Abstract: A seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. A turbo machine having a seal configuration (100) is also provided.
Type:
Grant
Filed:
November 4, 2014
Date of Patent:
August 14, 2018
Assignee:
MTU Aero Engines AG
Inventors:
Andre Werner, Stephan Klaen, Manuel Hertter, Frank Stiehler
Abstract: Disclosed is a blade/vane cascade segment of a blade/vane cascade of a turbomachine, which comprises at least two blade/vane elements defining an axial cascade width, and a stage with a stage surface, as well as a stage edge on the inflow side. The stage surface has an elevation extending up to the pressure side of a first blade/vane element and a depression extending up to the suction side of the other blade/vane. At least one highest point of the elevation and at least one lowest point of the depression each lie at least 30% and at most 60% of the axial cascade width downstream of the inflow edges of the blade/vane elements. In this case, the elevation and the depression each come close to the stage edge on the inflow side. Also disclosed are a blade/vane cascade, a stage for a blade/vane cascade segment, a blade/vane channel, and a turbomachine.
Abstract: A power generating assembly including an internal combustion engine and a combustion gas supply connected to the internal combustion engine in order to supply combustion gas. The combustion gas supply has an at least double-walled line at least in the region of the internal combustion engine, the line having an inner line volume for combustion gas and an outer line volume. The outer line volume is fluidically connected to an inert gas supply. The power generating assembly also includes a combustion gas pressure adjusting device that adjusts a combustion gas pressure in the inner line volume, and an inert gas pressure adjusting device that adjusts an inert gas pressure in the outer line volume. The combustion gas pressure adjusting device and the inert gas pressure adjusting device select the inert gas pressure and the combustion gas pressure such that the inert gas pressure is higher than the combustion gas pressure.
Type:
Application
Filed:
July 7, 2016
Publication date:
August 9, 2018
Applicant:
MTU FRIEDRICHSHAFEN GMBH
Inventors:
Manuel BOOG, Wolfgang FIMML, Jan Gerrit PRUNNBAUER
Abstract: An internal combustion engine including a cylinder head, a fresh air duct configured for providing a fresh air supply to the internal combustion engine, and a quick-closing valve arranged in the fresh air duct, upstream of the cylinder head of the internal combustion engine, in order to interrupt the fresh air supply. The internal combustion engine also includes an exhaust gas recirculation pipe that has an outlet opening that is arranged centrally in the fresh air duct and, in a flow direction of the fresh air supply, upstream of the quick-closing valve forming a minimum gap between the outlet opening and the quick-closing valve.
Type:
Application
Filed:
April 5, 2018
Publication date:
August 9, 2018
Applicant:
MTU Friedrichshafen GmbH
Inventors:
Hermann Braun, Thomas Rode, Christian-Paul Stelzer
Abstract: A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.
Type:
Grant
Filed:
August 6, 2014
Date of Patent:
August 7, 2018
Assignee:
MTU Aero Engines AG
Inventors:
Jochen Gier, Yavuz Guendogdu, Karl Engel
Abstract: A blade-disk assembly of a turbomachine is provided, 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. A method for assembling such a blade-disk assembly, as well as a turbomachine, is also provided.
Type:
Grant
Filed:
November 18, 2014
Date of Patent:
August 7, 2018
Assignee:
MTU Aero Engines AG
Inventors:
Werner Humhauser, Herman Klingels, Alexander Kloetzer
Abstract: A method for the quality evaluation of a component produced by an additive manufacturing method and device includes at least the following steps: providing image data that characterizes at least one component site of a component produced by an additive manufacturing method; converting the image data into a binary image; eroding the binary image into a structure image; determining contour data of the structure image; determining at least one image section of the image data that is delimited by the contour data; inspecting the at least one image section for the presence of an image region corresponding to a quality defect; and classifying the component as being qualitatively OK if no quality defect is present, or classifying the component as being qualitatively not OK if a quality defect is present.
Abstract: A system control unit for controlling a charging system that is intended for charging an electrical energy storage device, comprising an electric generator; an internal combustion engine that is mechanically connected with the electric generator; a generator controller for controlling the electric generator; an engine controller for controlling the internal combustion engine; and a transmitting device for transmission of messages, whereby the engine controller is connected with the generator controller by way of the transmitting device, and whereby the engine controller is operable in that a message containing information about an operating state of the internal combustion engine can be produced and said message can be sent to the generator controller via the transmitting device.
Type:
Grant
Filed:
February 18, 2016
Date of Patent:
July 31, 2018
Assignee:
MTU Friedrichshafen GmbH
Inventors:
Eckhard Osterloff, Martin Roscher, Arndt Von Drathen, Gerhard Droullier
Abstract: The invention relates to a repair method for a component and includes the steps of removal of a damaged region of the component with the formation of at least one separating surface; arrangement of the component in a processing chamber of a device for the additive restoration of at least the region of the component that has been removed; determining first structural data of the component disposed in the processing chamber; providing second structural data of the component; determining third structural data based on the first and the second structural data; and additive restoration of the component region that has been removed on the at least one separating surface of the component. In addition, the invention relates to a device for the additive repair of a component.
