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公开(公告)号：EP3628894A1
公开(公告)日：2020-04-01
申请号：EP19205494.8
申请日：2012-12-19
摘要： An epicyclic gear train, 22, includes a carrier, 26, that supports star gears, 32, that mesh with a sun gear, 30. A ring gear, 38, surrounds and meshes with the star gears, 32. Each of the star gears is supported on a respective journal bearing, 34. Each journal bearing includes an internal central cavity, 34a, and at least one passage, 37, that extends radially from the internal cavity to a peripheral journal surface of the respective journal bearing. The epicyclic gear train, 22, has a gear reduction ratio of greater than or equal to about 2.3.
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公开(公告)号：EP3115588B1
公开(公告)日：2020-01-29
申请号：EP16178207.3
申请日：2016-07-06
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公开(公告)号：EP3597883A1
公开(公告)日：2020-01-22
申请号：EP19187436.1
申请日：2019-07-19
摘要： An aircraft propulsion system is disclosed and includes a first gas turbine engine (20A) including a first input shaft (72) driving a first gear system (48A), a first fan (62A) driven by the first gear system (48A), a first generator (64A) supported on the first input shaft (72) and a fan drive electric motor (66A) providing a drive input to the first fan (22A), a second gas turbine engine (20B) including a second input shaft (72) driving a second gear system (48B), a second fan (62B) driven by the second gear system (48B), a second generator (64B) supported on the second input shaft (72) and a second fan drive electric motor (66B) providing a drive input to the second fan (62B) and a controller (68) controlling power output from each of the first and second generators (64A-B) and directing the power output between each of the first and second fan drive electric motors (66A-B).
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公开(公告)号：EP3591193A1
公开(公告)日：2020-01-08
申请号：EP19184263.2
申请日：2019-07-03
摘要： A gas turbine engine (20) includes a first tap (72) connected to a compressor section (24) to deliver air at a first pressure. A heat exchanger (78) is downstream of the first tap (72). A cooling air valve (106a, 106b) selectively blocks flow of cooling air across the heat exchanger (78). A cooling compressor (84) is downstream of the heat exchanger (78) and pressurizes the air from the first tap (72) to a greater second pressure. A shut off valve (82) selectively stops flow of the air between the heat exchanger (78) and the cooling compressor (84). A controller (104) controls the cooling air valve (106a, 106b), the shut off valve (82), and the cooling compressor (84) such that the flow of the air is stopped between the heat exchanger (78) and the cooling compressor (84) only after the controller (104) has stopped the cooling compressor (84). A monitoring system (112) communicates with the controller (112) and includes a pressure sensor (112a) and a temperature sensor (112b) downstream of the cooling compressor (84).
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公开(公告)号：EP3171168B1
公开(公告)日：2020-01-01
申请号：EP16199358.9
申请日：2016-11-17
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公开(公告)号：EP3552971A2
公开(公告)日：2019-10-16
申请号：EP19164870.8
申请日：2019-03-25
摘要： A propulsion system includes an electric fan propulsion motor (818) with a plurality of propulsion motor windings (820). The propulsion system also includes a means for controlling a flow rate of a working fluid (3206) through a cryogenic working fluid flow control assembly (3204) to the propulsion motor windings (820).
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公开(公告)号：EP3550239A1
公开(公告)日：2019-10-09
申请号：EP19165041.5
申请日：2019-03-25
摘要： A cryogenic cooling system (2200) for an aircraft (800) includes a first air cycle machine (2201), a second air cycle machine (2220), and a means for collecting liquid air. The first air cycle machine (2201) is operable to output a cooling air stream (2210) based on a first air source (2204). The second air cycle machine (2220) is operable to output a chilled air stream (2223) at a cryogenic temperature based on a second air source (2221) cooled by the cooling air stream (2210) of the first air cycle machine (2201). An output of the second air cycle machine (2220) is provided to the means for collecting liquid air.
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公开(公告)号：EP3533988A1
公开(公告)日：2019-09-04
申请号：EP19160126.9
申请日：2019-02-28
摘要： A gas turbine engine (201) includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap (156) is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger (158) is connected downstream of the first tap (156) and configured to deliver air to an aircraft fuselage (152). A cooling compressor (164) is connected downstream of the heat exchanger (158). A high pressure feed (200) is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor (164) is configured to deliver air to at least one of the plurality of rotating components. A valve assembly (202) can select whether air from the first tap (156) or air from the high pressure feed (200) is delivered to the aircraft fuselage (152).
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公开(公告)号：EP3483412A1
公开(公告)日：2019-05-15
申请号：EP18206063.2
申请日：2018-11-13
摘要： A gas turbine engine for an aircraft includes a fan section, a turbine section, a compressor section, and an engine bleed system (100). The compressor section includes a low compressor stage proximate to the fan section, a high compressor stage axially downstream from the low compressor stage and proximate to the turbine section, and a mid-compressor stage including variable vane assemblies distributed axially between the low and high compressor stage. The engine bleed system includes engine bleed taps (152A-152D) with a mid-compressor bleed tap (152B) axially between two of the variable vane assemblies, at least one low stage bleed tap (152A) axially upstream from the mid-compressor bleed tap, and at least one high stage bleed tap (152C, 152D) axially downstream from the mid-compressor bleed tap. An external manifold (154) is in pneumatic communication with the mid-compressor bleed tap. A valve system (150) can select one engine bleed tap as a bleed air source for an aircraft use (164).
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100.发明授权
公开(公告)号：EP3205837B1
公开(公告)日：2019-04-03
申请号：EP17155721.8
申请日：2017-02-10
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