Patents by Inventor Werner Humhauser
Werner Humhauser 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: 20150275683Abstract: An adjustable guide vane ring of a turbomachine having an inner ring, the guide vanes of which each have a radially inner vane disk with disk thickness increasing in the direction of flow and acting as a bearing pin; a guide vane, as well as an inner ring for such a guide vane ring, as well as a turbomachine are disclosed.Type: ApplicationFiled: March 30, 2015Publication date: October 1, 2015Inventors: Werner Humhauser, Hermann Klingels
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Publication number: 20150139811Abstract: Disclosed is a blade-disk assembly of a turbomachine, the blade-disk assembly having a plurality of adjacent rotor blades and a closure blade which are tilted into an anchoring groove, and at least one circumferential retention element which interlockingly cooperates with at least one blade, as well as a plurality of tilt-out prevention elements which are disposed between the groove base and the root portions and which, in the rest state, space the blades from the groove base when in the upper position. The blade-disk assembly further has a locking element, a portion of which is located between the groove base and the root portions and which, in the rest state, spaces the closure blade from the groove base when in the upper position. Also disclosed are a method for assembling such a blade-disk assembly, as well as a turbomachine.Type: ApplicationFiled: November 18, 2014Publication date: May 21, 2015Inventors: Werner Humhauser, Herman Klingels, Alexander Kloetzer
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Patent number: 8764390Abstract: The invention relates to a device (1) and to a method associated with an assembly mechanism for a rotor system of an axial turbo engine having a central tension anchor, as is particularly known from engine technology. To this end, the invention provides a tensioning tool that pre-tensions or biases the tension anchor prior to and during the insertion of the anchor into the compound rotor assembly. After inserting the biased tension anchor in the compound rotor assembly, the tension anchor is relaxed, whereby the anchor exercises a compressive force on the compound rotor assembly. According to a preferred embodiment, the compound rotor assembly is also biased (compressed) and relaxed after assembling the tension anchor, so that a desired nominal bias Sigmanominal can be particularly easily achieved. The use of a shaft locking nut is no longer necessary in the device according to the invention, thus avoiding the difficulties that are associated with the use of this nut, such as complexity and safety problems.Type: GrantFiled: December 2, 2009Date of Patent: July 1, 2014Assignee: MTU Aero Engines GmbHInventor: Werner Humhauser
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Publication number: 20140044526Abstract: Disclosed is an adjustable stationary blade ring of a turbomachine, whose stationary blades are each supported in a bearing body onto which an inner ring, which is divided into two half rings and acts as a seal carrier, is pushed without deformation, viewed in the circumferential direction, as well as a method for assembling a stationary blade ring of this type and a turbomachine having a stationary blade ring of this type.Type: ApplicationFiled: August 2, 2013Publication date: February 13, 2014Applicant: MTU Aero Engines AGInventor: Werner Humhauser
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Patent number: 8356741Abstract: The invention relates to a method for producing a blade tip plating (20) on a blade (10) for a turbomachine, in particular on a high-pressure rotating compressor blade for a gas turbine, comprising the following steps: —producing a particle composite material (24) having embedded hard material particles (18); —placing the panicle composite material (24) on a solder (30) applied to the blade tip (16); and—healing the solder (30).Type: GrantFiled: February 2, 2010Date of Patent: January 22, 2013Assignee: MTU Aero Engines GmbHInventors: Thomas Uihlein, Erich Steinhardt, Werner Humhauser
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Publication number: 20120045313Abstract: A flow device having a cooling-air injection system for injecting cooling air into cavities (20, 24) between sealing elements (14a, 14b) or sealing bodies (16a, 16b), respectively, on the side of the guide vanes and on the side of the rotor is disclosed.Type: ApplicationFiled: May 12, 2010Publication date: February 23, 2012Applicant: MTU AERO ENGINES GMBHInventors: Peter Klaus Rued, David Koch, Werner Humhauser
