Rocket combustion chamber wall having cooling channels and method for making thereof

US11643996B2 · kind B2 · utility

Assignee

• ArianeGroup GmbH · DE

Inventors

• Stefan Winter · Würselen, DE
• Martin Malisz · Munich, DE

Key dates

• Filing date: Dec 7, 2021
• Grant date: May 9, 2023
• Expiry date: Dec 7, 2041

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2300/172
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A combustion chamber suitable in particular for use in an engine comprises a combustion space, a combustion space wall delimiting the combustion space, and a plurality of cooling channel webs extending from a surface of the combustion space wall which faces away from the combustion space and separating mutually adjacent cooling channels from one another. The cooling channel webs are each provided with a projection extending from an end face of the cooling channel webs which faces away from the combustion space. Furthermore, the combustion chamber comprises a plurality of cover elements, wherein each cover element extends along a longitudinal axis of a cooling channel delimited by two mutually adjacent cooling channel webs between the projections of the mutually adjacent cooling channel webs and is form-fittingly connected to the projections of the two mutually adjacent cooling channel webs in order to cover the cooling channel.