Patents by Inventor Klaus Pirker
Klaus Pirker 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: 10865651Abstract: The invention relates to a sealing assembly for a fluid kinetic machine, in particular for an aircraft engine, for sealing a radial gap between a rotor and a stator, including at least one sealing support for retaining and/or fixing at least one sealing element, wherein the sealing support includes a first and a second radial web extending in a radial extension direction as well as an axial web extending in an axial extension direction, firmly bonded to the radial webs, and the radial webs form a receptacle for receiving an element of the stator. Therein, the radial webs are formed as sheet elements formed elongated in radial direction, wherein a radially interior end of the radial webs is respectively firmly bonded, in particular welded, to a radially exterior surface of the axial web.Type: GrantFiled: November 7, 2018Date of Patent: December 15, 2020Assignees: MTU Aero Engines AG, Almecon Technologie GmbHInventors: Markus Schlemmer, Klaus Pirker, Ralph Kropp, Lorenz Vinke, Waldemar Wiebe
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Patent number: 10808561Abstract: The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.Type: GrantFiled: May 27, 2018Date of Patent: October 20, 2020Assignee: MTU Aero Engines AGInventors: Markus Schlemmer, Klaus Pirker, Lukasz Sosnowka, Bernd Kislinger, Rudolf Stanka, Marcin Regulski
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Patent number: 10428656Abstract: The present invention relates to a gas turbine, in particular an aircraft engine gas turbine having a shaft and a bladed turbine rotor joined therewith that has a first rotor segment which has a downstream rotating cascade of the turbine rotor and bounds a first space in the radial direction, this first space communicating with a first gas passage disposed in the shaft, and has a second rotor segment axially adjacent to the first rotor segment, which has at least one second rotating cascade of the turbine rotor and bounds in the radial direction a second space axially adjacent to the first space, this second space communicating with a second gas passage, wherein the first rotor segment has at least one first discharge opening for the discharge of gas from the first space upstream of the furthest downstream rotating cascade.Type: GrantFiled: July 19, 2016Date of Patent: October 1, 2019Assignee: MTU Aero Engines AGInventors: Klaus Pirker, Christoph Lauer
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Publication number: 20190136705Abstract: The invention relates to a sealing assembly for a fluid kinetic machine, in particular for an aircraft engine, for sealing a radial gap between a rotor and a stator, including at least one sealing support for retaining and/or fixing at least one sealing element, wherein the sealing support includes a first and a second radial web extending in a radial extension direction as well as an axial web extending in an axial extension direction, firmly bonded to the radial webs, and the radial webs form a receptacle for receiving an element of the stator. Therein, the radial webs are formed as sheet elements formed elongated in radial direction, wherein a radially interior end of the radial webs is respectively firmly bonded, in particular welded, to a radially exterior surface of the axial web.Type: ApplicationFiled: November 7, 2018Publication date: May 9, 2019Applicants: MTU Aero Engines AG, ALMECON TECHNOLOGIE GMBHInventors: Markus Schlemmer, Klaus Pirker, Ralph Kropp, Lorenz Vinke, Waldemar Wiebe
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Publication number: 20180340435Abstract: The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.Type: ApplicationFiled: May 27, 2018Publication date: November 29, 2018Applicant: MTU Aero Engines AGInventors: Markus Schlemmer, Klaus Pirker, Lukasz Sosnowka, Bernd Kislinger, Rudolf Stanka, Marcin Regulski
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Publication number: 20170030196Abstract: The present invention relates to a gas turbine, in particular an aircraft engine gas turbine having a shaft and a bladed turbine rotor joined therewith that has a first rotor segment which has a downstream rotating cascade of the turbine rotor and bounds a first space in the radial direction, this first space communicating with a first gas passage disposed in the shaft, and has a second rotor segment axially adjacent to the first rotor segment, which has at least one second rotating cascade of the turbine rotor and bounds in the radial direction a second space axially adjacent to the first space, this second space communicating with a second gas passage, wherein the first rotor segment has at least one first discharge opening for the discharge of gas from the first space upstream of the furthest downstream rotating cascade.Type: ApplicationFiled: July 19, 2016Publication date: February 2, 2017Inventors: Klaus Pirker, Christoph Lauer
