公开(公告)号：US20200318546A1

公开(公告)日：2020-10-08

申请号：US16839123

申请日：2020-04-03

Applicant: Safran Nacelles

Inventor： Vincent PEYRON ,  Nicolas BOUCHOUT

IPC: F02C7/16 ,  F28F9/00

Abstract: A surface heat-exchanger for a turbojet engine nacelle between a fluid (C) to be cooled down and air (F) includes a circulation duct of the fluid (C) to be cooled down disposed in contact with air. The circulation duct includes a plurality of channels extending substantially in the same direction with a distance (D) between two adjacent channels between two and five times the width (L) of the channels, each channel having a wall with an area intended to be in contact with air and an area opposite to the area intended to be in contact with air.

公开(公告)号：US20200317358A1

公开(公告)日：2020-10-08

申请号：US16839145

申请日：2020-04-03

Applicant: Safran Nacelles

Inventor： Vincent PEYRON ,  Nicolas BOUCHOUT

IPC: B64D33/10 ,  B64D29/02 ,  B64D33/02 ,  B64D27/18 ,  F02C7/16 ,  F28D9/00

Abstract: An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).

公开(公告)号：US20190153947A1

公开(公告)日：2019-05-23

申请号：US16253352

申请日：2019-01-22

Applicant: Safran Nacelles

Inventor： Vincent PEYRON ,  Patrick GONIDEC ,  Nicolas BOUCHOUT

IPC: F02C7/14 ,  F02C7/16 ,  F02K3/115 ,  B64D29/06 ,  B64D33/08

Abstract: A nacelle of a turbine engine has a substantially tubular structure and defines a secondary channel. The nacelle includes a shroud forming a trailing edge on a downstream end of the nacelle, the shroud being defined by at least one outer face subjected to an outside air flow and an inner face subjected to an inside air flow circulating in the secondary channel of the nacelle. The nacelle further includes a cooling device having at least one heat-exchange channel that extends into the shroud.