, and an aircraft engine.Type: GrantFiled: May 9, 2018Date of Patent: July 7, 2020Assignee: MTU Aero Engines AGInventors: Fadi Maatouk, Markus Brettschneider, Inga Mahle
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Patent number: 10648339Abstract: A blade/vane cascade segment for a blade/vane cascade of a turbomachine includes a stage and at least two blade/vane elements that define a blade/vane intermediate strip with an axial cascade span on the stage surface by their leading and trailing edges. A stage edge on the inflow side has a contour with a depression. In the axial direction, this depression extends at most by 10% of the cascade span into the blade/vane intermediate strip. Also provided is a corresponding stage, a blade/vane cascade, a blade/vane channel, and a turbomachine.Type: GrantFiled: February 28, 2018Date of Patent: May 12, 2020Assignee: MTU Aero Engines AGInventors: Inga Mahle, Markus Brettschneider, Fadi Maatouk
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Patent number: 10590773Abstract: Disclosed is a blade/vane cascade segment of a blade/vane cascade of a turbomachine, which comprises at least two blade/vane elements defining an axial cascade width, and a stage with a stage surface, as well as a stage edge on the inflow side. The stage surface has an elevation extending up to the pressure side of a first blade/vane element and a depression extending up to the suction side of the other blade/vane. At least one highest point of the elevation and at least one lowest point of the depression each lie at least 30% and at most 60% of the axial cascade width downstream of the inflow edges of the blade/vane elements. In this case, the elevation and the depression each come close to the stage edge on the inflow side.Type: GrantFiled: February 2, 2018Date of Patent: March 17, 2020Assignee: MTU Aero Engines AGInventors: Markus Brettschneider, Inga Mahle
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Patent number: 10458248Abstract: A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite suction side of an adjacent airfoil that, in the radial direction of the turbomachine, is delimited by two opposing side walls, and whose extent in the axial direction of the turbomachine is delimited by leading edges and by trailing edges of airfoils; at least one of the side walls being provided with localized contours, of which at least two are formed as elevations and at least two as depressions; a saddle surface being formed between the contours that, in one rotation, alternately merges into an elevation and a depression; a blade cascade having such blade channels, as well as a turbomachine having such a blade cascade.Type: GrantFiled: November 30, 2016Date of Patent: October 29, 2019Assignee: MTU Aero Engines AGInventors: Nina Wolfrum, Markus Brettschneider, Inga Mahle, Markus Schlemmer, Martin Pernleitner
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Patent number: 10436044Abstract: The invention relates to a guide vane cluster for a turbomachine, in particular for a turbojet engine, having at least two vanes that are joined together by way of at least one common platform for the radial delimiting of a flow channel of the turbomachine, wherein each vane has a vane element with a suction side and a pressure side that are joined together by a leading edge and a trailing edge, wherein the at least two vanes have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.Type: GrantFiled: December 2, 2016Date of Patent: October 8, 2019Assignee: MTU Aero Engines AGInventors: Markus Schlemmer, Martin Pernleitner, Nina Wolfrum, Markus Brettschneider, Inga Mahle
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Publication number: 20190017384Abstract: An airfoil array for a turbomachine, in particular a turbine or compressor stage of a gas turbine.Type: ApplicationFiled: July 11, 2018Publication date: January 17, 2019Inventors: Inga MAHLE, Markus BRETTSCHNEIDER, Fadi MAATOUK
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Publication number: 20180328185Abstract: Disclosed is an airfoil array segment (110, 120, 130, 140, 150) of an airfoil array for a turbomachine, the airfoil array segment including a platform (10) having a platform surface, as well as at least two airfoils (20, 30). The platform surface has a depression (111, 121, 131, 141, 151) which extends up to the first airfoil and contacts the pressure side (21) of the first airfoil downstream of 80% of the axial chord (g) downstream of the leading edges (23, 33) and which contacts the pressure side (21) of the first airfoil downstream up to no more than 80% of the axial chord (g) downstream of the leading edges (23, 33). At least one lowest point (112, 122) of the depression is located at least 90% of the axial chord (g) downstream of the leading edges (23, 33). Also disclosed are an airfoil array, an airfoil passage, a platform, a turbomachine, and an aircraft engine.Type: ApplicationFiled: May 9, 2018Publication date: November 15, 2018Inventors: Fadi MAATOUK, Markus BRETTSCHNEIDER, Inga MAHLE
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Publication number: 20180328184Abstract: Described are an airfoil array segment (100, 200, 300) having at least two airfoils (20, 30) and a platform (10) that features an axis asymmetrical platform surface (12). This platform surface features an elevation (110, 210, 310) that extends from the pressure side (21) of the first to the suction side (32) of the second airfoil (30). A highest point (111, 211, 311) of the elevation is more proximate to the suction side 32 of the second airfoil (30) than to the pressure side (21) of the first airfoil (20). Also described are an airfoil, a platform, an airfoil passage and a turbomachine.Type: ApplicationFiled: May 14, 2018Publication date: November 15, 2018Inventors: Markus BRETTSCHNEIDER, Inga MAHLE, Fadi MAATOUK
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Publication number: 20180298761Abstract: A blade/vane cascade segment of a blade/vane cascade for a turbomachine is disclosed, which comprises a stage with a stage surface as well as a first blade/vane element and a second blade/vane element. The stage surface comprises a first elevation reaching as far as the pressure side of the first blade/vane element and a second elevation reaching as far as the suction side of the second blade/vane element. A furthest downstream point of a boundary of the second elevation has an axial position which differs from the axial position of at least one highest point of the first elevation by a maximum of 10% of an axial cascade span. Furthermore, a blade/vane cascade, a blade/vane channel, a stage, a turbomachine and an aircraft engine are disclosed.Type: ApplicationFiled: April 9, 2018Publication date: October 18, 2018Applicant: MTU Aero Engines AGInventors: Markus Brettschneider, Inga Mahle, Fadi Maatouk
