Patents by Inventor Stephan Klaen
Stephan Klaen 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: 11859504Abstract: A seal arrangement for sealing a gap between two housing parts, the gap being situated between opposite end faces of the housing parts. In the first housing part, there is a first receiving groove on the first end face, in which first receiving groove a sealing strip is arranged which protrudes out of the receiving groove and lies against a first outer flank. The sealing strip engages in an opposite second receiving groove of the second housing part and lies against a second outer flank. For position securing purposes and to achieve a sealing effect, even if there is no differential pressure, a spiral strip is provided, which spiral strip is situated in the first receiving groove and exerts an elastic force on the sealing strip.Type: GrantFiled: September 19, 2019Date of Patent: January 2, 2024Assignee: Siemens Energy Global GmbH & Co. KGInventors: Dirk Allebrod, Stephan Klän, Stephan Sonnen
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Publication number: 20220025783Abstract: A seal arrangement for sealing a gap between two housing parts, the gap being situated between opposite end faces of the housing parts. In the first housing part, there is a first receiving groove on the first end face, in which first receiving groove a sealing strip is arranged which protrudes out of the receiving groove and lies against a first outer flank. The sealing strip engages in an opposite second receiving groove of the second housing part and lies against a second outer flank. For position securing purposes and to achieve a sealing effect, even if there is no differential pressure, a spiral strip is provided, which spiral strip is situated in the first receiving groove and exerts an elastic force on the sealing strip.Type: ApplicationFiled: September 19, 2019Publication date: January 27, 2022Applicant: Siemens Energy Global GmbH & Co. KGInventors: Dirk Allebrod, Stephan Klän, Stephan Sonnen
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Patent number: 10287989Abstract: Disclosed is a turbomachine having an annular flow duct and a housing structure surrounding the flow duct and a multiplicity of guide vanes and rotor blades which are arranged in the flow duct. The rotor blades are rotatably accommodated in the housing structure whereas the guide vanes are fixed in the housing structure, a plurality of guide vanes forming an annular guide vane ring. The housing structure has a seal in the region of the radially inner flow duct boundary in order to prevent hot gas escaping from the flow duct, which seal is arranged on guide vane roots of the guide vanes of the guide vane ring via a seal support and forms a seal against a rotatable seal surface, the seal support being formed from an intermetallic material, in particular a TiAl material.Type: GrantFiled: January 28, 2014Date of Patent: May 14, 2019Assignee: MTU AERO ENGINES AGInventors: Frank Stiehler, Stephan Klaen, Stefan Busam, Bernhard Theis
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Patent number: 10047619Abstract: A seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. A turbo machine having a seal configuration (100) is also provided.Type: GrantFiled: November 4, 2014Date of Patent: August 14, 2018Assignee: MTU Aero Engines AGInventors: Andre Werner, Stephan Klaen, Manuel Hertter, Frank Stiehler
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Patent number: 10024192Abstract: A ceramic component for a turbomachine, the ceramic component (1) being configured to be destroyed in response to a contacting with another component (2) of the turbomachine that moves relative to the ceramic component (1). A turbomachine component pairing and a turbomachine including such a ceramic component.Type: GrantFiled: July 2, 2014Date of Patent: July 17, 2018Assignee: MTU Aero Engines AG & Co. KGInventors: Norbert Schinko, Janine Sangl, Stephan Klaen, Markus Schlemmer
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Patent number: 9920838Abstract: A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.Type: GrantFiled: July 2, 2015Date of Patent: March 20, 2018Assignee: MTU Aero Engines AGInventors: Stephan Klaen, Julian Weber, Frank Stiehler, Christoph Cernay, Thomas Hess
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Patent number: 9771896Abstract: The invention relates to a mixing device and a turbofan engine having such a mixing device 30 for mixing a first gas flow 40 with a second gas flow 50 in a turbofan engine 20, having an actuating device 95 and walls 60, which bound a channel 65 for the first gas flow 40 and a channel 70 lying radially outside for the second gas flow 50, the actuating device 95 comprising a coupling element 110 that is coupled to the walls (60), the actuating device 95 being designed to pivot the walls 60 between a first position and a second position disposed radially outside relative to the first position, the actuating device 95 comprising an adjusting ring 105 that can be rotated between a first rotating position and a second rotating position in the peripheral direction and that is joined to the coupling element 110.Type: GrantFiled: April 3, 2014Date of Patent: September 26, 2017Assignee: MTU AERO ENGINES AGInventors: Hermann Klingels, Stephan Klaen, Christian Scherer, Uwe Vogel
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Patent number: 9664141Abstract: A thrust deflecting device for deflecting a thrust stream is disclosed, which includes a flap system having a plurality of deflecting flaps, each of which is pivotable around its yaw axis, the flap system being situated between parallel control surfaces such as baffle plates which, together with the flap system, form a box structure, which is pivotable around a pivot axis running in the direction of the transverse axis for the purpose of deflecting the thrust stream in the pitch direction, an aircraft engine also being disclosed.Type: GrantFiled: June 9, 2014Date of Patent: May 30, 2017Assignee: MTU Aero Engines AGInventors: Hermann Klingels, Stephan Klaen, Christian Scherer, Uwe Vogel
