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公开(公告)号：US20170298822A1
公开(公告)日：2017-10-19
申请号：US15378238
申请日：2016-12-14
Applicant: Airbus Operations, S.L.
Inventor： Alexandre Garde La Casa
IPC: F02C7/08 , B64D41/00 , F01D5/02 , F01D9/04 , F02C9/18 , F02C3/04 , B64D27/10 , F01D15/12 , F01D17/10 , F01D15/10
CPC classification number: F02C7/08 , B64D27/10 , B64D41/00 , B64D2041/002 , F01D1/12 , F01D5/02 , F01D9/041 , F01D15/10 , F01D15/12 , F01D17/105 , F02C3/04 , F02C3/145 , F02C7/10 , F02C9/18 , F05D2220/323 , F05D2220/50 , F05D2240/35 , F05D2240/60 , Y02T50/671
Abstract: A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.
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公开(公告)号：US09782958B2
公开(公告)日：2017-10-10
申请号：US14388555
申请日：2013-03-22
Applicant: AIRBUS OPERATIONS, S.L.
Inventor： David Cano Cediel , Ruth Chinarro Vera , Francisco Escobar Benavides , Pedro Nogueroles Viñes
IPC: B29C70/28 , B29C51/08 , B32B37/00 , B29C70/38 , B29D99/00 , B32B37/16 , B32B38/00 , B29L31/00 , B29C33/30
CPC classification number: B32B37/0046 , B29C33/308 , B29C70/386 , B29D99/0003 , B29L2031/001 , B32B37/16 , B32B38/0012 , B32B2305/076 , B32B2305/72 , B32B2309/06 , B32B2605/18 , Y10T156/1044
Abstract: The manufacturing method object of the invention comprises the following stages: A) stacking strips of prepreg material on a laminating tool (14), so that an angled laminated part (2) is obtained comprising a central section (2a) contained in a first plane (12), at least one side section (2b) contained in a second plane (13), and at least one bending axis (5) between the central section (2a) and the at least one side section (2b), so that, the first plane and the second plane form an angle α; B) forming of the angled laminated part (2) comprising bending along the bending axis (5) the, at least, one side section with respect to the central section (2a), obtaining a formed part (6); C) curing, of the formed part (6).
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公开(公告)号：US09771140B2
公开(公告)日：2017-09-26
申请号：US14140511
申请日：2013-12-25
Applicant: Airbus Operations S.L.
Inventor： Elena Arevalo Rodriguez , Estelle Baligand
CPC classification number: B64C1/061 , B32B2605/18 , B64C1/064 , B64C1/12 , B64C1/1461 , B64C3/18 , B64C3/182 , B64C2001/0072 , Y02T50/43 , Y10T428/24008
Abstract: The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.
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公开(公告)号：US20170190430A1
公开(公告)日：2017-07-06
申请号：US15395425
申请日：2016-12-30
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Carlos CASADO MONTERO
IPC: B64D13/08
CPC classification number: B64D13/08 , B64D13/06 , B64D2013/0603 , B64D2013/0618 , B64D2013/0644 , B64D2013/0648 , B64D2013/0688 , Y02T50/56
Abstract: An air conditioning system 1 for a cabin 10 including a pressurized air source 2, a cooling air source 3, a main heat exchanger 4, a compressor 5, a manifold 6 and a mixing chamber 7. An inlet 43 to a cold side of the main heat exchanger 4 is in fluid communication with the cooling air source 3. An inlet 41 of a hot side of the main heat exchanger 4 is in fluid communication with the pressurized air source 2. An inlet 51 of the compressor is in fluid communication with the outlet 44 of the cold side of the main heat exchanger 4.
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公开(公告)号：US20170190429A1
公开(公告)日：2017-07-06
申请号：US15395365
申请日：2016-12-30
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Carlos CASADO MONTERO
IPC: B64D13/08
CPC classification number: B64D13/08 , B64D13/06 , B64D2013/0611 , B64D2013/0618 , B64D2013/0688 , Y02T50/56
Abstract: An air conditioning system 1 for a cabin 6 of an aircraft. The air conditioning system 1 includes a work air source 2 suitable for providing work air, a distribution and control system 3, a main heat exchanger 4, a turbine 5 and a compressor 7. The inlet 51 of the turbine 5 is in fluid communication with an outlet 61 of the cabin 6 and the outlet 52 of the turbine 5 is in fluid communication with ambient. The inlet 71 of the compressor is suitable for being fed by the work air, and the outlet 72 of the compressor is in fluid communication with the inlet 41 hot side of the main heat exchanger 4, the compressor 7 being moved by the outlet shaft 53 of the turbine 5. The outlet 42 of the hot side of the main heat exchanger 4 is in fluid communication with the inlet 31 of the distribution and control system 3, the outlet 32 of which is in turn in fluid communication with an inlet of the cabin 6.
