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公开(公告)号：EP3708494A1
公开(公告)日：2020-09-16
申请号：EP19162028.5
申请日：2019-03-11
发明人： MEDDA, Bruno , MARTINO-GONZALEZ, Esteban , STEVENS, Thomas , CAYSSIALS, Julien , PRIETO PADILLA, Juan Tomas , SOULIE, Adeline , POIRIER, Didier , PINAULT, Pierre-Alain , BARRON VEGA, Diego
摘要： The invention relates to an aircraft propulsion system, which includes a turbojet and a heat exchanger system (200) which includes a main heat exchanger (202), a supply pipe (204) supplying hot air, a transfer pipe (222) transferring the hot air to an air management system, a main supply pipe (216) supplying cold air from the fan duct, an evacuation pipe (220) expelling the air to the outside, a sub heat exchanger (230) with a high pressure pipe (250) going through the sub heat exchanger (230), a sub supply pipe (232) supplying cold air and including a sub regulating valve (234), a sub evacuation pipe (236) expelling the air, a temperature sensor (223), and a control unit (224) which controls the system according to the temperature measured, wherein the sub regulating valve (234) comprises a door (240) articulated between a closed position and an open position, a return spring (242) which constraints the door (240) in the open position, and a realising system (244), controlled by the control unit (224), which is mobile between a blocking position and a realising position in which it releases the door (240) which is free to move to the open position.
This embodiment allows a supplementary cold air flow if necessary.-
公开(公告)号：EP3741678A1
公开(公告)日：2020-11-25
申请号：EP19175694.9
申请日：2019-05-21
发明人： MEDDA, Bruno , MARTINO-GONZALEZ, Esteban , STEVENS, Thomas , CAYSSIALS, Julien , PRIETO PADILLA, Juan Tomas , SOULIE, Adeline , POIRIER, Didier , PINAULT, Pierre-Alain , BARRON VEGA, Diego
摘要： The invention relates to a regulating valve (318) for a heat exchanger system of a propulsion system comprising a turbojet with a fan duct, and the heat exchanger system comprising a supply pipe which bleeds cold air from the fan duct, and wherein the regulating valve (318) has a front side (404) and a back side (406) and includes an open frame (402) which delimits a window (401) and is set in position in front of the supply pipe, two flaps (410a-b) rotatably mounted on the open frame (402) around a same rotation axis (412) located at the front side (404) between a closed position and an open position, a mechanism (420) linked to the flaps (410a-b) and mobile between a first position and a second position, and wherein the mechanism (420) moves the flaps (410a-b) from the closed position to the open position when it moves from the first position to the second position, and an actuator acting on the mechanism (420) to move it from the first position to the second position and vice versa.
The specific embodiment of the cold regulating valve reduces the necessary space to implement it.-
公开(公告)号：EP3708495A1
公开(公告)日：2020-09-16
申请号：EP19162032.7
申请日：2019-03-11
发明人： MEDDA, Bruno , MARTINO-GONZALEZ, Esteban , STEVENS, Thomas , CAYSSIALS, Julien , PRIETO PADILLA, Juan Tomas , SOULIE, Adeline , POIRIER, Didier , PINAULT, Pierre-Alain , BARRON VEGA, Diego
摘要： The invention relates to an aircraft propulsion system, which includes a turbojet and a heat exchanger system (200) which includes a main heat exchanger (202), a supply pipe (204) supplying hot air and including a regulating valve (214), a high pressure pipe (250) bleeding hot air from a high pressure stage (206) through a first valve (210), an intermediate pressure pipe (252) bleeding hot air from an intermediate pressure stage (208) through a second valve (212), a transfer pipe (222) transferring the hot air to an air management system, a main supply pipe (216) supplying cold air from the fan duct and including a main regulating valve (218), an evacuation pipe (220) expelling the air to the outside, a sub heat exchanger (230), wherein the supply pipe (204) issued from the regulating valve (214) goes through the sub heat exchanger (230), a sub supply pipe (232) supplying cold air from the main supply pipe (216), a sub evacuation pipe (236) expelling the air to the fan duct, a temperature sensor (223) measuring the temperature of the hot air exiting the main heat exchanger (202), and a control unit (224) which controls the valves according to the temperature measured by the temperature sensor (223).
The embodiment including two separate heat exchangers induces a size reduction of the main heat exchanger and a better integration in the reduced space between the pylon and the pylon fairing.-
公开(公告)号：EP3708493A1
公开(公告)日：2020-09-16
申请号：EP19162017.8
申请日：2019-03-11
发明人： MEDDA, Bruno , MARTINO-GONZALEZ, Esteban , STEVENS, Thomas , CAYSSIALS, Julien , PRIETO PADILLA, Juan Tomas , SOULIE, Adeline , POIRIER, Didier , PINAULT, Pierre-Alain , BARRON VEGA, Diego
摘要： The invention relates to an aircraft propulsion system, which includes a turbojet and a heat exchanger system (200) which includes a main heat exchanger (202), a supply pipe (204) supplying hot air and including a regulating valve (214), a high pressure pipe (250) bleeding hot air from a high pressure stage (206) through a first valve (210), an intermediate pressure pipe (252) bleeding hot air from an intermediate pressure stage (208) through a second valve (212), a transfer pipe (222) transferring the hot air to an air management system, a main supply pipe (216) supplying cold air from the fan duct and including a main regulating valve (218), an evacuation pipe (220) expelling the air to the outside, a sub heat exchanger (230), wherein the high pressure pipe (250) goes through the sub heat exchanger (230), a sub supply pipe (232) supplying cold air from the fan duct and including a sub regulating valve (234), a sub evacuation pipe (236) expelling the air to the fan duct, a temperature sensor (223) measuring the temperature of the hot air exiting the main heat exchanger (202), and a control unit (224) which controls the valves according to the temperature measured by the temperature sensor (223).
The embodiment including two separate heat exchangers induces a size reduction of the main heat exchanger and a better integration in the reduced space between the pylon and the pylon fairing.
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