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公开(公告)号：EP3697691A1
公开(公告)日：2020-08-26
申请号：EP18867996.3
申请日：2018-10-15
申请人： Bombardier Inc.
发明人： SADRI, Reza , DUSSAULT, Kathleen , BOILEAU, Edmond
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公开(公告)号：EP3569498A1
公开(公告)日：2019-11-20
申请号：EP19171413.8
申请日：2019-04-26
申请人： Rolls-Royce plc
发明人： Scothern, David
摘要： A hybrid aircraft propulsion system. The sytem comprises a gas turbine engine (5) comprising a compressor (11), a combustor (12), one or more turbines (13), a shaft (14) coupled to one of the turbines (13), and a bypass fan (10) mechanically driven by the shaft (14). The system further comprises an electrical generator (15) mechanically coupled to the shaft (14), and an auxiliary propulsor (6) mechanically coupled to an electric motor (16) and electrically coupled to the electric generator (15). At maximum power, the gas turbine engine (5) is configured to produce a turbine entry temperature at maximum power between 1800 Kelvin and 2000 Kelvin, the engine comprises a fan bypass ratio of between 4:1 and 13:1, and the generator is configured to absorb between 10% and 60% of the mechanical power generated by the turbine.
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公开(公告)号：EP3487763A1
公开(公告)日：2019-05-29
申请号：EP17754400.4
申请日：2017-07-20
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公开(公告)号：EP3418195A1
公开(公告)日：2018-12-26
申请号：EP17461552.6
申请日：2017-06-21
发明人： IGLEWSKI, Tomasz
CPC分类号： B64D33/04 , B64D27/12 , B64D2033/0293 , F01D25/30
摘要： An aircraft engine assembly (15) can include an engine (16) having an exhaust turbine with drive shaft (21) and exhaust collector (25), a propeller (17) rotationally coupled to the drive shaft (21) and defining a rotational axis (20), and an exhaust stub (30) to direct exhaust gases away from the aircraft (1).
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公开(公告)号：EP3052783B1
公开(公告)日：2018-08-08
申请号：EP14850274.3
申请日：2014-08-29
CPC分类号： B64D33/04 , B64D41/00 , B64D2041/002 , F01D25/28 , F01D25/30 , F02C7/20 , F02K1/04 , F05D2220/50 , F05D2230/60 , F05D2230/644 , F05D2250/241 , F05D2250/711 , F05D2250/712 , F05D2260/30
摘要： An exhaust system for an aircraft includes an exhaust duct configured to be inserted within a plurality of leaf springs of an aircraft. The exhaust duct is configured to be in fluid communication with the auxiliary power unit for conveying exhaust from the auxiliary power unit to an exhaust exit, the exhaust duct including at least one exhaust bracket for movably mounting the exhaust duct to an airframe. An alignment system is configured to be operatively connected to the exhaust duct.
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公开(公告)号：EP3323730A1
公开(公告)日：2018-05-23
申请号：EP17199663.0
申请日：2017-11-02
发明人： Keller, Richard
摘要： An airplane (10) including an airframe (12) and a turboprop propulsion system (14) is disclosed. The turboprop propulsion system (14) includes a propeller (20) mounted for rotation about a propeller axis (30) and a gas turbine engine (22) coupled to the propeller (20) to drive rotation of the propeller (30). The gas turbine engine (22) rotates about an axis (32) which is offset from the propeller axis (30).
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公开(公告)号：EP2943670A4
公开(公告)日：2016-01-20
申请号：EP13870617
申请日：2013-06-04
发明人： SUCIU GABRIEL L , CHANDLER JESSE M
CPC分类号： F02C7/36 , B64D27/10 , B64D2027/005 , F02C7/06 , F02C7/20 , F02C7/32 , F02K3/072 , F05D2240/90 , Y02T50/66
摘要： A gas turbine engine has a first shaft including a first turbine rotor, and a second shaft including a second turbine rotor disposed downstream of the first turbine rotor. A third shaft includes a propulsor turbine positioned downstream of the second turbine rotor for driving a propeller. A mount ring is secured between the second turbine rotor and the propeller.
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