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Patent number: 9470103Abstract: The turbomachine includes a mid turbine vane frame, with an annular compartment formed between the mid turbine vane frame and a low-pressure turbine casing being sealed by means of at least two ring seals, wherein one ring seal is in contact with the mid turbine vane frame and the other ring seal is in contact with the low-pressure turbine casing and a radial annular overlap is thereby created with the first-mentioned ring seal.Type: GrantFiled: December 4, 2013Date of Patent: October 18, 2016Assignee: MTU AERO ENGINES AGInventor: Klaus Pirker
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Publication number: 20140161607Abstract: The turbomachine includes a mid turbine vane frame, with an annular compartment formed between the mid turbine vane frame and a low-pressure turbine casing being sealed by means of at least two ring seals, wherein one ring seal is in contact with the mid turbine vane frame and the other ring seal is in contact with the low-pressure turbine casing and a radial annular overlap is thereby created with the first-mentioned ring seal.Type: ApplicationFiled: December 4, 2013Publication date: June 12, 2014Applicant: MTU Aero Engines AGInventor: Klaus Pirker
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Patent number: 8601881Abstract: Described is a material sample for testing material properties under biaxial load as well as a method therefor. The material sample has a circular disk shape and, for rotation about the center line thereof, is provided with an integrally formed hub. The edge of the material sample and the hub are thicker than the ring section of the material sample located in between. In one embodiment, the ring section is designed with an annular concave fillet concentric to the hub and the concave fillet may extend from the edge to the hub and have a continuous curvature over its width. In the method, it is rotated about its center line at least at 100,000 rpm, preferably at 150,000 rpmĀ±10,000 rpm.Type: GrantFiled: August 1, 2009Date of Patent: December 10, 2013Assignee: MTU Aero Engines GmbHInventor: Klaus Pirker
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Publication number: 20110138925Abstract: Described is a material sample for testing material properties under biaxial load as well as a method therefor. The material sample has a circular disk shape and, for rotation about the center line thereof, is provided with an integrally formed hub. The edge of the material sample and the hub are thicker than the ring section of the material sample located in between. In one embodiment, the ring section is designed with an annular concave fillet concentric to the hub and the concave fillet may extend from the edge to the hub and have a continuous curvature over its width. In the method, it is rotated about its center line at least at 100,000 rpm, preferably at 150,000 rpmĀ±10,000 rpm.Type: ApplicationFiled: August 1, 2009Publication date: June 16, 2011Applicant: MTU AERO ENGINES GMBHInventor: Klaus Pirker
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Patent number: 7367775Abstract: A rotor comprising several blades rotating together with the rotor, particularly running blades, and the blades forming at least one blade ring, is disclosed. The blades within the, or each, blade ring are arranged at a different distance from one another.Type: GrantFiled: June 3, 2004Date of Patent: May 6, 2008Assignee: MTU Aero Engines GmbHInventors: Hans-Peter Borufka, Klaus Pirker
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Publication number: 20060275127Abstract: A rotor comprising several blades rotating together with the rotor, particularly running blades, and the blades forming at least one blade ring, is disclosed. The blades within the, or each, blade ring are arranged at a different distance from one another.Type: ApplicationFiled: June 3, 2004Publication date: December 7, 2006Inventors: Hans-Peter Borufka, Klaus Pirker
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Patent number: 5288020Abstract: Apparatus for sealing the side edges of flaps of a propulsion nozzle of an engine and the walls of a casing of the nozzle by sealing elements carried by the flaps and extending across a clearance between the side edges of the flaps and the walls. The sealing elements are carried in slots in the side edges of the flaps with clearance for capability of movement towards the walls. The sealing elements contact the walls to form a primary seal therewith. The flaps are formed with chambers carrying a pressure medium and plungers are supported in the flaps for being subjected to the pressure of the pressure medium and bearing against the sealing elements to urge the sealing elements against the surfaces of the walls. A differential pressure exists on both sides of the flaps and acts on the sealing elements in the clearance to press the sealing elements against respective side surfaces of the slots to form a secondary seal thereat.Type: GrantFiled: March 29, 1993Date of Patent: February 22, 1994Assignee: MTU Motoren-und Turbinen-Union Munchen GmbHInventor: Klaus Pirker