公开(公告)号：US20220023931A1

公开(公告)日：2022-01-27

申请号：US17492790

申请日：2021-10-04

Applicant: Safran Nacelles

Inventor： Vincent PEYRON ,  Jean-Nicolas BOUCHOUT ,  Flavie HUBERT-CHOINARD ,  Alexandra DUGARDIN

IPC: B21D53/04

Abstract: A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.

公开(公告)号：US20220186665A1

公开(公告)日：2022-06-16

申请号：US17490766

申请日：2021-09-30

Applicant: Safran Nacelles

Inventor： Julien CORBIN ,  Jean-Nicolas BOUCHOUT ,  Caroline DANG

IPC: F02C7/14 ,  F02K1/56

Abstract: An engine nacelle, for a turbojet engine of the type having a lubricant, includes a cooling system. The cooling system includes a cold source heat-exchanger, configured to exchange heat between a heat-transfer fluid and air, a heat-transfer fluid inlet duct leading into the cold source heat-exchanger, and a heat-transfer fluid outlet duct leading out of the cold source heat-exchanger. The inlet and outlet ducts are configured to form a recirculation loop between the cold source heat-exchanger and a hot source heat-exchanger, configured to exchange heat between the heat-transfer fluid and the lubricant. The cold source heat-exchanger is arranged on a movable surface of the nacelle with respect to the hot source heat-exchanger and the heat-transfer fluid inlet and outlet ducts are extendable and/or flexible to permit the relative movement between the cold source heat-exchanger and the hot source heat-exchanger.

公开(公告)号：US20220025816A1

公开(公告)日：2022-01-27

申请号：US17492783

申请日：2021-10-04

Applicant: Safran Nacelles

Inventor： Julien CORBIN ,  David PEREIRA ,  Vincent PEYRON ,  Jean-Nicolas BOUCHOUT ,  Caroline DANG ,  Nicolas CHOUQUET

IPC: F02C7/18 ,  F02C9/00

Abstract: A cooling system for cooling an aircraft turbojet engine includes a first heat-exchanger for exchanging heat between a heat-transfer fluid and a lubricant of the turbojet engine, a second heat-exchanger for exchanging heat between the heat-transfer fluid and air, and a circulation duct for circulating heat-transfer fluid in a closed circuit. The cooling system further includes at least one regulating device for regulating the heat drawn from the lubricant, controlled by a control module of the regulating device that is configured to receive information according to the various flight phases.