Cooling device for a turbojet engine of an aircraft nacelle

Patent metadata

Field	Value
Publication number	US-2016017751-A1
Application number	US-201514865072-A
Country	US
Kind code	A1
Filing date	Sep 25, 2015
Priority date	Mar 26, 2013
Publication date	Jan 21, 2016
Grant date	—

Abstract

The present disclosure provides a cooling device for a turbo engine of an aircraft nacelle, including: a heat exchanger and an air outlet pipe. The nacelle includes a front housing that has a front lip forming a hollow leading edge that delimits an annular de-icing chamber. In particular, the cooling device further includes a pipe for supplying pressurized air that extends from an inlet end linked to a pressurized air source, to an outlet end forming an air ejection nozzle opening into the de-icing chamber, and the outlet pipe of the heat exchanger has an air outlet section that is arranged in the de-icing chamber in a position designed such that the pressurized air ejection nozzle forms an air suction pump in the outlet pipe of the exchanger.

First claim

What is claimed is:

1 . A cooling device for a turbojet engine of an aircraft nacelle, comprising:
a heat exchanger which has an inlet connected on an inlet duct which supplies the heat exchanger with an cooling air; and an outlet connected on an outlet duct which evacuates the air passing through the heat exchanger, the nacelle including a front fairing which comprises:
an aerodynamic outer wall;
an inner wall configured to guide an air towards the turbojet engine; and
a…

Assignees

• Aircelle Sa

Inventors

• Caruel Pierre

Classifications

• F01D25/02

  Mechanical Engineering · mapped topic

• F01D25/24

  Mechanical Engineering · mapped topic

• F05D2220/10

  Mechanical Engineering · mapped topic

• F05D2260/213

  Mechanical Engineering · mapped topic

• F01D25/12 Primary

  Mechanical Engineering · mapped topic