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.

公开(公告)号：US11428582B2

公开(公告)日：2022-08-30

申请号：US16391825

申请日：2019-04-23

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

Inventor： Romain Merat ,  Marta Castillo De Alvear ,  Sijmen Zandstra ,  Javier Fraile Martin ,  Carlos Bueno Vazquez ,  Jose Perez Garcia

IPC: H02H5/00 ,  G01K3/00 ,  G01K1/024 ,  A62C37/48 ,  B64D45/00

Abstract: An overheat detection system comprising a controller for declaring the overheat, and two wiring connections running along a monitored system and configured to react upon overheat. The controller is configured to determine an electrical status of each wiring connection at least between operative and inoperative, the inoperative status corresponding to an electrical anomaly thereof, and electrically connect or disconnect the wiring connections depending on the electrical status thereof, wherein the declaration of overheat is based on a dynamic reconfiguration of the overheat detection system.

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.