Patent ID: 6470671
Filing Date: 2002-10-29
Classification: B23P,F02K,F05D,Y10T

Abstract:
A regeneratively coolable nozzle for a rocket engine, comprising a nozzle body (3) including a wound helical structure (5) of tubular material (6) forming turns (T) for flowing a coolant through said turns of said tubular material, said helical structure (5) having an axially facing end surface of tubular material, and an internal load bearing layer (9) applied to a radially inwardly facing surface of said wound helical structure (5) and capable of withstanding heat prevailing in said rocket engine, said internal load bearing layer (9) forming a radially inwardly facing hot-gas side (H) of said nozzle body (3), said nozzle body (3) further comprising at least one external load bearing layer (7) positioned at least on one outer radially facing end surface area (7A) of said nozzle body (3), radially outwardly of said wound helical structure (5) said external load bearing layer (7) of said nozzle body (3) further comprising an axially facing, radially extending flange-mounting (7B) positioned radially outwardly of said axially facing end surface of said tubular material.