Safran Nacelles

Jean-Nicolas Bouchout

Vincent Peyron

Patrick Gonidec

Julien Corbin

Flavie Hubert-Choinard

Caroline Dang

Alexandra Dugardin

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.

System for cooling an aircraft turbojet engine

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.

Method for manufacturing a structural surface heat exchanger for a nacelle

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).

Aircraft nacelle comprising at least one heat exchanger

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.

Surface heat-exchanger for a cooling system of an aircraft turbojet engine

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.

Turbine engine nacelle comprising a cooling device

In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between &#x2212;70&#xb0; C. and +175&#xb0; C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).

Growing community of inventors

Moissy Cramayel, France

Jean-Nicolas Bouchout