Patents Assigned to MTU Aero Engines GmbH
-
Patent number: 9346141Abstract: A joining device for arranging a component on a component carrier is disclosed. The joining device includes an application system for positioning the component in the joining device and a receptacle for clamping the component carrier in the joining device. The component is arranged on the component carrier by an adapter. A method for arranging the component on the component carrier is also disclosed.Type: GrantFiled: July 7, 2010Date of Patent: May 24, 2016Assignee: MTU Aero Engines GmbHInventors: Martin Fessler-Knobel, Roland Huttner
-
Patent number: 9333623Abstract: A method for removing a layer made of a first material from a surface of a body made of a second material is disclosed. The body is subjected to a pressurized jet containing a blasting medium composed of particles, where the pressurized jet at least intermittently has an Almen intensity of at most 0.35 Almen A, preferably at most 0.3 Almen A and particularly preferably at most 0.25 Almen A.Type: GrantFiled: August 6, 2011Date of Patent: May 10, 2016Assignee: MTU Aero Engines GmbHInventors: Horst Pillhoefer, Johann Oettl, Markus Niedermeier, Thomas Cosack, Dirk Ruhlig
-
Patent number: 9333589Abstract: A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements.Type: GrantFiled: March 14, 2007Date of Patent: May 10, 2016Assignee: MTU Aero Engines GmbHInventors: Herbert Hanrieder, Alexander Gindorf, Reinhold Meier
-
Publication number: 20160116442Abstract: The invention relates to a method of nondestructive and contactless testing of components (3), wherein ultrasonic waves (6) are irradiated onto the surface of the component (3) at a predefinable, non-perpendicular angle of incidence (9) using an ultrasonic transmission sound transducer (1) arranged spaced apart from the surface of the component (3) and the intensity of the ultrasonic waves (7) reflected from the surface of the component (3) is detected with time resolution and/or frequency resolution by the antenna array elements (2n) of an ultrasonic antenna array (2) configured for detecting ultrasonic waves (7) and the phase shift of the ultrasonic waves guided at the surface of the test body is determined therefrom with respect to the ultrasonic waves (7) directly reflected at the surface of the component (3).Type: ApplicationFiled: November 23, 2015Publication date: April 28, 2016Applicants: Fraunhofer-Gesellschaft Zur Foerderung Der Angewandten Forschung E.V., MTU Aero Engines GmbHInventors: Bernd KOEHLER, Martin BARTH, Joachim BAMBERG, Hans-Uwe BARON
-
Patent number: 9322100Abstract: A method for manufacturing an abrasive coating on a gas turbine component, especially on a gas turbine rotor blade tip, comprising at least the following steps: a) providing a gas turbine component, especially a gas turbine rotor blade; b) providing a high temperature melting alloy powder; c) providing abrasive particles; d) providing a low temperature melting alloy powder; e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture; f) applying said low temperature melting alloy powder and said mixture to an area of said gas turbine component, especially to a tip of said turbine rotor blade; g) locally heating said area of said gas turbine component to a temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder is provided.Type: GrantFiled: May 4, 2007Date of Patent: April 26, 2016Assignees: MTU Aero Engines GmbH, Liburdi Engineering LimitedInventors: Karl-Heinz Manier, Ilya Chuprakov, Robert Sparling
-
Patent number: 9321107Abstract: A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.Type: GrantFiled: November 6, 2012Date of Patent: April 26, 2016Assignee: MTU Aero Engines GmbHInventors: Bernd Daniels, Herbert Hanrieder, Karl-Hermann Richter, Michael Strasser
-
Patent number: 9322281Abstract: A shroud segment to be arranged on a gas turbine blade is disclosed. The shroud segment includes a shroud segment surface and a stiffening structure that is raised relative to the shroud segment surface. The stiffening structure is cross-shaped at least in some areas.Type: GrantFiled: June 21, 2010Date of Patent: April 26, 2016Assignee: MTU Aero Engines GmbHInventors: Markus Schlemmer, Bartlomiej Pikul
-
Patent number: 9314844Abstract: A method for manufacturing a component having at least one element configured in the component, in particular at least one conduit, conduit unit, or supporting element configured within an aerodynamic rib, the component having an element leadthrough for leading through the at least one element, the method including the following step: building up in layers of the component including the element leadthrough, together with the at least one element in a generative production process.Type: GrantFiled: April 6, 2012Date of Patent: April 19, 2016Assignee: MTU Aero Engines GmbHInventor: Peter Geiger
