公开(公告)号：US20180155055A1

公开(公告)日：2018-06-07

申请号：US15817826

申请日：2017-11-20

Applicant: Airbus Operations, S.L.

Inventor： Tamara Blanco Varela ,  José Sanchez Gomez ,  Leire Segura Martinez De Ilarduya ,  Mariano Morales Monge

IPC: B64D45/02 ,  B29C70/88 ,  B32B15/02 ,  H01M2/02 ,  B32B7/06 ,  B32B15/08 ,  B32B15/14

CPC classification number: B64D45/02 ,  B29C70/885 ,  B32B3/26 ,  B32B5/00 ,  B32B5/02 ,  B32B7/00 ,  B32B7/02 ,  B32B7/04 ,  B32B7/06 ,  B32B7/10 ,  B32B9/00 ,  B32B9/04 ,  B32B15/00 ,  B32B15/02 ,  B32B15/04 ,  B32B15/08 ,  B32B15/14 ,  B32B15/20 ,  B32B27/00 ,  B32B27/06 ,  B32B27/28 ,  B32B2250/00 ,  B32B2262/00 ,  B32B2262/106 ,  B32B2307/10 ,  B32B2307/102 ,  B32B2307/20 ,  B32B2307/202 ,  B32B2307/30 ,  B32B2307/3065 ,  B32B2307/50 ,  B32B2307/558 ,  B32B2307/56 ,  B32B2307/732 ,  B32B2457/00 ,  B32B2457/10 ,  B32B2571/00 ,  B32B2605/00 ,  B32B2605/18 ,  H01M2/0267 ,  H01M2/0295

Abstract: A structural composite component, in particular for an aircraft or spacecraft, includes: a lightning strike protection layer; and a composite battery including a cathode layer and a separation layer, wherein the lightning strike protection layer is formed integrated with the cathode layer, and wherein the separation layer is configured for providing acoustic damping, and/or fire barrier, and/or impact resistance to the structural composite component. A method for configuring such a structural composite component; and an aircraft or spacecraft including such a structural composite component are also described.

公开(公告)号：US10975769B2

公开(公告)日：2021-04-13

申请号：US15842352

申请日：2017-12-14

Applicant: Airbus Operations, S.L.

Inventor： Leire Segura Martinez De Ilarduya ,  Alberto Juarez Becerril ,  Salvatore Demelas

IPC: F02C7/268 ,  F02C7/06 ,  F01D25/20 ,  F01D25/10 ,  F02C7/14 ,  F28D7/00 ,  B64D41/00 ,  F02C7/22

Abstract: An oil heating system in a turbine engine such as an aircraft turbojet or turboprop main engines, or in an aircraft auxiliary power unit (APU). The turbine oil heating system includes a turbine engine oil circuit for conducting lubricating oil to the turbine engine, an electric starter generator oil circuit for conducting cooling oil from the electric starter generator, and an oil-to-oil heat exchanger connected with the engine oil circuit and connectable with the electric starter generator oil circuit, for transferring heat from the starter generator oil to the engine oil as to warm-up the engine oil during turbine engine motoring prior to actual starting sequence. A low cost and highly integrated system is therefore provided for reducing drag torque of a turbine engine prior to the starting phase.

公开(公告)号：US10773824B2

公开(公告)日：2020-09-15

申请号：US15817826

申请日：2017-11-20

Applicant: Airbus Operations, S.L.

Inventor： Tamara Blanco Varela ,  José Sanchez Gomez ,  Leire Segura Martinez De Ilarduya ,  Mariano Morales Monge

IPC: B64D45/02 ,  B29C70/88 ,  B32B15/02 ,  H01M2/02 ,  B32B7/06 ,  B32B15/08 ,  B32B15/14 ,  B32B15/00 ,  B32B27/00 ,  B32B9/04 ,  B32B7/02 ,  B32B5/00 ,  B32B9/00 ,  B32B3/26 ,  B32B27/06 ,  B32B7/04 ,  B32B27/28 ,  B32B7/10 ,  B32B15/04 ,  B32B5/02 ,  B32B7/00 ,  B32B15/20

Abstract: A structural composite component, in particular for an aircraft or spacecraft, includes: a lightning strike protection layer; and a composite battery including a cathode layer and a separation layer, wherein the lightning strike protection layer is formed integrated with the cathode layer, and wherein the separation layer is configured for providing acoustic damping, and/or fire barrier, and/or impact resistance to the structural composite component. A method for configuring such a structural composite component; and an aircraft or spacecraft including such a structural composite component are also described.

公开(公告)号：US20180187601A1

公开(公告)日：2018-07-05

申请号：US15842352

申请日：2017-12-14

Applicant: Airbus Operations, S.L.

Inventor： Leire Segura Martinez De Ilarduya ,  Alberto Juarez Becerril ,  Salvatore Demelas

IPC: F02C7/06 ,  F02C7/268 ,  F28D7/00

CPC classification number: F02C7/06 ,  B64D41/00 ,  F01D25/10 ,  F01D25/20 ,  F02C7/14 ,  F02C7/22 ,  F02C7/268 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/213 ,  F05D2260/85 ,  F05D2260/98 ,  F05D2270/303 ,  F28D7/0008 ,  Y02T50/671 ,  Y02T50/675

Abstract: An oil heating system in a turbine engine such as an aircraft turbojet or turboprop main engines, or in an aircraft auxiliary power unit (APU). The turbine oil heating system includes a turbine engine oil circuit for conducting lubricating oil to the turbine engine, an electric starter generator oil circuit for conducting cooling oil from the electric starter generator, and an oil-to-oil heat exchanger connected with the engine oil circuit and connectable with the electric starter generator oil circuit, for transferring heat from the starter generator oil to the engine oil as to warm-up the engine oil during turbine engine motoring prior to actual starting sequence. A low cost and highly integrated system is therefore provided for reducing drag torque of a turbine engine prior to the starting phase.