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公开(公告)号：US11125115B2
公开(公告)日：2021-09-21
申请号：US16266612
申请日：2019-02-04
申请人： MTU Aero Engines AG
发明人： Werner Humhauser
摘要： Described is a connecting device (50) for a variable vane (51) of a gas turbine (10), in particular of an aircraft gas turbine, the connecting device including a trunnion element (52) connected to a respective vane (51); a lever element (54) connected to the trunnion element (52), the lever element (54) and the trunnion element (52) being movable together about a trunnion axis of rotation (ZD). It is provided that the lever element (54) and the trunnion element (52) be aligned with each other by a positioning element (68), the positioning element (68) being received in a trunnion receptacle (60) and a lever receptacle (66, 66a, 66b).
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公开(公告)号：US20210285838A1
公开(公告)日：2021-09-16
申请号：US17194678
申请日：2021-03-08
申请人： MTU Aero Engines AG
发明人： Sebastian Weber , Manfred Feldmann
摘要： The invention relates to a method and a set of balance weights for balancing a rotor, particularly of a turbomachine, on which a plurality of balance weights, which are distributed over the periphery, can be arranged for balancing an imbalance. A set of balance weights, in particular plate-shaped weights, with a predetermined number of groups of balance weights, is used for balancing the rotor. Each of the balance weights of every group of balance weights has an identical weight that is assigned to this group and a shape assigned to this group, which differs in basic shape and/or thickness of the balance weights from the balance weights of the other groups.
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43.发明授权公开(公告)号：US11098603B2
公开(公告)日：2021-08-24
申请号：US16293897
申请日：2019-03-06
申请人： MTU Aero Engines AG
发明人： Lothar Albers
摘要： The invention relates to an inner ring for a guide vane assembly for mounting adjustable guide vanes of a turbomachine, of a compressor stage or turbine stage of a gas turbine, a guide vane assembly for a turbomachine having an inner ring, a turbomachine having an inner ring, and a method for producing an inner ring, wherein the inner ring has a plurality of guide vane bearing mounts, which are each arranged spaced apart in the peripheral direction, recesses, which are each formed for receiving a bearing element, a bearing journal, of a guide vane, wherein, between at least two adjacent guide vane bearing mounts, the inner ring has at least one depression with a wall thickness in a radial direction that is reduced in comparison to a region that abuts the depression and is outside of the depression.
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公开(公告)号：US11085453B2
公开(公告)日：2021-08-10
申请号：US16518057
申请日：2019-07-22
申请人： MTU Aero Engines AG
摘要： An engine, having a first, second, third and fourth quasi-stage, each with a stator and a downstream rotor, wherein a particular blade/vane solidity in the center section is in the first quasi-stage, at least 1.04 and at most 1.16 for the stator and at least 1.46 and at most 1.67 for the rotor; in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor; in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor; in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.
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45.发明申请公开(公告)号：US20210207500A1
公开(公告)日：2021-07-08
申请号：US17056085
申请日：2019-05-21
申请人： MTU Aero Engines AG
发明人： Hermann KLINGELS , Oliver SCHMITZ
摘要： An exhaust gas treatment device, an aircraft propulsion system and method for treating an exhaust gas stream are provided. The exhaust gas treatment has a condenser, which condenses at least a portion of water contained in the exhaust gas stream from the turbomachine and thereby releases a first energy; an evaporator, which evaporates at least a portion of the water condensed in the condenser and thereby absorbs a second energy, which is extracted from the exhaust gas stream from the turbomachine; a turbine, which is driven by steam output by the evaporator and expands the steam; a fan, which can be driven by the turbine and feeds the condenser ambient air in order that it absorb the first energy; and at least one exhaust apparatus, out of which the ambient air given off by the condenser and/or a dehumidified exhaust gas stream is exhausted from the condenser.
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公开(公告)号：US10947850B2
公开(公告)日：2021-03-16
申请号：US16125104
申请日：2018-09-07
申请人： MTU Aero Engines AG
摘要： A blade (10) for a turbomachine is provided. The blade (10) includes an airfoil (16) having at least one thickening (22) on a pressure side (20) of the airfoil (16). The thickening (22) has a region (B) of constant thickness (D). A turbomachine, a compressor and a turbine having stator vanes and/or rotor blades including at least one such blade (10) is also provided.
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公开(公告)号：US10895162B2
公开(公告)日：2021-01-19
申请号：US15428386
申请日：2017-02-09
申请人： MTU Aero Engines AG
摘要： The invention relates to a guide vane segment for an aircraft engine, having at least one guide vane element, having at least one flange formed in a radial extension direction (R) of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction (R), and at least one seal carrier, which is arranged at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported, wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle (α) that is different from a zero angle.
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公开(公告)号：US20210001269A1
公开(公告)日：2021-01-07
申请号：US16977181
申请日：2019-02-27
申请人： MTU Aero Engines AG
发明人： Hermann KLINGELS
摘要： A method is described for reducing contrails during operation of an aircraft (100, 100′) having a heat engine 10. The method includes inducing a condensation of moisture contained in the exhaust gas (A) of the heat engine by mixing at least a portion of the exhaust gas with ambient air (U) of the aircraft as well as separating the condensed-out water on the aircraft. Also described is an aircraft (100, 100′) having a heat engine (10). The aircraft includes at least one nozzle (30) which is adapted for conducting exhaust gas (A) from the heat engine of the aircraft at least partially into ambient air (U) of the aircraft and thus to produce a gas mixture, and at least one separator device (40) for separating condensed-out water from the gas mixture.
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公开(公告)号：US10830090B2
公开(公告)日：2020-11-10
申请号：US15825962
申请日：2017-11-29
申请人： MTU Aero Engines AG
发明人： Vitalis Mairhanser
摘要： A lever assembly forming part of a vane actuating mechanism and serving to connect a stator vane of a turbomachine to an actuating ring of an actuator is provided. The lever assembly is adapted such that an actuating lever of the lever assembly is moved in a first mounting direction transversely to a vane stem of the stator vane extending radially relative to a longitudinal machine axis of the turbomachine and is thereby positioned laterally against the vane stem, and that the actuating lever is radially form-fittingly locked to the vane stem by a locking piece in a second mounting direction. An assembly method and a turbomachine is also provided.
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公开(公告)号：US10830084B2
公开(公告)日：2020-11-10
申请号：US16129401
申请日：2018-09-12
申请人： MTU Aero Engines AG
发明人： Werner Humhauser
摘要： The present invention relates to a housing for a gas turbine compressor, having an operating duct for taking up several rows of rotating blades arranged one behind the other axially, wherein a wall of the operating duct has a first air bleed, wherein the housing has a cooling passage for cooling said operating duct wall by conveying air from the first air bleed to a first outlet passage for supplying at least one first bleed air consumer, wherein the first outlet passage is arranged downstream of the first air bleed, and wherein the operating duct wall has a second air bleed downstream of the first air bleed, and the housing has a discharge passage from said second air bleed to a second outlet passage for supplying at least one bleed air consumer.
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