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Patent number: 8105016Abstract: A damping arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine, is disclosed. Referring to this damping arrangement, the radially external ends of the guide vanes of a guide vane grid or a guide vane ring are mounted to a housing. The radially internal ends of the guide vanes form an inner shroud. At least one seal bearing is mounted to the inner shroud of the guide vanes. At least one spring element is installed between the inner shroud of the guide vanes and the, or each, seal bearing. The, or each, spring element is configured as a leaf spring.Type: GrantFiled: February 4, 2005Date of Patent: January 31, 2012Assignee: MTU Aero Engines GmbHInventors: Carsten Butz, Werner Humhauser, Patrick Wackers, Walter Waschka, Moritz Wirth
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Publication number: 20110290861Abstract: The invention relates to a method for producing a blade tip plating (20) on a blade (10) Tor a lurhomachine, in particular on a high-pressure rotating compressor blade lor a gas turbine, comprising the following steps:—producing a particle composite material (24) having embedded hard material particles (18);—placing the panicle composite material (24) on a solder (30) applied (o the blade tip (16): and—healing the solder (30).Type: ApplicationFiled: February 2, 2010Publication date: December 1, 2011Applicant: MTU AERO ENGINES GMBHInventors: Thomas Uihlein, Erich Steinhardt, Werner Humhauser
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Patent number: 8061965Abstract: A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt.Type: GrantFiled: February 28, 2005Date of Patent: November 22, 2011Assignee: MTU Aero Engines GmbHInventors: Manfred A. Daeubler, Horst Mueller-Wittek, legal representative, Renate Mendritzki, legal representative, Ulrike Hain, Werner Humhauser
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Publication number: 20110225822Abstract: The invention relates to a device (1) and to a method associated with an assembly mechanism for a rotor system of an axial turbo engine having a central tension anchor, as is particularly known from engine technology. To this end, the invention provides a tensioning tool that pre-tensions or biases the tension anchor prior to and during the insertion of the anchor into the compound rotor assembly. After inserting the biased tension anchor in the compound rotor assembly, the tension anchor is relaxed, whereby the anchor exercises a compressive force on the compound rotor assembly. According to a preferred embodiment, the compound rotor assembly is also biased (compressed) and relaxed after assembling the tension anchor, so that a desired nominal bias Sigmanominal can be particularly easily achieved. The use of a shaft locking nut is no longer necessary in the device according to the invention, thus avoiding the difficulties that are associated with the use of this nut, such as complexity and safety problems.Type: ApplicationFiled: December 2, 2009Publication date: September 22, 2011Applicant: MTU Aero Engines GmbHInventor: Werner Humhauser
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Publication number: 20090263239Abstract: A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt.Type: ApplicationFiled: February 28, 2005Publication date: October 22, 2009Applicant: MTU Aero Engines GmbHInventors: Manfred A. Daeubler, Horst Mueller-Wittek, Renate Mendritzki, Ulrike Hain, Werner Humhauser
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Patent number: 7396206Abstract: A gas turbine has at least one guide blade ring, whose guide vanes are axially and radially fixed via detachable locking elements. A shell ring is configured as a freely machinable component having projections bearing a stop surface and mating surfaces. A holding piece is provided for each guide vane, which engages into corresponding recesses on an upstream shell ring. The holding pieces are held in a position determined by the locking elements, via spring clips.Type: GrantFiled: May 15, 2003Date of Patent: July 8, 2008Assignee: MTU Aero Engines GmbHInventor: Werner Humhauser
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Publication number: 20080019836Abstract: A damping arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine, is disclosed. Referring to this damping arrangement, the radially external ends of the guide vanes of a guide vane grid or a guide vane ring are mounted to a housing. The radially internal ends of the guide vanes form an inner shroud. At least one seal bearing is mounted to the inner shroud of the guide vanes. At least one spring element is installed between the inner shroud of the guide vanes and the, or each, seal bearing. The, or each, spring element is configured as a leaf spring.Type: ApplicationFiled: February 4, 2005Publication date: January 24, 2008Applicant: MTU Aero Engines GmbHInventors: Carsten Butz, Werner Humhauser, Patrick Wackers, Walter Waschka, Moritz Wirth
