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公开(公告)号：US20190040754A1
公开(公告)日：2019-02-07
申请号：US16045867
申请日：2018-07-26
申请人： MTU Aero Engines AG
发明人： Bernd KISLINGER
摘要： A stator vane segment for a turbomachine is provided, in particular for a gas turbine, in particular for a turbine stage of a gas turbine. The stator vane segment has at least one stator vane and at least one shroud, in particular an outer shroud, having at least one first profile disposed on the shroud and adapted for attachment of the stator vane segment to the turbomachine casing, the profile extending in the circumferential direction at least partially over a circumferential length of the stator vane segment along the shroud of the stator vane segment and having at least one functional surface which extends at least partially in the axial direction and in the circumferential direction, at least one functional surface of at least one profile having at least two different curvatures in the circumferential direction in at least one radial plane perpendicular to an axis of rotation of the turbomachine in at least one temperature range below a defined operating temperature of the turbomachine.
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公开(公告)号：US20180347384A1
公开(公告)日：2018-12-06
申请号：US15995304
申请日：2018-06-01
申请人： MTU Aero Engines AG
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F05D2230/10 , F05D2230/232 , F05D2240/55 , F05D2250/283 , F05D2250/75 , F16J15/444
摘要： A sealing system (100) for a turbomachine is provided which includes a support (10) designed as a ring part, and a ring-like sealing plate (20, 30) that protrudes from the support in the axial direction (X). The support includes a fastening section (11) for fastening the sealing system to a stator part (200), and a retaining area (12), situated radially within the fastening section, for retaining a radial gap seal (40). The sealing plate (20, 30) is welded to the support (10) radially outside the retaining area (12). Also provided are a turbomachine that includes a sealing system (100), a support (10) for a sealing system, and a method for manufacturing a sealing system.
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公开(公告)号：US20240102398A1
公开(公告)日：2024-03-28
申请号：US18370528
申请日：2023-09-20
申请人： MTU Aero Engines AG
CPC分类号： F01D11/001 , F01D9/02 , F05D2220/323 , F05D2240/12 , F05D2240/55
摘要： A module for a turbomachine, including a guide blade arrangement, a seal carrier that is situated radially within an inner platform of the guide blade arrangement, seal carrier walls, namely, a first seal carrier wall and a second seal carrier wall, and a sliding body as well as a connecting element. The seal carrier walls have a multipart design with respect to one another, and the second seal carrier wall is fastened to the first seal carrier wall and to the seal carrier via the connecting element. The sliding body holds the seal carrier walls at a distance from one another in such a way that they mutually axially delimit a clearance in which the guide blade arrangement engages via a radially inwardly extending guide pin. A radially inner section of the second seal carrier wall has frictional contact relative to the seal carrier.
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公开(公告)号：US20190264568A1
公开(公告)日：2019-08-29
申请号：US16278263
申请日：2019-02-18
申请人： MTU Aero Engines AG
摘要： A guide vane airfoil for placement in a flow path portion of a turbomachine is provided, which, relative to a flow pattern in flow path portion, has a leading edge and, downstream thereof, a trailing edge, as well as a suction side and a pressure side; relative to a longitudinal axis of the turbomachine, viewed in the axial direction, in a radially inner portion, forming a first angle α with a circular arc about the longitudinal axis, and, in a radially outer portion, a second angle γ with a circular arc about the longitudinal axis. The guide vane airfoil is inclined in the outer portion, thus γ−90°, in terms of absolute value, being >0° (|γ−90°|>0°), and the guide vane airfoil being more highly inclined in the outer portion than in the inner portion, thus γ−90°, in terms of absolute value, being >α−90° (|γ−90°|>α−90°).
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