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公开(公告)号：EP4452589A1
公开(公告)日：2024-10-30
申请号：EP22839875.6
申请日：2022-12-13
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公开(公告)号：EP4435264A1
公开(公告)日：2024-09-25
申请号：EP24157559.6
申请日：2024-02-14
申请人： Rolls-Royce plc
发明人： Murray, Christopher
摘要： There is provided an air pressurisation system 400, 401, 402. The air pressurisation system comprises: a blower compressor 420, 500 configured to be mechanically coupled to a spool 440 of a gas turbine engine 10 and configured to receive an inlet flow of air from a bypass duct 22 of the gas turbine engine 10. The blower compressor 420, 500 comprises: a compressor wheel 506 having a rotor 502 configured to be mechanically coupled to the spool 440 of the gas turbine engine 10; and a housing 504, wherein the rotor 502 is supported for rotation within the housing 504 about a rotor axis 502b, wherein the rotor 502 and housing 504 define a primary air channel 503 extending between an inlet 506a of the blower compressor 420, 500 for receiving the inlet flow of air and an outlet 506b from which the blower compressor 420, 500 is configured to output pressurised air to a delivery line 310. The housing further 504 comprises a bleed opening 520 in a wall 504c of the housing 504 between the inlet 506a and the outlet 506b, the bleed opening 520 extending circumferentially about the rotor axis 502b, wherein the bleed opening 520 is for contaminants within the inlet flow of air, which have been driven outward due to the rotation of the rotor 502, to be bled out of the blower compressor 420, 500. The air pressurisation system 400, 401, 402 further comprises the delivery line 310 configured to convey air compressed by the blower compressor 420, 500 to an airframe system 450 of the aircraft 1000.
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公开(公告)号：EP3748147B1
公开(公告)日：2024-06-12
申请号：EP20178047.5
申请日：2020-06-03
IPC分类号： F02C6/08
CPC分类号： F02C6/08 , F01D17/141 , F05D2260/9620130101 , F05D2260/5020130101 , F05D2300/50120130101
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公开(公告)号：EP3862539B1
公开(公告)日：2024-05-08
申请号：EP21155059.5
申请日：2021-02-03
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公开(公告)号：EP4317660A3
公开(公告)日：2024-04-17
申请号：EP23212606.0
申请日：2020-10-12
CPC分类号： F02C6/08 , F02C9/18 , F02C6/02 , F05D2270/30320130101 , F05D2260/8320130101 , F05D2260/8020130101 , F05D2220/32920130101
摘要： A method (80) of monitoring bleed air provided from a first engine (10) to a second engine (10) of a multi-engine aircraft (1) includes operating the first engine (10) in a powered mode to provide motive power to the multi-engine aircraft (1); and when the first engine (10) is in the powered mode: actuating an air valve (14') to open an air flow path (A) from a compressor section (9) of the first engine (10) to a plurality of parts of the second engine (10), after the step of actuating the air valve (14'), determining a change in a temperature in a main gas path (AF) of the first engine (10) at a location in the main gas path (AF) at or downstream of a combustor (8) of the first engine (10), and in response to determining that the change is below a threshold, executing an action with respect to the first engine (10), the air valve (14'), and/or the second engine (10).
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公开(公告)号：EP4345268A1
公开(公告)日：2024-04-03
申请号：EP23193844.0
申请日：2023-08-29
申请人： Rolls-Royce plc
发明人： Li, Jia , Lee, Seok Woo , Gill, Vincent
摘要： A thermoelectric generator system (300) comprising: a thermoelectric generator (102); a vortex tube (104) comprising a flow input (112) configured to receive an input of compressed gas and to separate the compressed gas into a hot flow discharged from a first output (114) of the vortex tube, and a cold flow discharged from a second output (116) of the vortex tube; a sensor system (308) configured to determine a first parameter indicative of a temperature of the hot flow, a second parameter indicative of a temperature of the cold flow and a third parameter indicative of a temperature of a third fluid flow; and a radiator system (306) comprising a first heat exchanger (120) and a second heat exchanger (118) disposed on opposing sides of the thermoelectric generator; and a tube system configured to separately direct the hot flow, the cold flow and the third fluid flow towards a switch arrangement (312). the switch arrangement is configured to receive each of the hot flow, the cold flow and the third fluid flow, and to be moveable between: a first configuration in which the cold flow is directed to the second heat exchanger and the hot flow is directed to the first heat exchanger; a second configuration in which the cold flow is directed to the second heat exchanger and the third fluid flow is directed to the first heat exchanger; and a third configuration in which the third fluid flow is directed to the second heat exchanger and the hot fluid is directed to the first heat exchanger. The thermoelectric generator system further comprises a control unit (314) configured to control the configuration of the switch arrangement based on the first parameter, the second parameter, and the third parameter.
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公开(公告)号：EP4343132A1
公开(公告)日：2024-03-27
申请号：EP23199536.6
申请日：2023-09-25
申请人： RTX Corporation
IPC分类号： F02C6/08
摘要： A turbine engine assembly (20) includes a tap (92) is at a location upstream of the combustor section (26) where a bleed airflow (64) is drawn. The bleed air is pressurized in an auxiliary compressor section (72), heated in an exhaust heat exchanger (82) and expanded through a power turbine (74) that is coupled to drive the auxiliary compressor section (72).
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