Patent ID: 6543135
Filing Date: 2003-04-08
Classification: B23P,F02K,F05D,Y10T

Abstract:
A method for producing a regeneratively coolable nozzle for a rocket engine, said method comprising the following steps:winding turns of a tubular material (6) onto a winding spindle or mandrel (M) to form a helical composite structure (5) as part of a nozzle body (3), for flowing a coolant through said tubular material during operation of the coolable nozzle; fixing said helical composite structure (5) for holding said turns in place to form a fixed helical composite structure (5); removing said fixed helical composite structure (5) from said winding spindle or mandrel (M); and applying an internal heat resistant load bearing layer (9) to a radially inwardly facing surface of said fixed helical composite structure (5), said load bearing layer having a radially inwardly facing surface forming a hot-gas side (H) of said nozzle body (3).