Combustion chamber structure, particularly for a rocket engine

US11525420B2 · kind B2 · utility

Assignee

• ArianeGroup GmbH · DE

Inventors

• Andreas Goetz · Vaterstetten, DE
• Marc Geyer · Munich, DE
• Torben Birck · Munich, DE
• Olivier De Bonn · Ottobrunn, DE

Key dates

• Filing date: Jul 16, 2019
• Grant date: Dec 13, 2022
• Expiry date: Jul 16, 2039

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/205
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A combustion chamber structure for a rocket engine includes a hot gas wall (12) that surrounds a combustion chamber (40) and has a plurality of first coolant channels (50) and a plurality of second coolant channels (52). The plurality of first (50) and second (52) coolant channels extend from a first longitudinal end (16) of the hot gas wall (12) to a second longitudinal end (18) of the hot gas wall (12) opposite to the first longitudinal end (16). The combustion chamber structure (10) further comprises a first manifold (20) forming a first coolant chamber (30) and a second manifold (22) forming a second coolant chamber (32) being fluidly separated from the first coolant chamber (30). The first (20) and second (22) manifolds are provided at the first longitudinal end (16) of the hot gas wall (12) and extend in a circumferential direction of the hot gas wall (12). The first coolant chamber (30) is fluidly connected to each of the plurality of first coolant channels (50) and the second coolant chamber (32) is fluidly connected to each of the plurality of second coolant channels (52).