Patents by Inventor Erich Steinhardt
Erich Steinhardt 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: 10267167Abstract: Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. in the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.Type: GrantFiled: January 9, 2017Date of Patent: April 23, 2019Assignee: MTU Aero Engines AGInventors: Erich Steinhardt, Wilfried Smarsly, André Werner
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Patent number: 10001083Abstract: A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W1) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W2) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (DF) of the fan to a maximum blade diameter (DL) of the second turbine is at least 3.5, in particular at least 4.Type: GrantFiled: July 18, 2014Date of Patent: June 19, 2018Assignee: MTU Aero Engines AGInventors: Klaus Peter Rued, Werner Humhauser, Hermann Klingels, Rudolf Stanka, Eckart Heinrich, Hans-Peter Hackenberg, Stefan Weber, Claus Riegler, Erich Steinhardt, Jochen Gier, Manfred Feldmann, Norbert Huebner, Karl Maar
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Publication number: 20170159609Abstract: The invention relates to a turbofan aircraft engine that comprises a primary duct including a combustion chamber; a first turbine disposed downstream of the combustion chamber; a compressor disposed upstream of the combustion chamber and coupled to the first turbine; and a second turbine disposed downstream of the first turbine and coupled to a fan for feeding a secondary duct of the turbofan aircraft engine. The bypass ratio of the inlet area of the secondary duct to the inlet area of the primary duct is at least 7 and the second turbine comprises at least two stages. The mean outer radius of the last stage of the second turbine divided by the length of the second turbine is at least 1.4.Type: ApplicationFiled: April 5, 2016Publication date: June 8, 2017Inventors: Carsten SCHOENHOFF, Rudolf STANKA, Erich STEINHARDT, Claus RIEGLER, Stephen Royston WILLIAMS, Hans-Peter HACKENBERG, Eckart HENRICH, Stefan WEBER, Klaus Peter RUED, Hermann KLINGELS, Patrick WACKERS, Christoph BICHLMAIER, Stefan BUSAM, Matthias KROBOTH, Norbert HUEBNER
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Publication number: 20170159573Abstract: The invention relates to a turbofan aircraft engine that comprises a primary duct including a combustion chamber; a first turbine disposed downstream of the combustion chamber; a compressor disposed upstream of the combustion chamber and coupled to the first turbine; and a second turbine disposed downstream of the first turbine and coupled to a fan for feeding a secondary duct of the turbofan aircraft engine. The bypass ratio of the inlet area of the secondary duct to the inlet area of the primary duct is at least 7 and the second turbine comprises at least two stages. For the first stage the mean radius r of a stator vane expressed in inch divided by the number of stator vanes is at least 0.18.Type: ApplicationFiled: April 5, 2016Publication date: June 8, 2017Inventors: Carsten SCHOENHOFF, Rudolf STANKA, Erich STEINHARDT, Claus RIEGLER, Stephen Royston WILLIAMS, Hans-Peter HACKENBERG, Eckart HENRICH, Stefan WEBER, Klaus Peter RUED, Hermann KLINGELS, Patrick WACKERS, Christoph BICHLMAIER, Stefan BUSAM, Matthias KROBOTH, Norbert HUEBNER
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Publication number: 20170122118Abstract: Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. in the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.Type: ApplicationFiled: January 9, 2017Publication date: May 4, 2017Inventors: Erich STEINHARDT, Wilfried SMARSLY, André WERNER
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Patent number: 9551231Abstract: Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. In the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.Type: GrantFiled: August 9, 2013Date of Patent: January 24, 2017Assignee: MTU AERO ENGINES AGInventors: Erich Steinhardt, Wilfried Smarsly, André Werner
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Publication number: 20160032826Abstract: A turbofan aircraft engine has at least one stage pressure ratio is at least 1.5, and a quotient of the total blade count divided by 110 is less than a difference ([(p1/p2)?1]) of the total pressure ratio minus one, and the total pressure ratio is greater than 4.5, and the turbine has at least two and no more than five turbine stages; and/or a product (An2) of an exit area (AL) of the second turbine and a square of a rotational speed of the second turbine at the design point is at least 4.5·1010 [in2·rpm2], and a blade tip velocity (uTIP) of at least one turbine stage of the second turbine at the design point is at least 400 meters per second. A jet and method are also provided.Type: ApplicationFiled: August 4, 2014Publication date: February 4, 2016Inventors: Klaus Peter Rued, Werner Humhauser, Hermann Klingels, Rudolf Stanka, Eckart Heinrich, Hans-Peter Hackenberg, Claus Riegler, Erich Steinhardt, Jochen Gier, Manfred Feldmann, Norbert Huebner, Karl Maar, Stefan Weber
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Publication number: 20160017797Abstract: A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W1) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W2) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (DF) of the fan to a maximum blade diameter (DL) of the second turbine is at least 3.5, in particular at least 4.Type: ApplicationFiled: July 18, 2014Publication date: January 21, 2016Inventors: Klaus Peter RUED, Werner Humhauser, Hermann Klingels, Rudolf Stanka, Eckart Heinrich, Hans-Peter Hackenberg, Stefan Weber, Claus Rieger, Erich Steinhardt, Jochen Gier, Manfred Feldmann, Norbert Huebner, Karl Maar
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Patent number: 8936442Abstract: A method for manufacturing an integrally bladed rotor (10), in particular for a gas turbine, including the following method steps: preparing a rotor base member (12) having at least one first weld surface (16) and one blade (14) having a second weld surface (18); positioning the rotor base member (12) and the blade (14) in such a way that a join zone (20) is formed between the first and second weld surface (16, 18); and filling the join zone (20) with metal powder (24) and the laser welding or electron beam welding of the metal powder (24). An integrally bladed rotor (10) has a join zone (20) between the rotor base member (12) and blades (14), the join zone (20) being filled with welded metal powder (24).Type: GrantFiled: January 30, 2010Date of Patent: January 20, 2015Assignee: MTU Aero Engines GmbHInventors: Thomas Uihlein, Erich Steinhardt
