公开(公告)号：US11136921B2

公开(公告)日：2021-10-05

申请号：US16814494

申请日：2020-03-10

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations, S.L.

Inventor： Bruno Medda ,  Esteban Martino-Gonzalez ,  Thomas Stevens ,  Julien Cayssials ,  Juan Tomas Prieto Padilla ,  Adeline Soulie ,  Didier Poirier ,  Pierre-Alain Pinault ,  Diego Barron Vega

IPC: F02C9/00 ,  F02C9/18 ,  F02C7/10

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.

公开(公告)号：US11597523B2

公开(公告)日：2023-03-07

申请号：US16916559

申请日：2020-06-30

Applicant: Airbus Operations S.L.

Inventor： Esteban Martino-Gonzalez ,  Juan Tomas Prieto Padilla

IPC: B64D13/02 ,  B64D13/04 ,  B64D13/06 ,  B64D27/12 ,  B64D41/00

Abstract: An air management system with a set of compressed air sources for supplying pressurized air to air consumer equipment. In particular, either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.

公开(公告)号：US20180371991A1

公开(公告)日：2018-12-27

申请号：US16018593

申请日：2018-06-26

Applicant: Airbus Operations, S.L.

Inventor： Marta Castillo De Alvear ,  Juan Tomas Prieto Padilla

IPC: F02C6/08 ,  F02C7/14 ,  B64D13/02 ,  B64D13/08 ,  B64D15/04

Abstract: An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced.

公开(公告)号：US11623752B2

公开(公告)日：2023-04-11

申请号：US16916549

申请日：2020-06-30

Applicant: Airbus Operations S.L.

Inventor： Angel Garcia Zuazo ,  Serafin Escudero Fraile ,  Esteban Martino-Gonzalez ,  Juan Tomas Prieto Padilla ,  Diego Barron Vega

IPC: B64D13/06 ,  B64D13/02 ,  B64D13/08 ,  F02C6/04 ,  F02C6/08 ,  F02C7/18 ,  B64D27/12 ,  B64D41/00

Abstract: An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed.

公开(公告)号：US11408338B2

公开(公告)日：2022-08-09

申请号：US16814506

申请日：2020-03-10

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations, S.L.

Inventor： Bruno Medda ,  Esteban Martino-Gonzalez ,  Thomas Stevens ,  Julien Cayssials ,  Juan Tomas Prieto Padilla ,  Adeline Soulie ,  Didier Poirier ,  Pierre-Alain Pinault ,  Diego Barron Vega

IPC: F02C6/08 ,  B64D15/04 ,  F02C7/047 ,  F02C7/10 ,  B64D33/02

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

公开(公告)号：US11215118B2

公开(公告)日：2022-01-04

申请号：US16712232

申请日：2019-12-12

Applicant: Airbus (S.A.S.) ,  Airbus Operations (S.A.S.) ,  Airbus Operations, S.L.

Inventor： Bruno Medda ,  Thomas Stevens ,  Julien Cayssials ,  Adeline Soulie ,  Didier Poirier ,  Pierre-Alain Pinault ,  Esteban Martino González ,  Juan Tomas Prieto Padilla ,  Diego Barron Vega

IPC: F02C7/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/04 ,  F02C7/047 ,  F02C6/08 ,  F02C7/14 ,  B64D13/06

Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

公开(公告)号：US10961907B2

公开(公告)日：2021-03-30

申请号：US16018593

申请日：2018-06-26

Applicant: Airbus Operations, S.L.

Inventor： Marta Castillo De Alvear ,  Juan Tomas Prieto Padilla

IPC: B64D13/08 ,  F02C6/08 ,  F02C7/14 ,  B64D13/02 ,  B64D15/04 ,  F02K3/06 ,  F02K3/115 ,  B64D29/02 ,  F02C7/18 ,  F02C9/18 ,  B64D13/06 ,  F28D21/00 ,  B64D33/02

Abstract: An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced.