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公开(公告)号：EP4127435B1
公开(公告)日：2024-09-25
申请号：EP21715479.8
申请日：2021-03-19
CPC分类号： F02C1/10 , F05D2220/6220130101 , F05D2260/21120130101 , F05D2240/5120130101 , F05D2220/7620130101 , F02C7/06 , F01D25/24 , F01D15/10
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公开(公告)号：EP3832074B1
公开(公告)日：2024-08-07
申请号：EP20212191.9
申请日：2020-12-07
CPC分类号： F01D25/08 , F05D2260/21120130101 , F01D25/12 , F28D1/06 , F28D2021/002620130101 , F28D2021/002120130101 , Y02T50/60
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公开(公告)号：EP3660294B1
公开(公告)日：2024-07-31
申请号：EP19206261.0
申请日：2019-10-30
CPC分类号： F02C6/00 , F02C7/10 , F05D2260/21120130101
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公开(公告)号：EP3325794B1
公开(公告)日：2024-07-03
申请号：EP16751205.2
申请日：2016-07-22
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公开(公告)号：EP3552971B1
公开(公告)日：2024-04-24
申请号：EP19164870.8
申请日：2019-03-25
IPC分类号： B64D27/24 , B64D33/08 , H02K9/08 , F17C5/02 , F25J1/00 , B64D13/06 , F02C6/08 , B64D37/32 , F25J3/04
CPC分类号： B64D33/08 , B64D2013/067420130101 , F02C6/08 , B64D13/06 , B64D37/32 , B64D2013/065920130101 , B64D2013/067720130101 , F25J3/04533 , F25J3/04563 , F25J3/046 , F25J3/04975 , F25J3/0429 , F25J2215/4020130101 , F25J2205/8620130101 , F25J3/04636 , F05D2260/20520130101 , F05D2260/21120130101 , F25J1/0012 , F25J1/0221 , F25J2210/4020130101 , F25J2230/3020130101 , F25J2230/0820130101 , F25J1/0035 , F25J1/0275 , Y02T50/50
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公开(公告)号：EP4414546A2
公开(公告)日：2024-08-14
申请号：EP24156423.6
申请日：2024-02-07
申请人： RTX Corporation
发明人： CHANDLER, Jesse M.
CPC分类号： F02C7/143 , F05D2260/21320130101 , F05D2260/21120130101 , F05D2250/31320130101 , F02C7/224
摘要： An intercooler (200) for a gas turbine engine (14) can include a shell (222) having a partial annular shape, the shell defining a duct (225) comprising an inlet (210) and an outlet (230), the shell defining a first flow path between the inlet and the outlet; a supply manifold (242) disposed proximate the outlet of the duct and extending circumferentially around the shell; and an outlet manifold (244) disposed proximate the inlet of the duct and extending circumferentially around the shell, the supply manifold in fluid communication with the outlet manifold through a heat transfer region (224) in the duct.
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公开(公告)号：EP4321744A3
公开(公告)日：2024-05-01
申请号：EP23191398.9
申请日：2023-08-14
申请人： RTX Corporation
CPC分类号： F02C7/185 , F02C3/22 , F02C7/143 , F02C7/224 , F02C3/305 , F05D2220/6220130101 , F05D2220/7220130101 , F05D2260/21120130101
摘要： A propulsion system for an aircraft includes a core engine that includes a core flow path (C) where a core flow (50) is compressed in a compressor section (24), communicated to a combustor section (30), mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a turbine section (32). A fuel system (56) is configured to supply a hydrogen based fuel to the combustor (30) through a fuel flow path (62). A condenser (72) is arranged along the core flow path (C) and configured to extract water from the gas flow. An intercooling system (90) receives a portion of water from the condenser (72) for cooling a portion of the core flow (50) at a first location within the compressor section (24). Heated water from the intercooling system (90) is exhausted to a second location within the core flow path (C) downstream of the first location.
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公开(公告)号：EP3988878B1
公开(公告)日：2024-04-24
申请号：EP21206279.8
申请日：2019-03-25
CPC分类号： B64D33/08 , B64D2013/067420130101 , F02C6/08 , B64D13/06 , B64D37/32 , B64D2013/065920130101 , B64D2013/067720130101 , F25J3/04533 , F25J3/04563 , F25J3/046 , F25J3/04975 , F25J3/0429 , F25J2215/4020130101 , F25J2205/8620130101 , F25J3/04636 , F05D2260/20520130101 , F05D2260/21120130101 , F25J1/0012 , F25J1/0221 , F25J2210/4020130101 , F25J2230/3020130101 , F25J2230/0820130101 , F25J1/0035 , F25J1/0275 , Y02T50/50
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公开(公告)号：EP4414546A3
公开(公告)日：2024-10-09
申请号：EP24156423.6
申请日：2024-02-07
申请人： RTX Corporation
发明人： CHANDLER, Jesse M.
CPC分类号： F02C7/143 , F05D2260/21320130101 , F05D2260/21120130101 , F05D2250/31320130101 , F02C7/224 , F02C7/18 , F02C3/00
摘要： An intercooler (200) for a gas turbine engine (14) can include a shell (222) having a partial annular shape, the shell defining a duct (225) comprising an inlet (210) and an outlet (230), the shell defining a first flow path between the inlet and the outlet; a supply manifold (242) disposed proximate the outlet of the duct and extending circumferentially around the shell; and an outlet manifold (244) disposed proximate the inlet of the duct and extending circumferentially around the shell, the supply manifold in fluid communication with the outlet manifold through a heat transfer region (224) in the duct.
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公开(公告)号：EP4403858A2
公开(公告)日：2024-07-24
申请号：EP24167787.1
申请日：2019-03-25
申请人： RTX Corporation
IPC分类号： F25J3/04
CPC分类号： B64D33/08 , B64D2013/067420130101 , F02C6/08 , B64D13/06 , B64D37/32 , B64D2013/065920130101 , B64D2013/067720130101 , F25J3/04533 , F25J3/04563 , F25J3/046 , F25J3/04975 , F25J3/0429 , F25J2215/4020130101 , F25J2205/8620130101 , F25J3/04636 , F05D2260/20520130101 , F05D2260/21120130101 , F25J1/0012 , F25J1/0221 , F25J2210/4020130101 , F25J2230/3020130101 , F25J2230/0820130101 , F25J1/0035 , F25J1/0275 , Y02T50/50 , Y02T50/60
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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