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Patent Agency Ranking
公开(公告)号：US20170190428A1
公开(公告)日：2017-07-06
申请号：US15395293
申请日：2016-12-30
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Carlos CASADO MONTERO
IPC: B64D13/08
CPC classification number: B64D13/08 , B64D13/06 , B64D2013/0611 , B64D2013/0618 , B64D2013/0688 , Y02T50/56
Abstract: Air conditioning system for a cabin 6 of an aircraft, the air conditioning system 1 including a pressurized air source 2, a ram air duct 3, an air amplifier 4 and a heat exchanger 5. The air amplifier 4 includes an inlet 41 for work air, a slot 42 suitable for letting the work air exit the air amplifier, and a main fluid zone 43. The inlet 41 is in fluid communication with the pressurized air source 2 and the slot 42 is arranged in fluid communication with the ram air duct 3, in such a way that the work air exiting from the slot 42 produces a suction effect in the ambient air in such a way that this ambient air flows along the ram air duct 3. The air amplifier 4 is arranged so that the ambient air is forced by the suction effect to pass from the inlet 51 to the outlet 52 of the cold side of the heat exchanger 5.
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公开(公告)号：US20170174308A1
公开(公告)日：2017-06-22
申请号：US15381747
申请日：2016-12-16
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Carlos GARCÍA NIETO , Francisco José CRUZ DOMÍNGUEZ , Juan Pablo JUSTE MENCÍA , Nuria COLMENAREJO MATELLANO , Alejandro MARTÍNEZ CAÑIZARES
Abstract: A pressure bulkhead for an aircraft comprising a pressurized zone, the pressure bulkhead made of a composite material and comprising a front panel intended to be faced towards the pressurized zone; and a rear panel, substantially parallel to the front panel and intended to be located farther from the pressurized zone than the front panel. The pressure bulkhead further comprises a plurality of longerons located between the front panel and the rear panel, each one of them being attached to the front panel and to the rear panel; and a plurality of stiffeners, some of them being attached to the front panel and a remainder of them being attached to the rear panel.
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公开(公告)号：US20170158304A1
公开(公告)日：2017-06-08
申请号：US15366126
申请日：2016-12-01
Applicant: AIRBUS OPERATIONS S.L.
CPC classification number: B64C1/10 , B64C1/34 , B64C2001/0072
Abstract: A pressure bulkhead for an aircraft comprising a fuselage. The pressure bulkhead comprises an inflatable element, suitable for being filled with air, which in turn comprises a cover which delimits an inner zone. The pressure bulkhead further comprises a seal suitable for providing an airtight seal between the cover and the fuselage of the aircraft.
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公开(公告)号：US09656736B2
公开(公告)日：2017-05-23
申请号：US14695731
申请日：2015-04-24
Applicant: Airbus Operations (S.A.S.) , Airbus Operations, S.L.
Inventor： Julien Guillemaut , Esteban Martino Gonzalez , Diego Folch Cortes , Jerome Colmagro , Jonathan Blanc
Abstract: In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.
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公开(公告)号：US09637216B2
公开(公告)日：2017-05-02
申请号：US14585877
申请日：2014-12-30
Applicant: Airbus Operations S.L.
Inventor： Elena Arevalo Rodriguez
CPC classification number: B64C1/12 , B32B37/02 , B32B37/16 , B32B38/00 , B32B2038/0076 , B32B2305/34 , B32B2305/74 , B32B2605/18 , B64C1/061 , B64C1/064 , B64C2001/0072 , Y02T50/43
Abstract: An aircraft structure made of composite material, comprising a skin reinforced longitudinally with stringers, and frames perpendicular to the stringers, each stringer comprising a head and two webs, and each frame having recesses in its web for the passage of the longitudinal stringers, such that an internal preform is provided in the gap existing between each stringer and the skin, filling the gap.
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