Arrangement for the production of rotational energy in rocket combustion engines

US3937012A · kind A · utility

Assignee

• Messerschmitt Bolkow Blohm GmbH · DE

Inventors

• Willi Zeh
• Werner Beck · Weyhe, DE
• German Munding · Bad Friedrichshall, DE

Key dates

• Filing date: Dec 10, 1973
• Grant date: Feb 10, 1976
• Expiry date: Dec 10, 1993

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F02K9/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

An arrangement for producing rotational energy, particularly for generating thrust gases in rocket combustion chambers using hypergolically reacting propellants, comprises a rocket combustion chamber having a closed end and a gas discharge end with an impeller mounted in the closed end. The impeller has a plurality of spaced vanes which extend radially and which define flow ducts therebetween having discharge ends which extend substantially tangential to the combustion periphery. The apparatus includes means for directing hypergolically reacting propellant components into the combustion chamber at a location in which they are deposited at the inner radial ends of the flow ducts. The oxygen carrier propellant is supplied radially inside of the other propellant component so that it forms a cooling veil along the impeller. The impeller is advantageously rotatably mounted so that the components are whirled outwardly into the combustion chamber and the individual blades are provided with passages in order to enhance the interreaction of the propellant components.