Patents by Inventor Fadi Maatouk
Fadi Maatouk 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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Publication number: 20230383662Abstract: An airfoil array segment for an airfoil array of a turbomachine including a platform having a platform surface and an upstream-side platform edge, as well as at least two airfoils, whose leading and trailing edges define an inter-airfoil strip, the platform surface having a trough with a bottom configured such that the bottom is a global minimum and a radial position of the trough decreases relative to a reference surface in the circumferential direction from a suction side of one of the airfoils toward the pressure side of the adjacent other airfoil toward the bottom and from there increases in the circumferential direction, at most up to the radial position of the reference surface, and a radial position of the trough decreasing relative to a reference surface axially in the downstream direction toward the bottom and from there increasing axially in the downstream direction, at most up to the radial position of the reference surface, and the platform surface reaching at most a radial position of the referenType: ApplicationFiled: May 17, 2023Publication date: November 30, 2023Inventors: Markus BRETTSCHNEIDER, Fadi MAATOUK
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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: 11319820Abstract: The invention relates to a blade or vane, particularly of a turbine stage of a gas turbine, in particular of an aircraft gas turbine, having a blade or vane root and a blade or vane element joined to the blade or vane root, wherein the blade or vane element has a pressure side and a suction side, and wherein the blade or vane root has at least one raised region on its radial outer side facing the blade or vane element. It is proposed according to the invention that the blade or vane has a first raised region on the pressure side and a second raised region on the suction side, wherein the highest point of the first raised region is disposed essentially directly adjacent to the pressure side, and the highest point of the second raised region is disposed essentially directly adjacent to the suction side.Type: GrantFiled: June 21, 2017Date of Patent: May 3, 2022Assignee: MTU Aero Engines AGInventors: Markus Brettschneider, Fadi Maatouk
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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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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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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: 20170370234Abstract: The invention relates to a blade or vane, particularly of a turbine stage of a gas turbine, in particular of an aircraft gas turbine, having a blade or vane root and a blade or vane element joined to the blade or vane root, wherein the blade or vane element has a pressure side and a suction side, and wherein the blade or vane root has at least one raised region on its radial outer side facing the blade or vane element. It is proposed according to the invention that the blade or vane has a first raised region on the pressure side and a second raised region on the suction side, wherein the highest point of the first raised region is disposed essentially directly adjacent to the pressure side, and the highest point of the second raised region is disposed essentially directly adjacent to the suction side.Type: ApplicationFiled: June 21, 2017Publication date: December 28, 2017Inventors: Markus Brettschneider, Fadi Maatouk