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公开(公告)号：US10371054B2
公开(公告)日：2019-08-06
申请号：US14972767
申请日：2015-12-17
Applicant: MTU Aero Engines AG
Inventor： Stefan Sasse , Erwin Bayer
Abstract: A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine. In the axial direction, the respective axial bounding wall having the cooling-air outlet orifices has a layer-type structure; the cooling-air outlet orifices being formed by deformation of at least one first cooling air chamber-side layer and by deformation of at least one second, turbine-side layer.
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公开(公告)号：US10215050B2
公开(公告)日：2019-02-26
申请号：US14475238
申请日：2014-09-02
Applicant: MTU Aero Engines AG
Inventor： Stefan Sasse , Norbert Schinko
Abstract: An apparatus for absorption of an impact energy from at least one blade fragment is disclosed. The impact energy acts on an element that is inserted into an opening in a turbo-machine. The opening passes radially through a housing section in a region of a row of rotating blades. The apparatus has a holder for holding the element in an ideal position and releasing the element beyond a preset maximum load and has a cage at a rear to secure the element in a radially outward-directed displacement. A turbo-machine having such an apparatus, as well as a method for multistage energy absorption, is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20160177831A1
公开(公告)日：2016-06-23
申请号：US14972767
申请日：2015-12-17
Applicant: MTU Aero Engines AG
Inventor： Stefan Sasse , Erwin Bayer
CPC classification number: F02C7/18 , F01D5/02 , F01D5/082 , F01D25/24 , F02C3/04 , F05D2220/3213 , F05D2230/54 , F05D2240/35 , F05D2240/61 , F05D2260/14 , F05D2260/20 , F05D2260/201 , F05D2300/6033 , F05D2300/702 , Y02T50/672 , Y02T50/676
Abstract: A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine. In the axial direction, the respective axial bounding wall having the cooling-air outlet orifices has a layer-type structure; the cooling-air outlet orifices being formed by deformation of at least one first cooling air chamber-side layer and by deformation of at least one second, turbine-side layer.
Abstract translation: 一种用于燃气轮机的冷却空气供应装置，特别是包括冷却空气室的飞机燃气轮机，其设置在燃气轮机的涡轮机轴周围，至少一个冷却空气入口，以及至少一个冷却 出口孔; 所述冷却空气供应装置具有第一和第二轴向边界壁，以及连接两个轴向边界壁的周壁，所述两个轴向边界壁一起形成冷却空气室; 在轴向边界壁中的至少一个中，设置有多个冷却空气出口孔，其周向分布在涡轮轴上并且适于允许冷却空气基本上从单独的冷却空气出口孔排出 燃气轮机的旋转方向。 在轴向方向上，具有冷却空气出口孔的相应轴向边界壁具有层型结构; 所述冷却空气出口孔由至少一个第一冷却空气室侧层的变形和至少一个第二涡轮机侧层的变形形成。
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公开(公告)号：US20150377068A1
公开(公告)日：2015-12-31
申请号：US14730801
申请日：2015-06-04
Applicant: MTU Aero Engines AG
Inventor： Alois Eichinger , Stefan Sasse , Mark Fritz
CPC classification number: F01D25/28 , B23P19/04 , F01D25/243 , F23R3/002
Abstract: The present invention relates to a component arrangement for a gas turbine, having a first component of a gas turbine duct casing; a second component, connected to it, of a gas turbine duct casing with a flange; a rocker with an articulated section, which is rotatably mounted in a groove on the first component, which, in a cross section perpendicular to the groove longitudinal direction, has two groove flanks that lie opposite each other in the groove width direction, a groove base connecting these groove flanks, and a groove edge that lies opposite the groove base in a groove depth direction; and a setting screw. The flange of the second component is clamped between the first component and an arm of the rocker, which is tightened against the flange by the setting screw.
