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

IPC分类号： F02C6/08 ,  F02C7/12 ,  F25B9/04 ,  H10N10/13

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.

公开(公告)号：EP4345267A1

公开(公告)日：2024-04-03

申请号：EP23193843.2

申请日：2023-08-29

申请人： Rolls-Royce plc

发明人： Li, Jia ,  Lee, Seok Woo ,  Gill, Vincent

IPC分类号： F02C6/08 ,  F02C7/12 ,  F25B9/04 ,  H10N10/13

摘要： There is disclosed a gas turbine engine (10) for an aircraft, the gas turbine engine comprising: a compressor stage; a bleed air line (50) diverted from the compressor stage; and a thermoelectric generator system (100, 200, 300). The thermoelectric generator system comprises a thermoelectric generator (102); a vortex tube (104) and a radiator system (106). The vortex tube comprises a flow input (112) fluidically connected to the bleed air line to receive an input of compressed gas from the bleed air line, wherein the vortex tube is configured 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. The radiator system comprises a first heat exchanger (120) and a second heat exchanger (118) disposed on opposing sides of the thermoelectric generator. At least one of the hot flow is directed to the first heat exchanger, and the cold flow is directed to the second heat exchanger.