Method for producing a nozzle for a rocket engine
AssigneeAstrium GmbH
InventorJoachim Kretschmer
Life of this patent
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Abstract
A regeneratively coolable nozzle for a rocket engine is formed by winding a tubular material (6) onto a winding mandrel to produce a helical composite structure (5), through which a coolant can flow during operation of the nozzle. The spiral composite structure (5) is fixed temporarily and the fixed composite structure (5) is removed from the winding mandrel. Then an inner heat resistant, load bearing layer (9) is applied to the radially inner hot-gas facing surface (H) of the fixed composite structure (5). The present nozzle is lightweight and withstands a high coolant pressure.
Claims21
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).
The method of clain 15, further comprising annealing said nozzle body (3), said internal heat resistant, load bearing layer (9) and said external heat resistant load bearing layer (7).
Dependencies are inferred from the claim text.