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Publication number: 20140044549Abstract: Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. In the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.Type: ApplicationFiled: August 9, 2013Publication date: February 13, 2014Applicant: MTU AERO ENGINES AGInventors: Erich Steinhardt, Wilfried Smarsly, André Werner
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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: 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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Publication number: 20110217176Abstract: The invention relates to a method for connecting at least one turbine blade (10) to a turbine disk (18) or a turbine ring for a turbine stage of a turbomachine, particularly a thermal gas turbine, wherein first a connecting body (16) is formed on the at least one turbine blade (10) by means of a cold gas spraying method, and the connecting body (16) is subsequently connected to turbine disk (18) or to the turbine ring by means of a fusion-welding method. The invention further relates to a turbine stage for a turbine of a turbomachine as well as a turbomachine having a turbine.Type: ApplicationFiled: October 16, 2009Publication date: September 8, 2011Applicant: MTU AERO ENGINES GMBHInventors: Thomas Uihlein, Bertram Kopperger, Erich Steinhardt
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Patent number: 7984547Abstract: A method is for manufacturing and/or repairing components, e.g., blades and blade segments, for gas turbines, e.g., for aircraft engines, by laser-powder build-up welding. Laser-powder build-up welding is performed using at least one substructure, the material build-up by a powder material occurring in the process of laser-powder build-up welding such that the or every substructure is at least in sections enclosed by the built-up powder material.Type: GrantFiled: July 29, 2004Date of Patent: July 26, 2011Assignee: MTU Aero Engines GmbHInventor: Erich Steinhardt
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Patent number: 7950147Abstract: A method for producing gas turbine components, in particular blades, blade sections or rotors with integral blades for a jet engine is provided. The method comprises at least the following steps: preparation of at least one metallic powder and at least one expanding agent; mixing of the metallic powder or each metallic powder with the expanding agent or each expanding agent; compression of the resultant mixture to form at least one semi-finished product; expansion of the semi-finished product or each semi-finished product by heating to achieve a defined degree of expansion; termination of the expansion process by cooling, once the defined degree of expansion has been reached.Type: GrantFiled: November 24, 2004Date of Patent: May 31, 2011Assignee: MTU Aero Engines GmbHInventors: Reinhold Meier, Erich Steinhardt
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Patent number: 7775766Abstract: A static gas turbine component, especially for an aircraft engine, is formed at least partially region-wise of metal foam. An abradable shroud lining of metal foam and a carrier allow a radial through-flow of gas.Type: GrantFiled: December 9, 2004Date of Patent: August 17, 2010Assignee: MTU Aero Engines GmbHInventors: Reinhold Meier, Erich Steinhardt
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Publication number: 20090277009Abstract: A method for manufacturing and/or machining components, in particular gas turbine components such as blades, blade segments or integrally bladed rotors for an aircraft engine, is disclosed. In an embodiment, the method for manufacturing components, in particular gas turbine components, includes at least the following steps: a) providing a workpiece; b) milling the workpiece to provide a component to be manufactured; c) rounding the edges of the component and/or smoothing the surface of the component and/or hardening the surface of the component by a hydraulic method using a lubricant and/or coolant required for the milling.Type: ApplicationFiled: December 21, 2004Publication date: November 12, 2009Applicant: MTU AERO ENGINESInventors: Thorben Kotzbacher, Erich Steinhardt
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Publication number: 20070122269Abstract: The invention relates to a gas turbine component, namely static gas turbine component, especially for an aircraft engine. According to the invention, the static gas turbine component is formed at least region-wise of metal foam.Type: ApplicationFiled: December 9, 2004Publication date: May 31, 2007Inventors: Reinhold Meier, Erich Steinhardt
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Publication number: 20070122606Abstract: A method for producing gas turbine components, in particular blades, blade sections or rotors with integral blades for a jet engine is provided. The method comprises at least the following steps: preparation of at least one metallic powder and at least one expanding agent; mixing of the metallic powder or each metallic powder with the expanding agent or each expanding agent; compression of the resultant mixture to form at least one semi-finished product; expansion of the semi-finished product or each semi-finished product by heating to achieve a defined degree of expansion; termination of the expansion process by cooling, once the defined degree of expansion has been reached.Type: ApplicationFiled: November 24, 2004Publication date: May 31, 2007Applicant: MTU Aero Engines GmbHInventors: Reinhold Meier, Erich Steinhardt
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Publication number: 20070007260Abstract: A method is for manufacturing and/or repairing components, e.g., blades and blade segments, for gas turbines, e.g., for aircraft engines, by laser-powder build-up welding. Laser-powder build-up welding is performed using at least one substructure, the material build-up by a powder material occurring in the process of laser-powder build-up welding such that the or every substructure is at least in sections enclosed by the built-up powder material.Type: ApplicationFiled: July 29, 2004Publication date: January 11, 2007Inventor: Erich Steinhardt