Outlet of a hot-gas pipe of an aircraft engine passing through an engine wall

Patent metadata

Field	Value
Publication number	US-11199108-B2
Application number	US-201917058433-A
Country	US
Kind code	B2
Filing date	May 24, 2019
Priority date	May 30, 2018
Publication date	Dec 14, 2021
Grant date	Dec 14, 2021

Abstract

The outlet of a heat exchange circuit extending under a wall, such as a nacelle cowling of an aircraft engine, is divided into openings in the form of parallel slots which are elongated in the longitudinal direction and successively arranged in the transverse direction to divide the hot gas into streams while facilitating the circulation of fresh gas streams, originating from an external flow, on the intermediate laminates. The hot gas cannot fall back easily onto the outer face of the wall and risk damaging the wall, and the gas mixes more effectively with the fresh outdoor air. The openings are provided with nozzles flaring in the transverse direction and the downstream longitudinal direction to facilitate the mixing of the hot and cold gas streams.

First claim

The invention claimed is:

1. An outlet of a hot-gas pipe of an aircraft engine, the pipe extending under a face called an inner face of an engine wall, opposite to a face called an outer face of the engine wall, the pipe connecting to the outlet, the outlet defining a plurality of oblong and distinct openings passing through the engine wall, having a direction of main elongation substantially coinciding with a direction of a flow of cool gas over the outer face during ordinary engine operation, the openings succeeding each other in a transverse direction of the engine wall which is perpendicular to the direction of main elongation, wherein the openings are provided with slats flaring in the transverse direction, and extending beyond one end of the openings in said downstream direction.

2. The outlet according to claim 1 , wherein the openings are surrounded and delimited by low walls established on the outer face of the engine wall and rising above the outer face in a radial direction, the slats being placed on an upper edge of the low walls.

3. The outlet according to claim 2 , wherein the low walls have different heights above the outer face for each of the openings.

4. The outlet according to claim 1 , wherein the outer face of the engine wall is in depression curved around the openings.

5. The outlet according to claim 1 , wherein the openings gradually taper along the longitudinal direction.

6. The outlet according to claim 1 , wherein the openings are separated by distances greater than their widths in the transverse direction.

7. The outlet according to claim 1 , wherein the pipe is divided into distinct branches respectively connected to the openings before reaching the outlet.

Assignees

• Safran Aircraft Engines

Inventors

• Ferrier Romain Jean-Claude
• Chalaud Sébastien Christophe
• Chanez Philippe Gérard
• Davis Lauren
• Verdier Bastien Pierre
• Vessot Christian Sylvain

Classifications

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F05D2250/52

  Outlet · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title