Patents Assigned to MTU
  • Patent number: 9989093
    Abstract: A roller bearing, particularly a needle bearing, for arranging on a pivot pin of a variable guide vane of a turbomachine, is disclosed. The roller bearing includes at least one radially elastic needle which has two opposing end regions and at least one roller region arranged between the end regions and constructed in a cross-sectionally thickened manner. The end regions roll off at associated raceways of a bearing housing of the roller bearing and the roller region is arranged in the region of an associated groove of the bearing housing. A variable guide vane with at least one such roller bearing, a housing of a turbomachine with such a guide vane, as well as a turbomachine, is also disclosed.
    Type: Grant
    Filed: August 7, 2015
    Date of Patent: June 5, 2018
    Assignee: MTU Aero Engines AG
    Inventor: Alexander Boeck
  • Patent number: 9988927
    Abstract: A housing for a gas turbine is disclosed. At least one wall element is housed on the housing so as to move, which limits a flow channel of the housing in the radial direction from a rotational axis of a rotor of the gas turbine toward the exterior. The housing includes at least one variably adjustable guide blade which extends through the wall element into the flow channel. The wall element can be moved between a sealing setting, in which the wall element makes contact at least in a partial area of a side of a blade leaf of the guide blade facing toward the wall element, and an open setting, in which the blade leaf and the wall element are spaced some distance apart from one another. A gas turbine as well as a process for operating a gas turbine is also disclosed.
    Type: Grant
    Filed: July 29, 2015
    Date of Patent: June 5, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Alexander Boeck, Franz Malzacher
  • Patent number: 9982559
    Abstract: The present invention relates to a blade or vane for a turbomachine, having at least one impulse element housing with a first impact cavity, in which an impulse element is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity, which is in alignment with the first impact cavity in a first matrix direction and in which an impulse element is arranged with play of movement, and has at least one third impact cavity, which is in alignment with the first impact cavity in a second matrix direction crosswise to the first matrix direction and in which an impulse element is arranged with play of movement.
    Type: Grant
    Filed: November 17, 2015
    Date of Patent: May 29, 2018
    Assignee: MTU AERO ENGINES AG
    Inventors: Andreas Hartung, Hermann Klingels, Patrick Wackers, Manfred Feldmann, Frank Stiehler, Markus Schlemmer
  • Patent number: 9982621
    Abstract: A method for operating an internal combustion engine having a hardware structure including an engine control unit and a maintenance unit, an electronic engine identification module and an engine control program, the method having the steps: providing a computer program product via a network by which an engine identification and engine data are loaded together and are exchanged, wherein the computer program product is designed for uploading and/or downloading a maintenance software module by which the engine identification and the engine data are compiled; loading the computer program product onto a non-volatile storage medium; coupling the non-volatile storage medium to the maintenance unit of the hardware structure and executing the computer program product; exchanging the maintenance software module between the non-volatile storage medium and the maintenance unit; identifying the engine and compiling engine data by the maintenance software module and a hardware component of the hardware structure.
    Type: Grant
    Filed: April 15, 2013
    Date of Patent: May 29, 2018
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Albrecht Debelak, Andreas Schneider, Michael Wölki
  • Patent number: 9982620
    Abstract: A method for correcting a fuel quantity injected by a fuel injection device during operation of an internal combustion engine, including: determining an air heat characteristic variable, on which an air heat stream fed to a combustion chamber of the engine functionally depends; determining an exhaust heat characteristic variable, on which an exhaust heat stream discharged from the combustion chamber functionally depends; determining a heat distribution factor, which specifies a fraction of the exhaust heat stream reduced by the air heat stream in relation to a heat stream fed with the injected fuel to the combustion chamber; calculating a fuel mass fed to the engine from the air heat characteristic variable, the exhaust heat characteristic variable and the heat distribution factor; calculating a comparison variable by comparing the calculated fuel mass with a fuel mass setpoint value and adapting actuation of the fuel injection device depending on the comparison variable.
    Type: Grant
    Filed: January 23, 2014
    Date of Patent: May 29, 2018
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Andreas Flohr, Francois Layec
  • Patent number: 9982633
    Abstract: A gas internal combustion engine, having a gas mixer, an intake section and an engine to which a fuel mixture having a charging mixture is fed. The engine is operated in the gas mode with gas as the fuel in the charging mixture. By an input mixture portion, from an earlier mixture state, of a gas/air mixture, an output mixture portion, from a later mixture state, of the gas/air mixture is determined by an intake section model. The output mixture portion is determined at an engine feed, the input mixture portion is determined over a number of intermediate states of the mixture portion in a number of assigned volumes of the intake section. The intake mixture portion of a gas/air mixture is determined at the gas mixer, and an air stream and/or gas stream is set at the gas mixer in accordance with the input mixture portion.