Abstract translation: 本发明涉及一种用于燃气轮机的部件装置，具有燃气轮机管壳体的第一部件; 与其连接的具有凸缘的燃气涡轮机管壳的第二部件; 具有铰接部的摇杆，其可旋转地安装在第一部件上的槽中，该槽在垂直于槽纵向的横截面中具有在槽宽度方向上彼此相对的两个槽侧面，槽基部 连接这些沟槽侧面，以及在沟槽深度方向上与槽底部相对的槽边缘; 和定位螺丝。 第二部件的凸缘被夹紧在第一部件和摇臂的臂之间，其通过定位螺钉紧固在凸缘上。
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公开(公告)号：US09726042B2
公开(公告)日：2017-08-08
申请号：US14638775
申请日：2015-03-04
Applicant: MTU Aero Engines AG
Inventor： Stefan Sasse , Martin Metscher , Jan Haegert
CPC classification number: F01D25/243 , F01D9/065 , F01D25/162 , F02C7/20 , F05D2230/60 , F05D2230/70 , F05D2240/14 , F05D2260/30 , F05D2260/36 , F05D2260/37 , Y10T29/49229
Abstract: A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a clamp arrangement. The clamp arrangement has at least one clamp and one bolt which passes through a hole in the clamp and is screwed to a nut on a side of the clamp facing away from the wall segments. The nut braces at least one first leg of the clamp against the first wall segment, in particular by an intermediate element, and braces at least one second leg of the clamp against the second wall segment. The bolt has a head which is guided in a form-fitting manner in a groove on the outside of the first wall segment facing away from the gas duct.
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公开(公告)号：US20160032777A1
公开(公告)日：2016-02-04
申请号：US14805496
申请日：2015-07-22
Applicant: MTU Aero Engines AG
Inventor： Stefan Sasse
IPC: F01D25/24
CPC classification number: F01D25/243 , F05D2220/32 , F05D2230/60 , F05D2260/37 , F05D2260/56
Abstract: The present invention relates to a component arrangement of a gas turbine, this arrangement having a first gas turbine component, in particular a first wall segment (10) of a gas turbine duct casing; a second gas turbine component that can be joined thereto, in particular a second wall segment (20) of a gas turbine duct casing, with a flange (21), which is particularly bent; and an eccentric clamping element (30), which is mounted rotatably about an axis of rotation (A) on the first gas turbine component and has an eccentric contour portion (31), whose radial distance (r) to the axis of rotation varies by an angle (φ) about the axis of rotation, in order to press the flange (21) of the second gas turbine component (20) against the first gas turbine component, in particular to clamp it between the first gas turbine component and the eccentric contour portion (31).
Abstract translation: 本发明涉及一种燃气轮机的部件布置，该装置具有第一燃气轮机部件，特别是燃气轮机管壳体的第一壁段（10）; 能与其连接的第二燃气涡轮机部件，特别是燃气轮机管道壳体的第二壁部分（20），其具有特别弯曲的凸缘（21）; 以及偏心夹紧元件（30），其围绕第一燃气轮机部件的旋转轴线（A）可旋转地安装，并且具有偏心轮廓部分（31），其偏心轴线的径向距离（r） 围绕旋转轴线的角度（＆phgr），以便将第二燃气轮机部件（20）的凸缘（21）压靠第一燃气轮机部件，特别是将其夹紧在第一燃气轮机部件和 偏心轮廓部分（31）。
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7.发明申请公开(公告)号：US20140363270A1
公开(公告)日：2014-12-11
申请号：US14295959
申请日：2014-06-04
Applicant: MTU Aero Engines AG
Inventor： Manfred FELDMANN , Stefan Sasse
IPC: F01D21/04
CPC classification number: F01D21/045 , F01D25/24 , F05D2300/702 , Y02T50/672
Abstract: A turbine casing (100) for a gas turbine, having a casing section (5a, 5b, 5c, 5d, 5e), the casing section (5a, 5b, 5c, 5d, 5e) having a containment section (16) for containing blade fragments expelled radially outward. The casing section (5a, 5b, 5c, 5d, 5e) has a first reinforcing element (1a, 1b, 1c, 1d, 1e) which is joined in face-to-face contact with the radially inner and/or outer surface of the casing section (5a, 5b, 5c, 5d, 5e).
Abstract translation: 一种用于燃气轮机的涡轮壳体（100），具有壳体部分（5a，5b，5c，5d，5e），所述壳体部分（5a，5b，5c，5d，5e）具有容纳部分（16） 刀片碎片径向向外排出。 壳体部分（5a，5b，5c，5d，5e）具有与第一加强元件（1a，1b，1c，1d，1e）的径向内侧和/ 壳体部分（5a，5b，5c，5d，5e）。
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