公开(公告)号：US20190263528A1

公开(公告)日：2019-08-29

申请号：US16336956

申请日：2016-09-29

Applicant: Airbus Operations S.L.

Inventor： Carlos CASADO-MONTERO ,  Victor BARREIRO RODRIGUEZ ,  Alexandra CARRASCO CARRASCAL

IPC: B64D13/08 ,  B64D13/06 ,  B64D27/10 ,  B64D41/00

Abstract: A secondary power unit for an aircraft comprises a gas turbine engine having at least one drive shaft, a twin-load compressor including first and second load compressors both coupled with the drive shaft, a first ram-air intake in fluid communication with the twin-load compressor, and a flow regulating arrangement coupled with the first and second compressors outputs to individually regulate the generated flow of compressed air. The flow regulating arrangement is also adapted to be fluidly communicated with an Air Cycle Machine of an aircraft, and a control system is adapted to feed the flow of compressed air as bleed air to the Air Cycle Machine of an aircraft, both when the aircraft is on ground and in flight. The secondary power unit is capable of avoiding bleed air extraction from the main engines with the aim of reducing fuel consumption.

公开(公告)号：US20180346132A1

公开(公告)日：2018-12-06

申请号：US15997005

申请日：2018-06-04

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Carlos CASADO-MONTERO ,  Alberto MOLINA PARGA

IPC: B64D13/08 ,  B64D33/02 ,  B64D41/00

CPC classification number: B64D41/00 ,  B64D13/06 ,  B64D2013/0611 ,  B64D2013/0648 ,  B64D2013/0696

Abstract: The invention relates to an aircraft incorporating an enhanced power unit for generating electric, pneumatic and/or hydraulic power for the aircraft during all stages of the aircraft operation. The power unit (1) comprises: a heat engine (14) with a drive shaft (2) and a combustion gases exhaust (7). The power unit (1) also includes a Rankine cycle system (12) for recovering thermal energy from a heat source of the power unit (1) for the assistance of the heat engine (14). The heat source for the Rankine cycle system can be taken from the exhaust gases of the heat engine, from the oil coolant circuit of the heat engine or from the output of a compressor driven by the heat engine. Preferably, the aircraft cabin air is reused as a source of oxygen for the combustion. The invention reduces bleed air extraction from the aircraft main engines thereby reducing fuel consumption.

公开(公告)号：US20190390601A1

公开(公告)日：2019-12-26

申请号：US16440301

申请日：2019-06-13

Applicant: Airbus Operations S.L.

Inventor： Carlos CASADO-MONTERO ,  Pio FERNANDEZ-LOPEZ

IPC: F02C7/057 ,  B64D13/02 ,  B64D33/02

Abstract: An air intake system comprising an air duct suitable for providing airflow to the inside of an aircraft, preferably to an auxiliary power unit; an inlet arranged at one end of the air duct; a skin surrounding the inlet; a plurality of slots arranged on the skin; a driving arrangement, a flap door connected to the driving arrangement, and a plurality of fins connected to the driving means. The driving arrangement is configured for moving the flap door between at least two positions, the positions being a closed position wherein the flap door closes the inlet, and an opened position wherein the flap door is driven away from the closed position. The driving arrangement is also configured for moving the plurality of fins such that the plurality of fins protrudes through the slots.

公开(公告)号：US20220161940A1

公开(公告)日：2022-05-26

申请号：US17526120

申请日：2021-11-15

Applicant: Airbus Operations S.L.

Inventor： Pedro Manuel MARTIN CANDELARIO ,  Lucas GRANJA PAREJO ,  Carlos CASADO-MONTERO

IPC: F02K1/34 ,  B64D41/00 ,  G10K11/162

Abstract: An exhaust muffler for an APU of an aircraft, including an exhaust gases inlet, an exhaust gases outlet, a peripheral wall configured to guide a flow of exhaust gases between the inlet and the outlet. The peripheral wall includes at least one vacuum chamber to provide thermal insulation.

公开(公告)号：US20190161209A1

公开(公告)日：2019-05-30

申请号：US16201613

申请日：2018-11-27

Applicant: Airbus Operations, S.L.

Inventor： Carlos CASADO-MONTERO ,  Javier LINDE AYLLON

IPC: B64F1/10 ,  B64F1/22 ,  B64C25/08

Abstract: An aircraft system with assisted taxi, take-off and climbing, comprising: a main air vehicle capable of performing autonomously the cruising and landing phases of a flight, an auxiliary air vehicle lighter than the main air vehicle and configured to assist the main air vehicle during the taxing and take-off phases of a flight. Main and auxiliary air vehicles are adapted to be detachably connectable, so that the auxiliary air vehicle can assist the main air vehicle when both are attached to each other during taxing, take-off and climbing. The auxiliary air vehicle is an unmanned air vehicle and it is further configured to fly and land when it is detached from the main air vehicle. Aircraft operations cost and aircraft production cost are reduced, by optimizing the design (sizing) and capabilities of some systems of an aircraft.