Abstract: A component, in particular an engine component, which has at least one mark with a predetermined three-dimensional shape for determining a stress in the component and where the component is constructed by a generative manufacturing method, is disclosed.
Abstract: A method is disclosed for the repair of a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with blades taken up in at least one groove and with at least one support region for limiting a blade tilt angle, whereby at least one segment, which has been subjected to wear, of the support region of the component is removed, and a coating that can be introduced in the unit on at least one supporting surface of at least one blade is formed on the component for limiting the blade tilt angle. In addition, a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with at least one such repair site is disclosed.
Abstract: The invention relates to a method for controlling a railway vehicle having a double drive system, wherein each drive system comprises an internal combustion engine and a transmission unit, wherein a target drive torque (M(SL)) is provided as a power requirement by means of a drive lever, wherein an actual drive torque (M(IST)) of the railway vehicle is determined and a drive torque deviation is calculated from the target drive torque (M(SL)) and the actual drive torque (M(IST)). The method further comprises determining a prediction drive type (AAP), and a target drive type (AA(SL)) in the sense of a single or double drive, a target operating point (BP(SL)), and a target transmission stage (US(SL)) are set for the transmission units, based on the drive torque deviation and the prediction drive type (AAP), by means of a traction manager (9).
Type:
Grant
Filed:
March 11, 2010
Date of Patent:
July 1, 2014
Assignee:
MTU Friedrichshafen GmbH
Inventors:
Holger Bottlang, Ingo Lehmann, Michael Willmann
Abstract: 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.
Abstract: A turbine blade (100) having an airfoil (1). In its radially outer region, the turbine blade (100) has at least one shroud (200) or at least one shroud segment, as well as at least one cutting tooth (300) which is intended to engage at least once into portions of a turbine casing during use of the turbine blade (100). The cutting tooth (300) is connected to the shroud (200) or the shroud segment.
Type:
Application
Filed:
December 10, 2013
Publication date:
June 26, 2014
Applicant:
MTU Aero Engines AG
Inventors:
Alexander Boeck, Manfred Feldmann, Stephen Royston Williams
Abstract: A device for redirecting a leakage current flowing between a stator and a rotor is disclosed. The device includes a sealing element for interrupting the leakage current, an outlet opening disposed on the rotor, and a guide which is configured to direct the leakage current past the sealing element to the outlet opening.
Abstract: A method for operating a traction vehicle, especially a locomotive, wherein the power delivered by a drive system is produced by at least two internal combustion engines, each of which is functionally connected to a generator for producing electric power, the engines preferably being gas engines, even more preferably lean gas engines. A previously determined number of separate power stages ranging from a minimum power up to a nominal power of the drive system is provided. The interval between all directly adjacent power stages is selected so that it corresponds to a constant fraction of the nominal power of the drive system.
Abstract: The invention relates to a method for the generative production of a component (2) and to a device for carrying out such a method, having the following steps: applying a material layer with a constant layer thickness; solidifying a region of the material layer according to a component cross section; generating an eddy-current scan of the solidified region, a scan depth corresponding to a multiple of the layer thickness; determining a material characterization of the solidified region taking into consideration a previous eddy-current scan of solidified regions of lower-lying material layers; and repeating the steps until the component (2) is assembled. An electric material characterization of each individual layer is determined using a recursive algorithm of individual measurements (monolayer by monolayer), and thus the entire component is tested step by step completely in a highly resolved manner.
Type:
Application
Filed:
July 31, 2012
Publication date:
June 12, 2014
Applicant:
MTU AERO ENGINES AG
Inventors:
Joachim Bamberg, Wilhelm Satzger, Thomas Hess
Abstract: A covering device for an integrally bladed rotor base body of a turbomachine for preventing or reducing a cooling air stream that flows from a high-pressure side to a low-pressure side through channels that are formed between adjacent rotor blades, a plurality of cover elements being provided that are individually insertable into the channels and have at least one peripheral sealing surface. Also an integrally bladed rotor base body having a covering device of this kind, a method for producing such an integrally bladed rotor base body, as well as a turbomachine having such an integrally bladed rotor base body.
Abstract: The invention relates to a method for producing, repairing and/or exchanging a housing, in particular an engine housing of an aircraft engine, comprising at least two shells, between which a structural part is formed, wherein the method comprises the following step: layer-by-layer construction of the at least two shells jointly with the structural part by means of a generative manufacturing system, wherein the structural part comprises at least one porous structure and/or honeycomb structure. The invention relates furthermore to such a housing.
Abstract: A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating.
Type:
Application
Filed:
July 18, 2012
Publication date:
June 12, 2014
Applicant:
MTU Aero Engines AG
Inventors:
Erwin Bayer, Thomas Hess, Sven-J. Hiller, Peter Geiger
Abstract: The turbomachine includes a mid turbine vane frame, with an annular compartment formed between the mid turbine vane frame and a low-pressure turbine casing being sealed by means of at least two ring seals, wherein one ring seal is in contact with the mid turbine vane frame and the other ring seal is in contact with the low-pressure turbine casing and a radial annular overlap is thereby created with the first-mentioned ring seal.
