Patents by Inventor Christoph Lauer
Christoph Lauer 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: 20240092687Abstract: A lithium aluminum silicate (LAS) glass-ceramic has an average coefficient of thermal expansion (CTE) in a range from 0 to 50° C. of at most 0±0.1×10?6/K and a thermal hysteresis at least in a temperature range from 15° C. to 35° C. of <0.1 ppm. The LAS glass-ceramic includes (in mol % based on oxide): SiO2 60-<70; Li2O 7-9.6; MgO+ZnO>0.5-1.5; R2O>0.5, where R2O is Na2O and/or K2O and/or Cs2O and/or Rb2O; and nucleating agent with a content of 1.5 to 6 mol %. The nucleating agent is at least one component selected from the group consisting of TiO2, ZrO2, Ta2O5, Nb2O5, SnO2, MoO3, WO3 and HfO2.Type: ApplicationFiled: September 15, 2023Publication date: March 21, 2024Applicant: Schott AGInventors: Ina Mitra, Sonja Lauer, Clemens Kunisch, Christoph Gross
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Patent number: 10876418Abstract: Described is a turbine center frame for a gas turbine, in particular an aircraft gas turbine, the turbine center frame having a radially inner wall and a radially outer wall bounding an annular space through which hot gas flows and each having a contour facing the annular space, the contours describing an inner annular space curve along the inner wall and an outer annular space curve along the outer wall. At least one vane element extends in the radial direction through the annular space and has an axial leading edge and an axial trailing edge, the vane element having an outer axial width.Type: GrantFiled: May 17, 2019Date of Patent: December 29, 2020Assignee: MTU Aero Engines AGInventors: Markus Brettschneider, Christoph Lauer, Rudolf Stanka
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Patent number: 10844737Abstract: The present invention relates to a module for a turbomachine, having a guide vane arrangement and a seal carrier, which is arranged, with reference to a longitudinal axis of the module, radially inside an inner platform of the guide vane arrangement, wherein, in each case with reference to the longitudinal axis of the module, when considered in an axial section, the seal carrier has a radially extending seal carrier wall and a sealing web extending axially away from it, which forms a labyrinth seal together with the inner platform of the guide vane arrangement, wherein the seal carrier wall and the sealing web are made up in one piece with each other, i.e., they are built up additively together.Type: GrantFiled: January 28, 2019Date of Patent: November 24, 2020Assignee: MTU Aero Engines AGInventor: Christoph Lauer
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Patent number: 10655483Abstract: A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.Type: GrantFiled: December 1, 2016Date of Patent: May 19, 2020Assignee: MTU Aero Engines AGInventors: Markus Schlemmer, Martin Pernleitner, Manfred Dopfer, Marcus Woehler, Oliver Thiele, Bernd Kislinger, Norman Cleesattel, Christoph Lauer, Manfred Schill, Manuel Hein
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Patent number: 10590788Abstract: A device for influencing the temperatures in inner ring segments of a gas turbine is provided, which includes in the circumferential direction of the gas turbine, at least one outer shell assembly having a plurality of outer ring segments and at least one inner shell assembly having a plurality of inner ring segments. The inner ring segments are equal to or greater in number than the outer ring segments. An outer ring segment gap is between each two adjacent outer ring segments. An inner ring segment gap is between each two adjacent inner ring segments. An outer ring segment gap, or at least a radial cooling air passage, is located opposite each inner ring segment gap in the radial direction of the gas turbine.Type: GrantFiled: August 5, 2016Date of Patent: March 17, 2020Assignee: MTU Aero Engines AGInventor: Christoph Lauer
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Publication number: 20190360347Abstract: Described is a turbine center frame for a gas turbine, in particular an aircraft gas turbine, the turbine center frame having a radially inner wall and a radially outer wall bounding an annular space through which hot gas flows and each having a contour facing the annular space, the contours describing an inner annular space curve along the inner wall and an outer annular space curve along the outer wall. At least one vane element extends in the radial direction through the annular space and has an axial leading edge and an axial trailing edge, the vane element having an outer axial width.Type: ApplicationFiled: May 17, 2019Publication date: November 28, 2019Inventors: Markus BRETTSCHNEIDER, Christoph LAUER, Rudolf STANKA