Type:
Grant
Filed:
October 21, 2015
Date of Patent:
July 31, 2018
Assignee:
MTU AERO ENGINES AG
Inventors:
Alexander Ladewig, Steffen Schlothauer, Thomas Hess, Christian Liebl
Abstract: A shaft seal system which is disposed axially between a first chamber and a second chamber is disclosed. The shaft seal system includes a shaft, a casing that surrounds the shaft, and a seal which is disposed axially closer to the second chamber where the first chamber has a fluid and the second chamber is to be protected from the fluid. In this arrangement, the seal includes a pressure booster.
Type:
Grant
Filed:
September 2, 2015
Date of Patent:
July 24, 2018
Assignee:
MTU Aero Engines AG
Inventors:
Michael Flouros, Richard Scharl, Francois Cottier
Abstract: The present invention relates to a process for producing a component, in particular a component for a turbomachine, composed of a TiAl alloy, which comprises the following: introduction of a powder of the TiAl alloy into the capsule whose shape corresponds to the shape of the component to be produced and closing of the capsule, hot isostatic pressing of the capsule together with the powder, heat treatment of the hot isostatically pressed capsule, removal of the capsule, post-working of the contour of the component by removal of material.
Abstract: A method for operating an exhaust after-treatment system including an SCR-catalyst, a metering device for dosing a reducing agent being controlled on the basis of a determining variable that influences a nitrogen-oxide concentration downstream of the SCR-catalyst. A breakthrough identification is carried out for the SCR-catalyst, wherein if a breakthrough is identified, the determining variable is altered to a higher nitrogen-oxide concentration downstream of the SCR-catalyst and the metering device is controlled in order to dose the reducing agent on the basis of the altered determining variable.
Type:
Application
Filed:
June 28, 2016
Publication date:
July 19, 2018
Applicant:
MTU FRIEDRICHSHAFEN GMBH
Inventors:
Klaus RUSCH, Jörg REMELE, Jens NIEMEYER
Abstract: A ceramic component for a turbomachine, the ceramic component (1) being configured to be destroyed in response to a contacting with another component (2) of the turbomachine that moves relative to the ceramic component (1). A turbomachine component pairing and a turbomachine including such a ceramic component.
Type:
Grant
Filed:
July 2, 2014
Date of Patent:
July 17, 2018
Assignee:
MTU Aero Engines AG & Co. KG
Inventors:
Norbert Schinko, Janine Sangl, Stephan Klaen, Markus Schlemmer
Abstract: A method for the at least partially automated diagnosis of aircraft gas turbine engines includes the steps of: 1) detecting actual parameter values of an aircraft gas turbine engine for several operational segments 2) determining deviations, of these actual parameter values from theoretical parameter values; and 3) determining damage pattern probabilities based on a similarity of at least one determined deviation, particularly based on a change between determined deviations, to deviation patterns of different known damage patterns.
Type:
Grant
Filed:
March 2, 2016
Date of Patent:
July 3, 2018
Assignee:
MTU AERO ENGINES AG
Inventors:
Andre Kando, Hassan Abdullahi, Anastasios Tsalavoutas, Thomas Speer
Abstract: A method for designing a turbine of a gas turbine, in particular of an aircraft engine, which has a last stage having a rotating last rotor grid, having a plurality of rotating blades, and an adjacent, downstream, stationary exit guide grid, having a plurality of guide vanes; with the last stage being characterized by a vane-to-blade ratio characteristic quantity, which indicates the ratio of the number of guide vanes to the number of rotating blades.
Abstract: A method for coating a turbine blade of a gas turbine is disclosed. The method includes applying a lacquer coat to a region of the turbine blade, where the lacquer coat includes chromium particles and/or chromium alloy particles, halides, and a binding agent. The method further includes drying the applied lacquer coat at a temperature between 50° C. and 600° C. with disintegration of the binding agent and subsequent reactive connection at a temperature between 900° C. and 1160° C.
Type:
Grant
Filed:
September 7, 2010
Date of Patent:
June 26, 2018
Assignee:
MTU Aero Engines GmbH
Inventors:
Heinrich Walter, Horst Pillhoefer, Michael Strasser, Karlheinz Manier, Max Morant, Richard Lange
Abstract: A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material.
Abstract: 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:
Grant
Filed:
July 18, 2014
Date of Patent:
June 19, 2018
Assignee:
MTU Aero Engines AG
Inventors:
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
Abstract: A turbomachine blade having a main body (10) that includes a plane, first attachment surface (100) having a first rim contour (110), a cover (20; 21, 22) that has a plane, second attachment surface (200) having a second rim contour (210) that is welded to the first attachment surface, and a tuning body configuration having at least one tuning body (30; 31-33) for contacting an inner wall (220) of the cover by impact therewith, a gap (s) being formed between the first and the second rim contour.
Abstract: Disclosed is a TiAl alloy for high-temperature applications which comprises not more than 43 at. % of Al, from 3 at. % to 8 at. % of Nb, from 0.2 at. % to 3 at. % of Mo and/or Mn, from 0.05 at. % to 0.5 at. % of B, from 0.1 at. % to 0.5 at. % of C, from 0.1 at. % to 0.5 at. % of Si and Ti as balance. Also disclosed is a process for producing a component made of this TiAl alloy and the use of corresponding TiAl alloys in components of flow machines at operating temperatures up to 850° C.
Type:
Grant
Filed:
September 9, 2014
Date of Patent:
June 12, 2018
Assignee:
MTU Aero Engines AG
Inventors:
Wilfried Smarsly, Helmut Clemens, Emanuel Schwaighofer