Abstract: Proposed is a method for closed loop rail pressure control of a V-type internal combustion engine with an asymmetrical firing order, wherein an actual rail pressure is computed from the measured rail pressure; a system deviation is determined by means of the actual rail pressure and a set rail pressure; and wherein a correcting variable for actuating a pressure actuating element, in particular a suction throttle, for regulating the rail pressure is computed. The invention is characterized by the fact that the actual rail pressure is computed from the measured rail pressure by means of an averaging filter in that below a limit speed (nLi) the rail pressure is averaged over a constant time and in that above the limit speed (nLi) the rail pressure is averaged over a working cycle of the internal combustion engine.
Abstract: A gas turbine, in particular an aircraft engine, having a housing in which at least one guide blade (12) is situated, the guide blade (12) including at least one shroud configuration (21) having a radially outer shroud (16) and having a shroud holding device (23) with the aid of which the shroud (16) is secured on the housing, as well as including a turbine blade (18) extending radially inward from the shroud configuration (21). The shroud holding device (23) or parts thereof include(s) at least one air passage channel (28), which permits a flow passage through the shroud holding device (23). The invention also relates to a guide blade (12) for placement on a housing of a gas turbine as well as a method for manufacturing such a guide blade (12).
Abstract: A device (2) having at least one connecting element (24, 26) for fastening a component (4) to, respectively for detaching it from a component carrier (6) using adhesive bonds; a mechanical peeling device (8) being provided for breaking the adhesive bonds. Also a method for fastening a component (4) to, respectively for detaching it from a component carrier (6).
Abstract: 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:
Application
Filed:
November 29, 2012
Publication date:
May 29, 2014
Applicant:
MTU Aero Engines GmbH
Inventors:
Matthias SIEBEL, Heinz RAUSCHMAIR, Andreas HOELZEL
Abstract: A method for machining a robot-guided component with a tool which is fastened in an articulated manner to a tool holder is disclosed. The method includes detecting a deflection of the tool with respect to the tool holder from a desired position and changing a pose of a robot that is guiding the robot-guided component on a basis of the detected deflection.
Type:
Application
Filed:
October 26, 2011
Publication date:
May 29, 2014
Applicants:
INSYS Industriesysteme AG, MTU Aero Engines GmbH
Abstract: In an engine crankcase including a crankshaft supported at its front end by a crankshaft bearing having a crankshaft bearing cover including a bearing top part and a bearing bottom part and a front end gear drive arranged in front of the crankcase for driving auxiliary component and including a first drive gear mounted onto the crankshaft, a second gear mounted to the auxiliary component and an intermediate gear in meshing engagement with the first and second gears and supported on a support plate, the support plate is screwed onto the crankcase, the bearing top part and the bearing bottom part.
Type:
Grant
Filed:
October 21, 2011
Date of Patent:
May 13, 2014
Assignee:
MTU Friedrichshafen GmbH
Inventors:
Joachim Pfau, Jürgen Giesselmann, Manfred Sulzmann
Abstract: Proposed is a method for controlling and regulating an internal combustion engine (1) having a common rail system and having a passive pressure limiting valve (11) for discharging fuel out of a rail (6) into the fuel tank (2), in which method, in a first stage, the pressure limiting valve (11) is set as open when the rail pressure, proceeding from a steady-state rail pressure, exceeds a first threshold value and subsequently falls below a second threshold value within a first critical time, wherein the first threshold value characterizes a higher pressure level than the steady-state rail pressure and the second threshold value characterizes a lower pressure level than the first threshold value, and in which method the opening duration of the opened pressure limiting valve (11) is monitored.
Abstract: Disclosed is a nickel base alloy which is substantially free of rhenium and has a solidus temperature of more than 1320° C. Precipitates of a ??-phase are present in a ?-matrix with a fraction of 40 to 50 vol % at 1050° C. to 1100° C., and a ?/?? mismatch at 1050° C. to 1100° C. is from ?0.15% to ?0.25%. The alloy comprises 11 to 13 at % aluminum, 4 to 14 at % cobalt, 6 to 12 at % chromium, 0.1 to 2 at % molybdenum, 0.1 to 3.5 at % tantalum, 0.1 to 3.5 at % titanium, 0.1 to 3 at % tungsten. The tungsten content of the ?-matrix is greater than that in the precipitated ??-phases.
Type:
Application
Filed:
October 23, 2013
Publication date:
May 1, 2014
Applicant:
MTU AERO ENGINES AG
Inventors:
Ralf RETTIG, Robert F. SINGER, Harald HELMER, Steffen NEUMEIER