-
Patent number: 9303522Abstract: A method for repairing run-in coatings is provided. The method includes the steps of filling a damaged site of the run-in coating with a filling material having a material composition that corresponds to a material composition of the run-in coating or is comparable to the material composition of the run-in coating or having material properties that are comparable to material properties of the run-in coating; drying the filling material that has been filled into the damaged site; depositing a donor diffusion layer over an area of the damaged site and onto the dried filling material; and thermally treating the run-in coating at least in the area of the damaged site to locally diffuse at least one metallic element from the donor diffusion layer into the filling material.Type: GrantFiled: June 14, 2007Date of Patent: April 5, 2016Assignee: MTU Aero Engines GmbHInventors: Manfred A. Daeubler, Horst Mueller-Wittek, Renate Mendritzki, André Werner, Heinrich Walter
-
Patent number: 9302351Abstract: The invention relates to a method for joining two components (10, 12) made of a metal material, which are connected on two mutually associated joining surfaces (14, 16) by means of a joined connection, wherein at least one of the components (10) is strengthened in at least a partial region of the joining surface (14) thereof prior to joining. The invention further relates to a joined connection of two components (10, 12) made of a metal material.Type: GrantFiled: July 24, 2008Date of Patent: April 5, 2016Assignee: MTU Aero Engines GmbHInventors: Joachim Bamberg, Roland Hessert, Wilhelm Satzger, Thomas Mack, Alexander Gindorf, Martina Mack, Legal Representative
-
Patent number: 9303513Abstract: A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades, whereby the trailing edges of the blades of the upstream row of blades and the leading edges of the blades of the downstream row of blades are arranged at an axial edge distance that decreases from the center of the main flow path in the direction of at least one main flow limiter.Type: GrantFiled: February 6, 2013Date of Patent: April 5, 2016Assignee: MTU Aero Engines GmbHInventors: Sergio Elorza Gomez, Tim Schneider
-
Patent number: 9272379Abstract: A mounting device and method for mounting a component is disclosed. The mounting device includes a component carrier and an adapter. The adapter is insertable into a guide of the component carrier. The method uses the mounting device to mount a component on the mounting device.Type: GrantFiled: March 9, 2011Date of Patent: March 1, 2016Assignee: MTU Aero Engines GmbHInventors: Martin Fessler-Knobel, Roland Huttner
-
Patent number: 9260784Abstract: The present invention relates to a method for producing a component, in particular a blade for a gas turbine, wherein a main body (2) is provided, to which a running-in layer (6) is applied, which can be worn away at least partially during operation to form an accurately fitting surface (11), wherein the running-in layer is applied by kinetic cold-gas compacting, and a component, in particular a blade for a gas turbine, comprising a main body, to which a running-in layer is applied, which can be worn away at least partially during operation to form an accurately fitting surface, wherein the running-in layer is a porous layer made of a Ti alloy.Type: GrantFiled: July 31, 2010Date of Patent: February 16, 2016Assignee: MTU Aero Engines GmbHInventors: Andreas Jakimov, Stefan Schneiderbanger, Manuel Hertter
-
Patent number: 9254530Abstract: A method for removing material from a component that is connected as an anode is disclosed. In an embodiment, an electrode that is connected as a cathode is guided to the component such that a gap is formed, an electrolyte is introduced into the gap, and a closed system is formed for the electrolyte by the formation of a duct. The electrolyte is continuously guided from an inlet opening to an outlet opening of the duct. Forming the duct, e.g., by guide elements that are mounted on the electrode, ensures that only those surface parts of the component to be machined from which material is to be removed enter in contact with the electrolyte while the other surface parts do not enter in contact with the electrolyte. Since the electrolyte is continuously guided across the surface, used electrolyte is continuously discharged along with residual matter while fresh electrolyte is delivered.Type: GrantFiled: December 5, 2008Date of Patent: February 9, 2016Assignee: MTU Aero Engines GmbHInventors: Erwin Bayer, Martin Bussmann, Albin Platz
