Patents by Inventor JANINE SANGL
JANINE SANGL 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: 11008946Abstract: A sealing assembly for sealing a first sealing bank of a first static component and a second sealing bank of a second static component of an axial turbomachine, the static components axially movable relative to each other, the sealing assembly including the two static components and a sealing element segmented in the circumferential direction, a first end of the sealing element being axially coupled in a groove at the first sealing bank facing an opposite second end bearing axially against the second sealing bank, as well as a stator vane assembly including a casing component of an axial turbomachine, which has at least one casing hook, and further including a stator vane component having at least one stator vane disposed on a platform and at least one stator vane hook which projects from the platform and bears against the casing hook, the stator vane hook having formed therein at least one through-hole for supply of cooling air.Type: GrantFiled: June 19, 2019Date of Patent: May 18, 2021Assignee: MTU Aero Engines AGInventors: Manfred Feldmann, Janine Sangl, Armin Kammerer
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Publication number: 20200011249Abstract: A sealing assembly for sealing a first sealing bank of a first static component and a second sealing bank of a second static component of an axial turbomachine, the static components axially movable relative to each other, the sealing assembly including the two static components and a sealing element segmented in the circumferential direction, a first end of the sealing element being axially coupled in a groove at the first sealing bank facing an opposite second end bearing axially against the second sealing bank, as well as a stator vane assembly including a casing component of an axial turbomachine, which has at least one casing hook, and further including a stator vane component having at least one stator vane disposed on a platform and at least one stator vane hook which projects from the platform and bears against the casing hook, the stator vane hook having formed therein at least one through-hole for supply of cooling air.Type: ApplicationFiled: June 19, 2019Publication date: January 9, 2020Inventors: Manfred FELDMANN, Janine SANGL, Armin KAMMERER
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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: 9945241Abstract: The present invention relates to a sealing element (100) of an axial turbomachine for the sealing of regions at or in at least two static components of the turbomachine, wherein the components can be moved axially relative to one another. The sealing element (100) has a first radial region (1) with a first stiffness or rigidity and a second radial region (5) with a second stiffness or rigidity, wherein the first stiffness and the second stiffness are different from one another, and the sealing element (100) is configured as segmented in the peripheral direction of the turbomachine.Type: GrantFiled: September 24, 2014Date of Patent: April 17, 2018Assignee: MTU AERO ENGINES AGInventors: Manfred Feldmann, Janine Sangl
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Patent number: 9835039Abstract: A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall (1) and an inner wall (2) defining the flow channel; and a hollow space (4) being formed between the inner wall and the outer housing wall. The hollow space is separable into at least two regions (5, 6); a movable wire element (slide ring seal) (10, 10?), which is adapted to rest against the contact faces (8, 9), being configured in the hollow space for purposes of the separation.Type: GrantFiled: April 9, 2014Date of Patent: December 5, 2017Assignee: MTU Aero Engines AGInventors: Manfred Feldmann, Norbert Schinko, Janine Sangl
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Patent number: 9664057Abstract: A stator vane segment (100) of a fluid flow machine, having an upstream casing-side attachment (1) and/or a downstream casing-side attachment (3), and a platform (5). The attachments are provided on the platform (5). The platform (5) has a first sealing section (17) and extends in the direction of flow beyond a connection region (15) that connects the rearward attachment (3) to the platform (5). The first sealing section (17) that is located in a section (18) downstream of the connection region (15) has a first slot (19) which is continuous in the circumferential direction. The present invention also relates to a turbine having at least one stator vane segment (100).Type: GrantFiled: June 4, 2014Date of Patent: May 30, 2017Assignee: MTU Aero Engines AGInventors: Manfred Feldmann, Norbert Schinko, Janine Sangl, Alexander Buck
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Patent number: 9605551Abstract: A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine.Type: GrantFiled: October 8, 2013Date of Patent: March 28, 2017Assignee: MTU Aero Engines AGInventors: Manfred Feldmann, Janine Sangl, Sebastian Kaltenbach, Joachim Lorenz
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Patent number: 9506368Abstract: A housing structure for a turbomachine having a stationary blade ring annularly surrounding a flow channel, and having a seal carrier ring which also annularly surrounds the flow channel, the stationary blade ring and the seal carrier ring being connected to each other, and either the stationary blade ring or the seal carrier ring having a one-sidedly open receptacle in the radial direction in relation to the flow channel and a radially projecting engagement area which corresponds to the connected seal carrier ring or stationary blade ring and which is held in a form-fitting manner in the axial direction and in the radial direction in the direction of the closed side of the receptacle but is freely movable with respect to the connected receptacle and the seal carrier ring or stationary blade ring having this receptacle in the radially opposite direction in the direction of the receptacle opening.Type: GrantFiled: October 28, 2013Date of Patent: November 29, 2016Assignee: MTU Aero Engines AGInventors: Manfred Feldmann, Janine Sangl, Norbert Schinko
