Method of manufacturing regeneratively cooled rocket combustion chambers

US4156306A · kind A · utility

Assignee

• Messerschmitt Bolkow Blohm GmbH · DE

Inventors

• Albert Seidel · Höhenkirchen-Siegertsbrunn, DE
• Dietmar Wolf · Höhenkirchen-Siegertsbrunn, DE
• Gunther Pulkert · Haar, DE
• Karl Butter · Ottobrunn, DE
• Kuno Knauer · Dorfen, DE

Key dates

• Filing date: Dec 16, 1977
• Grant date: May 29, 1979
• Expiry date: Dec 16, 1997

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y10T29/4981
• WIPO field: Machine tools
• WIPO sector: Mechanical engineering

Abstract

A method of manufacturing a regeneratively cooled rocket combustion chamber which includes a thrust nozzle portion connected to a combustion chamber portion and which is constructed with cooling channels which extend in the longitudinal direction between an inner shell or wall having a smooth interior surface and an outer shell or wall and which are laterally bounded by radially extending webs, comprises forming the inner shell along with the cooling channel webs by electrodepositing metal on an electroplating core which is made up of chemically dissolvable material and has its outside contour conformable to the inside contour of the inner wall of the combustion chamber which is provided with radially extending projections forming mold blades for the webs defining the lateral boundaries of the cooling channels. Thereafter, the cooling channels are filled with a multiple electrically well-conducting filling material up to the level of the outer ends of the webs after these outer ends have been finish turned. A metal layer is then electrodeposited around the complete periphery of the web end faces and over the periphery of the cooling channels to form the outer shell or wall. The fil…