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公开(公告)号：EP4375487A3
公开(公告)日：2024-08-14
申请号：EP23211748.1
申请日：2023-11-23
CPC分类号： F16J15/441 , F01D11/003 , F01D11/006 , F02C7/28 , F05D2240/5820130101 , F05D2240/6020130101 , F05D2250/7520130101 , F01D5/025 , F01D5/066
摘要： A gas turbine engine rotor assembly is provided that includes a shaft (42), a rotor (36), and a seal assembly (46). The seal assembly (46) is configured to seal between a first and second rotor compartments on opposite sides of the seal assembly (46). The seal assembly (46) includes a seal groove (48) and a split piston ring seal (50). The split piston ring seal (50) is configured such that air in the first rotor compartment at P1 produces a radial force acting on the split piston ring seal (50), and air in the second rotor compartment at P2 produces a second force acting on the split piston ring seal (50), wherein the second force is directed radially inward and the first force is directed radially outward, and the second force is greater than the first force.
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公开(公告)号：EP2964928B1
公开(公告)日：2024-08-07
申请号：EP14759956.7
申请日：2014-03-05
IPC分类号： F16C33/72 , F01D25/16 , F01D11/02 , F02C7/28 , F16C32/06 , F16J15/44 , F16J15/34 , F01D25/18 , F01D25/22
CPC分类号： F16J15/3412 , F16J15/342 , F16J15/441 , F01D25/166 , F01D25/22 , Y02T50/60
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公开(公告)号：EP4386179A1
公开(公告)日：2024-06-19
申请号：EP23216883.1
申请日：2023-12-14
申请人： RTX Corporation
发明人： KLING, Colin J. , LYDERS, David R.
CPC分类号： F01D11/003 , F05D2300/22420130101 , F01D5/066 , F01D11/005 , F05D2300/60320130101 , F05D2250/1520130101 , F05D2250/2520130101 , F16J15/188 , F16J15/30 , F05D2240/5820130101
摘要： A gas turbine engine (20) includes a rotor (62) that has a sealing surface (68) and a shaft (70) that is rotatable about an engine central axis (A). The shaft (70) has an annular seal channel (72) that opens to the seal surface (68), and there is a split seal (74) that is insertable into the annular seal channel (72) for sealing against the seal surface (68). The split seal (74) includes first and second end sections (74a, 74b) that are mateable to each other. The split seal (74) has a helical shape when in a state of rest such that the first and second end sections (74a, 74b) are axially offset from each other.
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公开(公告)号：EP4379192A1
公开(公告)日：2024-06-05
申请号：EP23211575.8
申请日：2023-11-22
申请人： RTX Corporation
CPC分类号： F05D2240/1120130101 , F05D2230/9020130101 , F01D11/003 , F01D5/225 , F01D11/005 , F02C7/28 , F05D2230/1020130101 , F05D2230/1120130101 , F05D2230/1220130101 , F05D2230/1320130101 , F05D2240/5720130101 , F05D2240/8020130101 , F05D2300/51620130101 , F05D2300/603320130101 , F05D2300/61120130101
摘要： A method of coating a seal slot (106a; 106b) includes applying a coating (200) to a slot (106a; 106b) in a component (102; 104) and machining the coating (200) to provide an open height (O) configured to receive a seal (100). After the machining a surface roughness of the coating (200) is less than about 100 ra. A sealing assembly is also disclosed.
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公开(公告)号：EP4375487A2
公开(公告)日：2024-05-29
申请号：EP23211748.1
申请日：2023-11-23
CPC分类号： F16J15/441 , F01D11/003 , F01D11/006 , F02C7/28 , F05D2240/5820130101 , F05D2240/6020130101 , F05D2250/7520130101 , F01D5/025 , F01D5/066
摘要： A gas turbine engine rotor assembly is provided that includes a shaft (42), a rotor (36), and a seal assembly (46). The seal assembly (46) is configured to seal between a first and second rotor compartments on opposite sides of the seal assembly (46). The seal assembly (46) includes a seal groove (48) and a split piston ring seal (50). The split piston ring seal (50) is configured such that air in the first rotor compartment at P1 produces a radial force acting on the split piston ring seal (50), and air in the second rotor compartment at P2 produces a second force acting on the split piston ring seal (50), wherein the second force is directed radially inward and the first force is directed radially outward, and the second force is greater than the first force.
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公开(公告)号：EP4375484A1
公开(公告)日：2024-05-29
申请号：EP23210937.1
申请日：2023-11-20
申请人： RTX Corporation
发明人： WINDER, Calvin Jay , MAALOUF, Fadi S. , BINTZ, Matthew E. , SCHUTTE, Peter T. , DELARM, Justin Roger , VAN LIEU, Pieter , MOHSENI, Hamidreza
CPC分类号： F01D11/003 , F01D11/005 , F02C7/28 , F05D2300/60320130101 , F05D2300/61420130101 , F05D2300/22420130101 , F01D5/066 , F05D2300/603420130101 , F05D2240/5820130101 , F16J15/30
摘要： A gas turbine engine includes a rotor that that has a seal surface (68), a shaft (70) that has an annular seal channel (72) that opens to the seal surface (68), and a seal (74) disposed in the annular seal channel (72) for sealing against the seal surface (68). The seal (74) is made of a composite having carbon fibers disposed in a carbon matrix.
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7.发明授权
公开(公告)号：EP3867505B1
公开(公告)日：2024-05-29
申请号：EP19762145.1
申请日：2019-08-30
CPC分类号： F02B37/186 , F01D11/003 , F02B37/24 , F05D2220/4020130101 , F01D17/105 , F05D2240/5520130101 , F05D2260/60620130101 , Y02T10/12 , F16J15/4476
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公开(公告)号：EP4345253A1
公开(公告)日：2024-04-03
申请号：EP23201066.0
申请日：2023-09-29
申请人： RTX Corporation
摘要： A gas turbine engine includes a primary flow path (206) fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath (202) is positioned radially outward of the primary flowpath (206). A first seal (210) spans from an inner diameter (203) of the cooling air flowpath (202) to an outer diameter of the cooling air flowpath (202). The first seal (210) includes at least one axial convolution (212) and a plurality of pass through features (240,242,244,246,248). A second seal (220) and the first seal (210) are configured to direct a portion of an airflow through the first seal (210) into a cooling air passage (226) and to direct another portion of the airflow radially inward of the cooling air passage (226).
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公开(公告)号：EP4043695B1
公开(公告)日：2024-03-27
申请号：EP22155000.7
申请日：2022-02-03
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公开(公告)号：EP3976935B1
公开(公告)日：2023-12-13
申请号：EP20737258.2
申请日：2020-05-20
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