-
Patent number: 9249686Abstract: A housing for a turbomachine includes a peripheral wall delimiting an annular space and a fluid conveying system for redirecting a partial flow of a main flow, which has an axial channel, a front annular channel and a rear annular channel in fluid connection with the axial channel and having a front annular space opening and a rear annular space opening. The fluid conveying system has a front valve device and a rear valve device controllable independently of the front valve device, for opening and closing the annular space openings, and an outlet opening for tapping the partial flow from the fluid conveying system. In the closed state of the rear annular space opening, the partial flow is directable through the rear annular channel and, in the closed state of the front annular space opening, the partial flow is directable through the front annular channel.Type: GrantFiled: March 11, 2013Date of Patent: February 2, 2016Assignee: MTU Aero Engines GmbHInventors: Sven Hiller, Erwin Bayer, Peter Geiger, Thomas Hess
-
Patent number: 9212555Abstract: A method for removing the coating from a gas turbine component, namely for the complete or partial removal of a multilayer wear protection coating from the surface of the gas turbine component, the wear protection coating having at least one relatively hard ceramic layer and at least one relatively soft metallic layer, wherein, in order to remove the multilayer wear protection coating, the gas turbine component is alternately positioned in two different chemical baths, a first bath being used exclusively for the removal of each relatively hard ceramic layer, and a second bath being used exclusively for the removal of each relatively soft metallic layer of the wear protection coating.Type: GrantFiled: October 10, 2006Date of Patent: December 15, 2015Assignees: MTU Aero Engines GmbH, AB Solut Chemie GmbHInventors: Karl-Heinz Manier, Thomas Uihlein, Carl-Stefan Thöne
-
Patent number: 9151163Abstract: A rotor disk for a turbomachine, which is connectable to at least one rotor blade and/or a shaft of the turbomachine, having at least one borehole, which has an elliptical inlet opening having a first passage cross-sectional area and an elliptical outlet opening having a second passage cross-sectional area, so that the second passage cross-sectional area is smaller than the first passage cross-sectional area.Type: GrantFiled: November 29, 2012Date of Patent: October 6, 2015Assignee: MTU Aero Engines GmbHInventors: Matthias Siebel, Heinz Rauschmair, Andreas Hoelzel
-
Patent number: 9140129Abstract: The turbomachine has a ring of radial blades which are connected to an annular end wall. Situated on the end wall upstream of each blade is a deflector wedge with two divergent guide surfaces. The deflector wedge generates pressure-side and suction-side vortices of which the vortices caused by the blade cascade are altered such that the transverse flow and backflow areas on the blade are reduced, and therefore the edge zone losses are decreased.Type: GrantFiled: November 2, 2010Date of Patent: September 22, 2015Assignee: MTU Aero Engines GmbHInventors: Alexander Hergt, Robert Meyer, Ralf-Dietmar Baier
-
Patent number: 9138834Abstract: A method for replacing a blade (12) of a rotor (2) having integral blades, wherein a new blade (22) is joined to a base (34) arranged on a separation surface (28) on the main rotor body, and to a rotor repaired or mended according to said method.Type: GrantFiled: July 8, 2010Date of Patent: September 22, 2015Assignee: MTU Aero Engines GmbHInventors: Karl-Hermann Richter, Marcus Klemm
-
Patent number: 9132508Abstract: The invention relates to a method for producing a rotor or stator blade (1a) of a gas turbine, in particular an aircraft gas turbine (2), comprising forming a airfoil (8a) made of at least one first material and attaching a blade root (4a) made of at least one second material to the airfoil (8a) by means of a thermal spraying method. The invention further relates to a rotor or stator blade (1a) produced according to such a method.Type: GrantFiled: October 2, 2010Date of Patent: September 15, 2015Assignee: MTU Aero Engines GmbHInventors: Thomas Dautl, Andreas Jakimov, Manuel Hertter