公开(公告)号：US20210245889A1

公开(公告)日：2021-08-12

申请号：US17175003

申请日：2021-02-12

Applicant: Airbus Operations S.L.

Inventor： Alberto MARTINEZ SANCHO

IPC: B64D31/14 ,  B64F5/40

Abstract: A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.

公开(公告)号：US20210284344A1

公开(公告)日：2021-09-16

申请号：US17188115

申请日：2021-03-01

Applicant: Airbus Operations S.L.

Inventor： Alberto MARTINEZ SANCHO

IPC: B64D13/08

Abstract: An operating method of a vehicle cabin air supply device comprising taking fresh air from outside the cabin, diverting the fresh air to an air exhaust during an exhaust duration period after starting the air supply device, before injecting the fresh air into the cabin, such that the fresh air injected in the cabin after the exhaust duration period minimizes unpleasant odors in the cabin. A vehicle cabin air supply device and an aircraft comprising such a device is also provided.

公开(公告)号：US20180142623A1

公开(公告)日：2018-05-24

申请号：US15817354

申请日：2017-11-20

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Marcos Javier CHIABRANDO ,  Miguel Angel CARRO SANCHEZ ,  Alberto MARTINEZ SANCHO ,  Samuel MARTINEZ VILLACORTA ,  Pio FERNANDEZ-LOPEZ

IPC: F02C7/27 ,  F02C7/12

CPC classification number: F02C7/27 ,  F02C7/12 ,  F02C7/277 ,  F05D2220/323 ,  F05D2220/50 ,  F05D2270/02 ,  F05D2270/301 ,  F05D2270/3013 ,  F05D2270/313

Abstract: A system for controlling aircraft main engines cooling during starting operations. An aircraft incorporates a main engine and a pneumatic starter for starting the same, and a pneumatic source fluidly communicated with the pneumatic starter to supply pressurized air thereto. A control system is provided with a data chart containing predetermined pressure values of the pneumatic source, and the values correspond to an ambient condition to obtain a desired rotating speed for the main engine for that ambient condition. The control system is configured to control the pneumatic source air pressure output based on the data chart and to rotate the main engine within a predefined rotating speed range during cooling procedure. A controlled reduced rotating speed during main engines cooling or cranking operation is thus provided before starting main engines, in order to mitigate bowed rotor phenomenon.