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Patent number: 9416672Abstract: A housing structure for a turbo-engine, especially for a gas turbine or an aircraft engine, includes an outer housing wall and an inner housing wall, the inner and outer housing walls annularly enclosing a flow channel for the turbo-engine and being spaced apart radially from the flow channel. At least one heat shield is arranged between the inner and outer housing walls, and a bar or a fixture projects at least somewhat radially from the inner housing wall. The bar or the fixture has on at least one side a broadening element that includes a sealing face against which the heat shield is positioned in a sealing manner.Type: GrantFiled: October 11, 2013Date of Patent: August 16, 2016Assignee: MTU AERO ENGINES AGInventors: Manfred Feldmann, Janine Sangl, Sebastian Kaltenbach, Joachim Lorenz
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Publication number: 20150102565Abstract: The present invention relates to a sealing element (100) of an axial turbomachine for the sealing of regions at or in at least two static components of the turbomachine, wherein the components can be moved axially relative to one another. The sealing element (100) has a first radial region (1) with a first stiffness or rigidity and a second radial region (5) with a second stiffness or rigidity, wherein the first stiffness and the second stiffness are different from one another, and the sealing element (100) is configured as segmented in the peripheral direction of the turbomachine.Type: ApplicationFiled: September 24, 2014Publication date: April 16, 2015Inventors: Manfred Feldmann, Janine Sangl
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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: 20140321969Abstract: A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall (1) and an inner wall (2) defining the flow channel; and a hollow space (4) being formed between the inner wall and the outer housing wall. The hollow space is separable into at least two regions (5, 6); a movable wire element (slide ring seal) (10, 10?), which is adapted to rest against the contact faces (8, 9), being configured in the hollow space for purposes of the separation.Type: ApplicationFiled: April 9, 2014Publication date: October 30, 2014Applicant: MTU Aero Engines AGInventors: Manfred Feldmann, Norbert Schinko, Janine Sangl
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Publication number: 20140119902Abstract: A housing structure for a turbomachine having a stationary blade ring annularly surrounding a flow channel, and having a seal carrier ring which also annularly surrounds the flow channel, the stationary blade ring and the seal carrier ring being connected to each other, and either the stationary blade ring or the seal carrier ring having a one-sidedly open receptacle in the radial direction in relation to the flow channel and a radially projecting engagement area which corresponds to the connected seal carrier ring or stationary blade ring and which is held in a form-fitting manner in the axial direction and in the radial direction in the direction of the closed side of the receptacle but is freely movable with respect to the connected receptacle and the seal carrier ring or stationary blade ring having this receptacle in the radially opposite direction in the direction of the receptacle opening.Type: ApplicationFiled: October 28, 2013Publication date: May 1, 2014Inventors: Manfred Feldmann, Janine Sangl, Norbert Schinko
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Publication number: 20140112768Abstract: A component combination for a shell of a flow channel (10) of a turbomachine, in particular for a housing of a gas turbine or an aircraft engine, including at least two components, a first component (1) forming a closed ring. The closed ring is axially and/or radially held in a form-fitting manner against at least one second component (2) in relation to the flow channel and is able to be removed from or placed into this position only by elastically deforming the ring without changing the second component; the present invention also includes a method for manufacturing a component combination of this type and a corresponding turbomachine having a component combination of this type.Type: ApplicationFiled: October 16, 2013Publication date: April 24, 2014Inventors: Manfred Feldmann, Janine Sangl, Norbert Schinko
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Publication number: 20140105731Abstract: A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine.Type: ApplicationFiled: October 8, 2013Publication date: April 17, 2014Inventors: Manfred Feldmann, Janine Sangl, Sebastian Kaltenbach, Joachim Lorenz
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Publication number: 20140102107Abstract: A housing structure for a turbo-engine, especially for a gas turbine or an aircraft engine, includes an outer housing wall and an inner housing wall, the inner and outer housing walls annularly enclosing a flow channel for the turbo-engine and being spaced apart radially from the flow channel. At least one heat shield is arranged between the inner and outer housing walls, and a bar or a fixture projects at least somewhat radially from the inner housing wall. The bar or the fixture has on at least one side a broadening element that includes a sealing face against which the heat shield is positioned in a sealing manner.Type: ApplicationFiled: October 11, 2013Publication date: April 17, 2014Inventors: MANFRED FELDMANN, JANINE SANGL, SEBASTIAN KALTENBACH, JOACHIM LORENZ