Patents by Inventor Krzysztof Skura
Krzysztof Skura 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: 11725518Abstract: A method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.Type: GrantFiled: February 8, 2021Date of Patent: August 15, 2023Assignee: MTU Aero Engines AGInventors: Krzysztof Skura, Martin Pernleitner, Christian Eichler, Lutz Friedrich
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Patent number: 11585225Abstract: The invention refers to a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade having an outer surface having at least one circumferential web arranged thereon, at least one pocket recessed in the outer surface and a hardfacing provided on at least one edge of the shroud wherein a pocket recessed in the outer surface is arranged adjacent to the hardfacing and a side face of the pocket joins the supporting wall with a radius corresponding at least to the length of the shorter extension of the supporting wall and at most to 1.5 times the length of the larger extension of the supporting wall.Type: GrantFiled: February 9, 2021Date of Patent: February 21, 2023Assignee: MTU Aero Engines AGInventors: Krzysztof Skura, Christian Eichler, Lutz Friedrich
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Publication number: 20210246793Abstract: The invention refers to a method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.Type: ApplicationFiled: February 8, 2021Publication date: August 12, 2021Applicant: MTU Aero Engines AGInventors: Krzysztof Skura, Martin Pernleitner, Christian Eichler, Lutz Friedrich
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Publication number: 20210246794Abstract: The invention refers to a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade having an outer surface having at least one circumferential web arranged thereon, at least one pocket recessed in the outer surface and a hardfacing provided on at least one edge of the shroud wherein a pocket recessed in the outer surface is arranged adjacent to the hardfacing and a side face of the pocket joins the supporting wall with a radius corresponding at least to the length of the shorter extension of the supporting wall and at most to 1.5 times the length of the larger extension of the supporting wall.Type: ApplicationFiled: February 9, 2021Publication date: August 12, 2021Applicant: MTU Aero Engines AGInventors: Krzysztof Skura, Christian Eichler, Lutz Friedrich
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Patent number: 10544687Abstract: The present invention relates to an improved cast-to-size gas turbine blade comprising a blade tip shroud with a stiffening rib extending outwardly from the section of the outer side of the shroud platform located between the upstream sealing fin and the upstream edge. The stiffening rib having substantially planar top surface in form of a trapezium, and two sloping sidewalls extending between the upstream sealing fin and the upstream edge on each side of the top surface and connecting said top surface with adjacent surface of the outer side of the shroud platform. The form of the stiffening rib allows to obtain an improved shroud configuration of reduced overall blade mass, capable of providing sufficient stiffening of the shroud, reducing vibrations of the shroud platform, creep curling of the shroud edges and bending stress at the intersection of the airfoil and of the shroud.Type: GrantFiled: July 10, 2017Date of Patent: January 28, 2020Assignee: MTU Aero Engines AGInventors: Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
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Patent number: 10400611Abstract: The invention relates to a blade for a turbomachine a shroud for such a blade, and a turbomachine having at least one such blade. The blade comprises a shroud which is positioned on the blade tip side of the blade and is stiffened in the region of its surface by means of a stiffening structure having at least one longitudinal stiffening element such as a rib. The height of the longitudinal stiffening element varies in the circumferential direction.Type: GrantFiled: January 28, 2016Date of Patent: September 3, 2019Assignee: MTU AERO ENGINES AGInventors: Marcin Kozdras, Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
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Patent number: 9951631Abstract: A rotor blade for a turbomachine, including an airfoil (1) for flow deflection, a blade root (2) for attachment to a rotor of the turbomachine, an inner platform (3) between the airfoil and the blade root, and at least one pocket (4, 5) defined by two axially spaced walls (4.1, 4.2; 5.1, 5.2) extending from the side of the platform opposite the airfoil toward the blade root. A first (4.1, 5.1) of these walls has an outer side (4.1A, 5.1A) that faces away from the pocket and, in at least one cross section perpendicular to a radial longitudinal axis of the rotor blade, slopes outwardly.Type: GrantFiled: June 26, 2014Date of Patent: April 24, 2018Assignee: MTU Aero Engines AGInventors: Krzysztof Skura, Marcin Kozdras, Lukasz Sosnowka, Manfred Feldmann, Manfred Schill
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Publication number: 20180016918Abstract: The present invention relates to an improved cast-to-size gas turbine blade comprising a blade tip shroud with a stiffening rib extending outwardly from the section of the outer side of the shroud platform located between the upstream sealing fin and the upstream edge. The stiffening rib having substantially planar top surface in form of a trapezium, and two sloping sidewalls extending between the upstream sealing fin and the upstream edge on each side of the top surface and connecting said top surface with adjacent surface of the outer side of the shroud platform. The form of the stiffening rib allows to obtain an improved shroud configuration of reduced overall blade mass, capable of providing sufficient stiffening of the shroud, reducing vibrations of the shroud platform, creep curling of the shroud edges and bending stress at the intersection of the airfoil and of the shroud.Type: ApplicationFiled: July 10, 2017Publication date: January 18, 2018Applicant: MTU Aero Engines AGInventors: Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
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Publication number: 20160237829Abstract: The invention relates to a blade for a turbomachine a shroud for such a blade, and a turbomachine having at least one such blade. The blade comprises a shroud which is positioned on the blade tip side of the blade and is stiffened in the region of its surface by means of a stiffening structure having at least one longitudinal stiffening element such as a rib. The height of the longitudinal stiffening element varies in the circumferential direction.Type: ApplicationFiled: January 28, 2016Publication date: August 18, 2016Inventors: Marcin KOZDRAS, Krzysztof SKURA, Piotr LEBIEDOWICZ, Marek SZPONAR
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Publication number: 20150003988Abstract: A rotor blade for a turbomachine, including an airfoil (1) for flow deflection, a blade root (2) for attachment to a rotor of the turbomachine, an inner platform (3) between the airfoil and the blade root, and at least one pocket (4, 5) defined by two axially spaced walls (4.1, 4.2; 5.1, 5.2) extending from the side of the platform opposite the airfoil toward the blade root. A first (4.1, 5.1) of these walls has an outer side (4.1A, 5.1A) that faces away from the pocket and, in at least one cross section perpendicular to a radial longitudinal axis of the rotor blade, slopes outwardly.Type: ApplicationFiled: June 26, 2014Publication date: January 1, 2015Inventors: Krzysztof Skura, Marcin Kozdras, Lukasz Sosnowka, Manfred Feldmann, Manfred Schill