Combustion chamber structure, particularly for a rocket engine

US10830182B2 · kind B2 · utility

Assignee

• ArianeGroup GmbH · DE

Inventors

• Marc Geyer · Munich, DE
• Andreas Goetz · Vaterstetten, DE
• Torben Birck · Munich, DE

Key dates

• Filing date: Aug 15, 2017
• Grant date: Nov 10, 2020
• Expiry date: Nov 30, 2037

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/31
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A combustion chamber structure, particularly for a rocket engine, which comprises a liner surrounding a combustion chamber with an outer surface facing away from the combustion chamber on which coolant channels extending in a longitudinal direction of the liner are formed. The liner forms, at one longitudinal end, a coolant chamber extending in the circumferential direction of the liner for collecting and/or distributing a coolant. The combustion chamber structure further comprises a connecting structure that fluidly connects the coolant chamber to the coolant channels.