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公开(公告)号：EP4375496A3
公开(公告)日：2024-10-09
申请号：EP24169542.8
申请日：2013-10-23
IPC分类号： F01D5/14 , B64C11/18 , B64C11/46 , F02K3/02 , F02C6/20 , F03D1/06 , B64D33/02 , B64D33/04 , F02K1/46 , F02C7/36
CPC分类号： B64C11/46 , F02K3/025 , F02C6/206 , F05B2240/1220130101 , F05B2260/9620130101 , F05D2220/32520130101 , F05D2250/3020130101 , F05D2260/1420130101 , F05D2220/32420130101 , F05D2250/5220130101 , F02K1/46 , F05D2250/5120130101 , B64C11/18 , Y02E10/72 , B64C11/00 , F05D2260/4031120130101 , F02C7/36 , F05D2250/7020130101 , F05D2220/9020130101 , F05D2240/30120130101 , Y02T50/60
摘要： A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.
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2.发明公开
公开(公告)号：EP4320341A1
公开(公告)日：2024-02-14
申请号：EP22718745.7
申请日：2022-03-31
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公开(公告)号：EP4227515A1
公开(公告)日：2023-08-16
申请号：EP23156273.7
申请日：2023-02-13
摘要： An engine system (200) includes a turbine engine (202) including a compressor section (206), a combustor section (208) having a burner, a turbine section (210), and a nozzle (212) in an open-loop configuration. The engine system (200) also includes a bottom-cycle apparatus (204) and an exhaust heat exchanger (228) downstream of the turbine section (210) of the turbine engine (202) configured to reject heat from the turbine engine (202) to the bottoming-cycle apparatus (204) and create a cooled turbine exhaust (226) in the turbine engine (202). The engine system (200) further includes an exhaust compressor (214) arranged downstream of the exhaust heat exchanger (228) and upstream of the nozzle (212) of the turbine engine (202) configured to compress the cooled turbine exhaust stream (226) and increase a pressure of the cooled turbine exhaust stream (226) prior to exiting the nozzle (212) of the turbine engine (202).
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公开(公告)号：EP2912270B1
公开(公告)日：2023-04-26
申请号：EP13786120.9
申请日：2013-10-23
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公开(公告)号：EP4163480A2
公开(公告)日：2023-04-12
申请号：EP22191092.0
申请日：2022-08-18
发明人： DILLON, Thomas , MILLER, Todd
摘要： There are describes methods and systems for operating an engine coupled to a fuel system (120) having a fuel manifold (200) configured to supply fuel to a combustor (16) of the engine (100). The method comprises receiving a gaseous fuel flow request indicative of a change in demand for gaseous fuel to the engine; applying a fuel loss bias to the gaseous fuel flow request to obtain a biased fuel flow request, the fuel loss bias associated with a change in mass flow rate of the gaseous fuel from the fuel manifold (200) to the combustor (16) in response to the change in demand; and causing the gaseous fuel to flow into the combustor (16) in accordance with the biased fuel flow request.
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公开(公告)号：EP4074955A1
公开(公告)日：2022-10-19
申请号：EP22167488.0
申请日：2022-04-08
摘要： A three-stream gas turbine engine (100) with an embedded electric machine (200) and methods of operating the same are disclosed. In one aspect, a three-stream engine includes an electric machine operatively coupled with a shaft (138) of the engine. The three-stream engine also includes a core engine (118) and a primary fan (152) and a mid-fan (190) positioned upstream of the core engine. The primary fan, the mid-fan, and a low pressure turbine are operatively coupled with the shaft. The three-stream engine defines an electric machine length to low pressure turbine length ratio. The electric machine length to low pressure turbine length ratio is equal to or greater than 0.01 and less than or equal to 3.0.
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公开(公告)号：EP4043710A1
公开(公告)日：2022-08-17
申请号：EP22154537.9
申请日：2022-02-01
摘要： A turbomachinery engine includes an unducted rotor assembly, a low-pressure turbine, a low-pressure shaft, a gearbox, and an engine correlation parameter. The unducted rotor assembly includes a plurality of rotor blades arranged in a single row and defining a blade diameter. The gearbox includes an input, an output, and a gear ratio. The input of the gearbox is coupled to the low-pressure shaft (which is coupled to the LPT), and the output of the gearbox is coupled to the unducted rotor assembly. The engine correlation parameter is greater than 0.17 and less than 0.83. The engine correlation parameter equals D/N/GR, where D is the blade tip diameter measured in feet, N is the stage count of the low-pressure turbine, and GR is the gear ratio of the gearbox. The unducted propulsor assembly optionally includes a disk loading within a range of 60-180 HP/ft 2 at a takeoff flight condition.
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公开(公告)号：EP3985239A1
公开(公告)日：2022-04-20
申请号：EP21203243.7
申请日：2021-10-18
发明人： CORMIER, Charles , COUTU, Daniel
摘要： An aircraft comprises an engine (10) having a rotor (29), a compressor (102, 104) mechanically coupled to the rotor (29), and a variable geometry mechanism (310) provided upstream of the compressor (102, 104) and configured to modulate an amount of compression work performed by the compressor (102, 104). A method comprises operating the rotor (29) with the variable geometry mechanism (310) in a first position, receiving a request to increase reverse thrust for the rotor (29), in response to the request, adjusting the variable geometry mechanism (310) from the first position towards a second position, the variable geometry mechanism (310) having a greater opening angle in the second position than in the first position, and operating the rotor (29) with the variable geometry mechanism (310) in the second position for causing an increase in the amount of compression work performed by the compressor (102, 104) and an increase in reverse thrust for the rotor (29).
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