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Publication number: 20180252107Abstract: A blade/vane cascade segment for a blade/vane cascade of a turbomachine includes a stage and at least two blade/vane elements that define a blade/vane intermediate strip with an axial cascade span on the stage surface by their leading and trailing edges. A stage edge on the inflow side has a contour with a depression. In the axial direction, this depression extends at most by 10% of the cascade span into the blade/vane intermediate strip. Also provided is a corresponding stage, a blade/vane cascade, a blade/vane channel, and a turbomachine.Type: ApplicationFiled: February 28, 2018Publication date: September 6, 2018Applicant: MTU Aero Engines AGInventors: Inga Mahle, Markus Brettschneider, Fadi Maatouk
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Publication number: 20180223670Abstract: Disclosed is a blade/vane cascade segment of a blade/vane cascade of a turbomachine, which comprises at least two blade/vane elements defining an axial cascade width, and a stage with a stage surface, as well as a stage edge on the inflow side. The stage surface has an elevation extending up to the pressure side of a first blade/vane element and a depression extending up to the suction side of the other blade/vane. At least one highest point of the elevation and at least one lowest point of the depression each lie at least 30% and at most 60% of the axial cascade width downstream of the inflow edges of the blade/vane elements. In this case, the elevation and the depression each come close to the stage edge on the inflow side. Also disclosed are a blade/vane cascade, a stage for a blade/vane cascade segment, a blade/vane channel, and a turbomachine.Type: ApplicationFiled: February 2, 2018Publication date: August 9, 2018Applicant: MTU Aero Engines AGInventors: Markus Brettschneider, Inga Mahle
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Patent number: 9920645Abstract: Disclosed is a sealing system for a turbomachine, in particular for a gas turbine, the sealing system being formed in an annular space between a flow-limiting wall of the turbomachine and at least one rotor blade tip of a rotor blade or an outer shroud arranged on the rotor blade tip, and comprising at least one sealing point. The sealing point comprises at least one run-in coating arranged on the rotor blade tip or on the outer shroud in the direction of the flow-limiting wall of the turbomachine. The invention furthermore encompasses a gas turbine comprising the sealing system.Type: GrantFiled: April 3, 2013Date of Patent: March 20, 2018Assignee: MTU AERO ENGINES GMBHInventors: Inga Mahle, Alexander Boeck
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Patent number: 9869184Abstract: A blade for a gas turbine has a leading edge and a trailing edge, which are connected by a pressure side and an intake side. In at least one segment of a stacking axis, the blade has a cross section with a profile with a common profile tangent at a leading edge region and a trailing edge region, a leading edge tangent at the leading edge, which is perpendicular to the common profile tangent, a trailing edge tangent at the trailing edge, which is perpendicular to the common profile tangent, and a camber line, which extends, at an equal distance from the pressure side and the intake side, from a center point of a leading edge circle, up to a center point of a trailing edge circle.Type: GrantFiled: April 2, 2015Date of Patent: January 16, 2018Assignee: MTU AERO ENGINES AGInventors: Norbert Huebner, Inga Mahle, Ulrich Haid, Kai Koerber
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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
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Publication number: 20170159443Abstract: The invention relates to a blade or vane ring for a gas turbine having a plurality of blades or vanes that are arranged next to one another in the peripheral direction (UR), wherein blades or vanes have a flow segment extending essentially in the radial direction, these blades or vanes having a convex suction side, a concave pressure side, a leading edge and a trailing edge, wherein the suction side and the pressure side are joined together by the leading edge and the trailing edge, wherein the blades or vanes transition into an annular segment of the blade or vane ring radially inside and/or radially outside, wherein annular segment connects a first blade or vane (12) and a second blade or vane, which are adjacent to one another, between the suction side of the first blade or vane and the pressure side of the second blade or vane.Type: ApplicationFiled: December 2, 2016Publication date: June 8, 2017Inventors: Martin Pernleitner, Inga Mahle, Nina Wolfrum, Markus Brettschneider, Markus Schlemmer
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Publication number: 20170159465Abstract: The invention relates to a guide vane cluster (10) for a turbomachine, in particular for a turbojet engine, having at least two vanes (14) that are joined together by way of at least one common platform (12, 16) for the radial delimiting of a flow channel of the turbomachine, wherein each vane (14) has a vane element (17) with a suction side (18) and a pressure side (20) that are joined together by a leading edge (22) and a trailing edge (24), wherein the at least two vanes (14) have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.Type: ApplicationFiled: December 2, 2016Publication date: June 8, 2017Inventors: Markus Schlemmer, Martin Pernleitner, Nina Wolfrum, Markus Brettschneider, Inga Mahle
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Publication number: 20170159444Abstract: A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite suction side of an adjacent airfoil that, in the radial direction of the turbomachine, is delimited by two opposing side walls, and whose extent in the axial direction of the turbomachine is delimited by leading edges and by trailing edges of airfoils; at least one of the side walls being provided with localized contours, of which at least two are formed as elevations and at least two as depressions; a saddle surface being formed between the contours that, in one rotation, alternately merges into an elevation and a depression; a blade cascade having such blade channels, as well as a turbomachine having such a blade cascade.Type: ApplicationFiled: November 30, 2016Publication date: June 8, 2017Inventors: Nina Wolfrum, Markus Brettschneider, Inga Mahle, Markus Schlemmer, Martin Pernleitner