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Patent number: 9617861Abstract: The invention relates to a guide vane arrangement and a method for mounting a guide vane. The guide vane arrangement has at least one guide vane having a radially inner journal, which engages in a borehole of a bushing. The bushing is disposed in a borehole of an inner ring segment. The journal is connected to the bushing in a rotation-resistant manner and a slide mounting is provided between the bushing and the inner ring borehole. For mounting the guide vane in an inner ring segment, the journal of the guide vane is introduced into the borehole of the bushing. Further, the journal is fastened to the bushing in a rotation-resistant manner, and the bushing is slide-mounted with the inner ring segment. The slide mounting is conducted prior to or simultaneously with or after the fastening of the journal to the bushing in a rotation-resistant manner.Type: GrantFiled: June 16, 2014Date of Patent: April 11, 2017Assignee: MTU AERO ENGINES AGInventors: Stephan Klaen, Norbert Schinko
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Publication number: 20160003360Abstract: A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.Type: ApplicationFiled: July 2, 2015Publication date: January 7, 2016Applicant: MTU Aero Engines AGInventors: Stephan KLAEN, Julian WEBER, Frank STIEHLER, Christoph CERNAY, Thomas HESS
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Publication number: 20150226155Abstract: A thrust deflecting device for deflecting a thrust stream is disclosed, which includes a flap system having a plurality of deflecting flaps, each of which is pivotable around its yaw axis, the flap system being situated between parallel control surfaces such as baffle plates which, together with the flap system, form a box structure, which is pivotable around a pivot axis running in the direction of the transverse axis for the purpose of deflecting the thrust stream in the pitch direction, an aircraft engine also being disclosed.Type: ApplicationFiled: June 9, 2014Publication date: August 13, 2015Inventors: Hermann Klingels, Stephan Klaen, Christian Scherer, Uwe Vogel
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Publication number: 20150125278Abstract: The present invention relates to a seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. The present invention further relates to a turbo machine having a seal configuration (100).Type: ApplicationFiled: November 4, 2014Publication date: May 7, 2015Inventors: Andre WERNER, Stephan Klaen, Manuel Hertter, Frank Stiehler
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Publication number: 20150016957Abstract: A ceramic component for a turbomachine, the ceramic component (1) being configured to be destroyed in response to a contacting with another component (2) of the turbomachine that moves relative to the ceramic component (1). A turbomachine component pairing and a turbomachine including such a ceramic component.Type: ApplicationFiled: July 2, 2014Publication date: January 15, 2015Inventors: Norbert Schinko, Janine Sangl, Stephan Klaen, Markus Schlemmer
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Publication number: 20150016984Abstract: The invention relates to a guide vane arrangement and a method for mounting a guide vane. The guide vane arrangement has at least one guide vane having a radially inner journal, which engages in a borehole of a bushing. The bushing is disposed in a borehole of an inner ring segment. The journal is connected to the bushing in a rotation-resistant manner and a slide mounting is provided between the bushing and the inner ring borehole. For mounting the guide vane in an inner ring segment, the journal of the guide vane is introduced into the borehole of the bushing. Further, the journal is fastened to the bushing in a rotation-resistant manner, and the bushing is slide-mounted with the inner ring segment. The slide mounting is conducted prior to or simultaneously with or after the fastening of the journal to the bushing in a rotation-resistant manner.Type: ApplicationFiled: June 16, 2014Publication date: January 15, 2015Inventors: Stephan Klaen, Norbert Schinko
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Publication number: 20140298772Abstract: The invention relates to a mixing device and a turbofan engine having such a mixing device 30 for mixing a first gas flow 40 with a second gas flow 50 in a turbofan engine 20, having an actuating device 95 and walls 60, which bound a channel 65 for the first gas flow 40 and a channel 70 lying radially outside for the second gas flow 50, the actuating device 95 comprising a coupling element 110 that is coupled to the walls (60), the actuating device 95 being designed to pivot the walls 60 between a first position and a second position disposed radially outside relative to the first position, the actuating device 95 comprising an adjusting ring 105 that can be rotated between a first rotating position and a second rotating position in the peripheral direction and that is joined to the coupling element 110.Type: ApplicationFiled: April 3, 2014Publication date: October 9, 2014Applicant: MTU Aero Engines AGInventors: Hermann Klingels, Stephan Klaen, Christian Scherer, Uwe Vogel
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Publication number: 20140227080Abstract: Disclosed is a turbomachine having an annular flow duct and a housing structure surrounding the flow duct and a multiplicity of guide vanes and rotor blades which are arranged in the flow duct. The rotor blades are rotatably accommodated in the housing structure whereas the guide vanes are fixed in the housing structure, a plurality of guide vanes forming an annular guide vane ring. The housing structure has a seal in the region of the radially inner flow duct boundary in order to prevent hot gas escaping from the flow duct, which seal is arranged on guide vane roots of the guide vanes of the guide vane ring via a seal support and forms a seal against a rotatable seal surface, the seal support being formed from an intermetallic material, in particular a TiAl material.Type: ApplicationFiled: January 28, 2014Publication date: August 14, 2014Applicant: MTU Aero Engines AGInventors: Frank STIEHLER, Stephan KLAEN, Stefan BUSAM, Bernhard THEIS
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Publication number: 20140044550Abstract: A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed.Type: ApplicationFiled: August 8, 2013Publication date: February 13, 2014Applicant: MTU Aero Engines AGInventors: Felix KERN, Frank Stiehler, Stephan Klaen