    Type: Grant
    Filed: January 20, 2014
    Date of Patent: May 29, 2018
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Andreas Flohr, Andreas Geller
  • Patent number: 9982566
    Abstract: A turbomachine includes a sealing segment ring that is provided between a front guide vane row and a back guide vane row for sealing a radial gap between a casing section and a rotor blade row rotating between the guide vane rows, wherein the sealing segment ring has a plurality of identical sealing segments and at least one of the guide vane rows has a plurality of identical guide vane segments, wherein the sealing segments each have a plurality of engagement sites lying adjacent to one another in the peripheral direction for interaction with securing elements of this guide vane row, wherein the engagement sites and securing elements are distributed uniformly over the periphery and the engagement sites are a multiple of the securing elements, a sealing element, and a guide vane segment.
    Type: Grant
    Filed: July 11, 2014
    Date of Patent: May 29, 2018
    Assignee: MTU AERO ENGINES AG
    Inventors: Walter Gieg, Petra Kufner, Rudolf Stanka
  • Patent number: 9982547
    Abstract: A guide mechanism for a gas turbine has a casing supporting on its interior a duct delimited by radially inner and outer duct segments. A variable guide vane located at least partially within the duct can rotate about an axis of rotation to guide flow of a fluid in the duct. The radially inner duct segment is fastened to the guide vane and is retained on the casing element via the guide vane, which is mounted on the casing element via a bushing inserted in the radial direction from outside to inside into a passage opening of the casing element.
    Type: Grant
    Filed: June 23, 2015
    Date of Patent: May 29, 2018
    Assignee: MTU AERO ENGINES AG
    Inventor: Alexander Boeck
  • Publication number: 20180142567
    Abstract: The present invention relates to a sealing system for an axial turbomachine for a gas turbine, including a rotor with a radially outward arranged shroud and a housing that surrounds the rotor, wherein a gap is arranged between the shroud and the housing, and wherein the gap is bounded by a seal, which is joined to the housing, and at least one sealing tip arranged at the shroud opposite to the seal, for reducing the flow losses through the gap. At the downstream end region of the seal, another static sealing tip, which is joined to the housing, is arranged for influencing the flow through the gap and/or for influencing the flow downstream of the static sealing tip. The present invention further relates to an axial turbomachine with at least one low-pressure turbine stage, wherein the low-pressure turbine stage comprises a sealing system according to the invention.
    Type: Application
    Filed: November 16, 2017
    Publication date: May 24, 2018
    Applicant: MTU Aero Engines AG
    Inventor: Hermann Klingels
  • Patent number: 9970314
    Abstract: An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.
    Type: Grant
    Filed: May 1, 2012
    Date of Patent: May 15, 2018
    Assignee: MTU Aero Engines GmbH
    Inventor: Frank Stiehler
  • Patent number: 9964496
    Abstract: The invention relates to a method for the quality assessment of a component produced by means of an additive manufacturing method. In the course of the method, it is checked first of all whether the component violates predetermined absolute limits in order to rule out the existence of serious malfunctions in the additive manufacturing process. Subsequently, a component-dependent targeting process is determined. On the basis of this targeting process, the limits for deviations are established and deviating actual values of the component are isolated and assessed by means of various parameters.
    Type: Grant
    Filed: August 17, 2015
    Date of Patent: May 8, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Thomas Hess, Alexander Ladewig
  • Patent number: 9963993
    Abstract: A turbine ring of a turbomachine is described, having a one-piece ring structure which has an outer ring which is continuous in the circumferential direction of the turbine ring and has a fastening section for fastening the turbine ring on a housing section of the turbomachine, an inner ring which is segmented in the circumferential direction and has a plurality of inner ring segments which are mutually displaceable in the circumferential direction for guiding the hot gas and has front sealing segments and rear sealing segments, as seen in the axial direction of the turbine ring, these sealing segments being spaced a distance apart from one another in the axial direction and extending between the inner ring and the outer ring, as well as a turbomachine having such a turbine ring.
    Type: Grant
    Filed: October 29, 2013
    Date of Patent: May 8, 2018
    Assignee: MTU Aero Engines AG
    Inventor: Manfred Feldmann
  • Patent number: 9963973
    Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.
    Type: Grant
    Filed: November 5, 2015
    Date of Patent: May 8, 2018
    Assignee: MTU Aero Engines GmbH
    Inventors: Roland Wunderer, Harald Passrucker
  • Publication number: 20180119552
    Abstract: An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.
