Method of manufacturing regeneratively cooled rocket combustion

Details Method of manufacturing regeneratively cooled rocket combustion Method of manufacturing regeneratively cooled rocket combustion

1977-12-16

1979-05-29

Tufariello, T. M.

Metal working

Method of mechanical manufacture

Utilizing transitory attached element or associated separate...

204 16, 204 9, C25D 102, C25D 120

Patent

active

041563069

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 filling material is then melted out of the cooling channels and the electroplating core is hollowed out except for some millimeters of residual wall thickness and the remnant of the core is dissolved along with the radial projections to form the slots between the cooling channel webs which open into the center of the combustion chamber. The entire electrodeposited rocket combustion chamber is then engaged over the finishing mandrel and while it is on the mandrel, the cooling channels are deformed by applying pressure from inside the channels to close the slot which extends between the webs. When the thrust nozzle portion is formed integrally with the combustion chamber, the mandrel is transversely parted in the nozzle throat plane to permit insertion during the deforming of the cooling channels.

REFERENCES:
patent: 3595025 (1971-07-01), Stockel
patent: 3690103 (1972-09-01), Dederra
patent: 3692637 (1972-09-01), Dederra
patent: 3738916 (1973-06-01), Butter et al.
patent: 3768256 (1973-10-01), Butter et al.
patent: 3835644 (1974-09-01), Butter et al.
patent: 3897316 (1975-07-01), Huang

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