Cooling system for hot parts of an aircraft engine, and aircraft engine equipped with such a cooling system

Abstract

The cooling system (30) for an aircraft engine (10) comprises a channel (32) that draws off cold air in the secondary air flow (200), and a heat exchanger (34) located in the channel (32) and in which hot air circulates.

The channel (32) comprises:

• • a supply pipe (322) and an evacuation pipe (326) fixed to the nacelle (324),
  • an intermediate box (324) located between the supply pipe (322) and the evacuation pipe (326), fixed to the engine (10), and in which the heat exchanger (34) is placed.

Application to cooling of hot parts (22) in an aircraft engine (10).

Description

TECHNICAL DOMAIN [0003] This invention relates to the technical field of cooling systems for hot parts of aircraft engines. [0004] More particularly it relates to a cooling system comprising a set of heat exchangers, to cool hot parts of an aircraft engine such as high pressure turbine blades in this aircraft engine. [0005] It also relates to an aircraft engine equipped with such a cooling system. STATE OF PRIOR ART [0006] It is known that heat exchangers can be installed in an aircraft engine to cool hot parts of an aircraft engine. [0007] Document FR 2 400 618 discloses a turbo-fan type of aircraft engine using an air / air type cooling system, and an associated cooling method. Hot parts such as fixed and mobile blades of the high pressure turbine are cooled by cooling air originating from part of the primary air drawn off at the outlet from the compressor or between compressor stages. This air cooling hot parts is itself firstly cooled before passing over the parts to be cooled, by...

AI Technical Summary

Benefits of technology

[0027] According to the invention, the outlet from the evacuation pipe of each channel opens up at the outlet from the nacelle ejection nozzle, or beyond it on the downstream side. Thus, air that exits from the evacuation pipe is at atmospheric pressure. Consequently, the risk of recirculation of air in the heat exchanger is eliminated, and pressure losses in the heat exchanger are increased.

Problems solved by technology

A first disadvantage is related to engine maintenance, particularly of the gas generator.

In the presence of a cooling system according to prior art, and particularly if the casing is in position around the gas generator or a channel fixed to the nacelle, it becomes difficult to access some parts of the engine for maintenance.

A second disadvantage of systems according to prior art is due to the fact that colder air used to cool fluid circulating in the heat exchanger is restored on the downstream side inside the fan duct.

There is then a risk that air could circulate in the inverse direction or not circulate at all, which would make the heat exchanger inoperative.

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