    Type: Application
    Filed: October 25, 2017
    Publication date: May 3, 2018
    Applicant: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Gerhard-Heinz Roesele, Martin Pernleitner, Manfred Schill, Manfred Feldmann, Adrian Ehrenberg
  • Publication number: 20180119567
    Abstract: An inner ring according to the invention or an inner ring segment according to the invention for an adjustable guide vane assembly comprises a plurality of uptakes, each for the bearing of an adjustable guide vane. The uptakes here each form an essentially ellipsoidally shaped uptake space for a guide vane head of the respective guide vane. A guide vane according to the invention for an adjustable guide vane assembly has a blade body and a guide vane head. The guide vane head is essentially ellipsoidal in shape and is equipped to be accommodated pivotably in an uptake of an inner ring or inner ring segment of the guide vane assembly.
    Type: Application
    Filed: October 25, 2017
    Publication date: May 3, 2018
    Applicant: MTU Aero Engines AG
    Inventors: Joachim Wulf, Philipp Langholf, Manuel Hein
  • Patent number: 9956652
    Abstract: A method for producing a rotor, particularly a turbine disk or a turbine ring for a turbine stage of a turbomachine, wherein at least the following steps are carried out: producing a blade ring (14) including a plurality of rotor blades (12), welding adapters (22) together which are disposed in the region of blade footings of the rotor blades (12), wherein at least substantially radial weld seams (30a) having predetermined welding depths are generated, disposing a rotor disk (32) or a rotor ring on the blade ring (14), and welding the rotor disk (32) or the rotor ring to the adapters (22) of the rotor blades (12), wherein at least one further weld seam (30b) is generated. A rotor, particularly a turbine disk or a turbine ring for a turbine stage of a turbomachine is also disclosed.
    Type: Grant
    Filed: October 7, 2009
    Date of Patent: May 1, 2018
    Assignee: MTU Aero Engines GmbH
    Inventor: Robert Schmidt
  • Patent number: 9957833
    Abstract: A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange. The sealing flange has a recess arrangement with at least one radial recess in which, centrally in particular, a radial projection is arranged. There is arranged on the housing a sensor arrangement with at least one capacitive sensor for detecting a radial clearance to a peripheral surface of the sealing flange.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: May 1, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Florian Gerbl, Juergen Gruendmayer, Martin Stadlbauer, Ernst Trassl
  • Patent number: 9951623
    Abstract: A blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another, on which first element arrangements that are identical to one another and have at least one first element are movably mounted; and a second group with at least two, in particular at least three, second blade arrangements, which are of the same type to one another and are of different type from the first blade arrangements, on which second element arrangements, which are identical to one another and have at least one second element are movably mounted, wherein first and second element arrangements are different from each other.
    Type: Grant
    Filed: July 16, 2015
    Date of Patent: April 24, 2018
    Assignee: MTU AERO ENGINES AG
    Inventors: Andreas Hartung, Frank Stiehler, Martin Pernleitner
  • Patent number: 9951411
    Abstract: The invention relates to an erosion protection coating (11), in particular, for gas turbine components, having a horizontally segmented and/or multi-layered construction. i.e., having at least one relatively hard layer (12) and having at least one relatively soft layer (13), wherein the relatively hard layer or each relatively hard layer as well as the relatively soft layer or each relatively soft layer are disposed on top of one another in an alternating manner, in such a way that an outer-lying layer, which forms an outer surface of the erosion protection coating, is formed as a relatively hard layer (12). According to the invention, the relatively hard layer or each relatively hard layer (12) as well as the relatively soft layer or each relatively soft layer (13) are formed as a ceramic layer in each case.
    Type: Grant
    Filed: April 18, 2009
    Date of Patent: April 24, 2018
    Assignee: MTU AERO ENGINES GmbH
    Inventors: Falko Heutling, Thomas Uihlein, Wolfgang Eichmann
  • Patent number: 9951631
    Abstract: A rotor blade for a turbomachine, including an airfoil (1) for flow deflection, a blade root (2) for attachment to a rotor of the turbomachine, an inner platform (3) between the airfoil and the blade root, and at least one pocket (4, 5) defined by two axially spaced walls (4.1, 4.2; 5.1, 5.2) extending from the side of the platform opposite the airfoil toward the blade root. A first (4.1, 5.1) of these walls has an outer side (4.1A, 5.1A) that faces away from the pocket and, in at least one cross section perpendicular to a radial longitudinal axis of the rotor blade, slopes outwardly.
    Type: Grant
    Filed: June 26, 2014
    Date of Patent: April 24, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Krzysztof Skura, Marcin Kozdras, Lukasz Sosnowka, Manfred Feldmann, Manfred Schill