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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: 20190234225Abstract: The present invention relates to a module for a turbomachine, having a guide vane arrangement and a seal carrier, which is arranged, with reference to a longitudinal axis of the module, radially inside an inner platform of the guide vane arrangement, wherein, in each case with reference to the longitudinal axis of the module, when considered in an axial section, the seal carrier has a radially extending seal carrier wall and a sealing web extending axially away from it, which forms a labyrinth seal together with the inner platform of the guide vane arrangement, wherein the seal carrier wall and the sealing web are made up in one piece with each other, i.e., they are built up additively together.Type: ApplicationFiled: January 28, 2019Publication date: August 1, 2019Applicant: MTU Aero Engines AGInventor: Christoph Lauer
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Patent number: 9829130Abstract: An adapter for connecting a fluid line to a housing section of a turbomachine is disclosed. A lower and an upper pair of flanges are arranged offset from each other about a channel axis of a fluid channel and are arranged without a space between each other in a direction of the channel axis, where the feed-throughs of the upper pair of flanges are open circumferentially.Type: GrantFiled: May 21, 2014Date of Patent: November 28, 2017Assignee: MTU AERO ENGINES AGInventors: Stefan Rauscher, Christoph Lauer
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Patent number: 9752455Abstract: A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.Type: GrantFiled: October 7, 2014Date of Patent: September 5, 2017Assignee: MTU Aero Engines AGInventors: Rudolf Stanka, Christoph Lauer, Hans Stricker
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Publication number: 20170159464Abstract: A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.Type: ApplicationFiled: December 1, 2016Publication date: June 8, 2017Inventors: Markus Schlemmer, Martin Pernleitner, Manfred Dopfer, Marcus Woehler, Oliver Thiele, Bernd Kislinger, Norman Cleesattel, Christoph Lauer, Manfred Schill, Manuel Hein
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Publication number: 20170138209Abstract: A device for influencing the temperatures in inner ring segments of a gas turbine is provided, which includes in the circumferential direction of the gas turbine, at least one outer shell assembly having a plurality of outer ring segments and at least one inner shell assembly having a plurality of inner ring segments. The inner ring segments are equal to or greater in number than the outer ring segments. An outer ring segment gap is between each two adjacent outer ring segments. An inner ring segment gap is between each two adjacent inner ring segments. An outer ring segment gap, or at least a radial cooling air passage, is located opposite each inner ring segment gap in the radial direction of the gas turbine.Type: ApplicationFiled: August 5, 2016Publication date: May 18, 2017Inventor: Christoph Lauer
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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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Publication number: 20160131028Abstract: A gas turbine, in particular an aircraft engine, including a core flow channel (K), in which a first compressor (20), a second compressor (40) adjacent downstream from the first compressor, a combustion chamber (60) adjacent downstream from the second compressor, a second turbine (50) adjacent downstream from the combustion chamber, which is coupled to the second compressor, and a first turbine (30) adjacent downstream from the second turbine, which is coupled to the first compressor via a first transmission (71), are situated; a quotient (r/R) of an inside diameter (r) of the core flow channel divided by an outside diameter (R) of the core flow channel at an upstream inflow of the first compressor being at most 0.65, in particular at most 0.5 is provided.Type: ApplicationFiled: November 6, 2015Publication date: May 12, 2016Inventors: Christoph Lauer, Winfried Lauer
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Publication number: 20150098799Abstract: A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.Type: ApplicationFiled: October 7, 2014Publication date: April 9, 2015Inventors: Rudolf Stanka, Christoph Lauer, Hans Stricker
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Publication number: 20140346768Abstract: An adapter for connecting a fluid line to a housing section of a turbomachine is disclosed. A lower and an upper pair of flanges are arranged offset from each other about a channel axis of a fluid channel and are arranged without a space between each other in a direction of the channel axis, where the feed-throughs of the upper pair of flanges are open circumferentially.Type: ApplicationFiled: May 21, 2014Publication date: November 27, 2014Applicant: MTU Aero Engines AGInventors: Stefan Rauscher, Christoph Lauer