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Publication number: 20050238490Abstract: A gas turbine has at least one guide blade ring, whose guide vanes are axially and radially fixed via detachable locking elements. A shell ring is configured as a freely machinable component having projections bearing a stop surface and mating surfaces. A holding piece is provided for each guide vane, which engages into corresponding recesses on an upstream shell ring. The holding pieces are held in a position determined by the locking elements, via spring clips.Type: ApplicationFiled: May 15, 2003Publication date: October 27, 2005Applicant: MTU AERO ENGINES GmbhInventor: Werner Humhauser
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Patent number: 6537020Abstract: A casing structure of metal construction for the rotor blade area of axial flow compressor and turbine stages includes a closed, stable outside wall, a segmented inside wall that is interrupted by multiple expansion joints, and a load-transmitting connecting structure between inside and outside wall. A multiple sub-divided hollow chamber structure with a plurality of thin wall elements standing upright on the inside wall and outside wall, at least the majority of which are directly connected together, is arranged as connecting structure. The hollow chamber structure is connected to the inside wall and/or the outside wall by brazing.Type: GrantFiled: April 27, 2001Date of Patent: March 25, 2003Assignee: MTU Aero Engines GmbHInventor: Werner Humhauser
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Patent number: 6431830Abstract: A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby, in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by beam cutting and is connected therewith.Type: GrantFiled: August 21, 2000Date of Patent: August 13, 2002Assignee: MTU Motoren-und Turbinen München GmbHInventors: Karl-Hermann Richter, Josef Reischl, Hans Juergen Schmuhl, Klaus Breitschwerdt, Ulrich Knott, Siegfried Boettcher, Karlheinz Manier, Werner Humhauser
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Publication number: 20010048876Abstract: A casing structure of metal construction for the rotor blade area of axial flow compressor and turbine stages includes a closed, stable outside wall, a segmented inside wall that is interrupted by multiple expansion joints, and a load-transmitting connecting structure between inside and outside wall. A multiple sub-divided hollow chamber structure with a plurality of thin wall elements standing upright on the inside wall and outside wall, at least the majority of which are directly connected together, is arranged as connecting structure. The hollow chamber structure is connected to the inside wall and/or the outside wall by brazing.Type: ApplicationFiled: April 27, 2001Publication date: December 6, 2001Inventor: Werner Humhauser
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Patent number: 6119339Abstract: A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by means of beam cutting and is connected therewith.Type: GrantFiled: March 29, 1999Date of Patent: September 19, 2000Assignee: MTU Motoren-und Turbinen-Union Munchen GmbHInventors: Karl-Hermann Richter, Josef Reischl, Hans Juergen Schmuhl, Klaus Breitschwerdt, Ulrich Knott, Siegfried Boettcher, Karlheinz Manier, Werner Humhauser
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Patent number: 5601407Abstract: A stator construction for turbomachines includes a plurality of support segments (3) and a plurality of guide vane segment roots (2) forming an inner shroud, with an abradable seal liner (4) provided on the radially inner surface of the support segments. An interlocking connection is provided between the vane segment roots and the support segments. The vane segment roots and support segments interlock with one another via radially extending annular flanges (21, 31), and annular grooves (23, 33) provided in the side faces (22, 32) of the annular flanges mate with one another to form annular channels therebetween. To secure the interlocked connection, an annular securing wire (5) is inserted into the annular channels. Spring members (6) may be arranged in annular spaces between the support segments and the vane segment roots.Type: GrantFiled: March 1, 1996Date of Patent: February 11, 1997Assignee: MTU Motoren- und Turbinen- Union Muenchen GmbHInventor: Werner Humhauser