Rocket engine with combustion chamber step structure insert, and

Power plants – Reaction motor – Liquid oxidizer

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Details

2989001, 60 3932, F02K 952, F02K 962

Patent

active

061384518

ABSTRACT:
A rocket engine has a combustion chamber formed of an annular wall made of an annular wall material, and an annular insert made of an annular insert material that is of substantially the same thermal expansion coefficient as the annular wall material. The annular insert has an insert outer surface sized to fit within and contact the wall inner surface along less than the wall length. The annular wall and the annular insert are welded together. There is further an attachment between the combustion chamber and an injector. The attachment includes an annular metallic deposit bonded to the combustion chamber, an annular adaptor ring, a weld joint between the adaptor ring and the metallic deposit, and a joint between the adaptor ring and the injector.

REFERENCES:
patent: 2992528 (1961-07-01), Ozanich et al.
patent: 3000184 (1961-09-01), Fish
patent: 3581495 (1971-06-01), Kah, Jr.
patent: 3851468 (1974-12-01), Frankle et al.
patent: 4901526 (1990-02-01), Barth et al.
patent: 4917968 (1990-04-01), Tuffias et al.
patent: 4936091 (1990-06-01), Schoenman
patent: 5613299 (1997-03-01), Ring et al.

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