Rocket engine having a transition attachment between a combustion chamber and an injector
OwnerKurt B. Kreiner, David Bronson +3inventors
InventorsKurt B. Kreiner, David Bronson, Carl R. Stechman, Peter W. Woll, Joel M. Neiderman
Life of this patent
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Abstract
A rocket engine has a combustion chamber, an injector, and an attachment between the combustion chamber and the injector. The attachment includes an annular metallic deposit joined to the chamber wall outer surface, and an annular transition ring structure. The transition ring structure has an annular step collar, and an annular adaptor ring brazed to the annular step collar. The adaptor ring is welded on one end to the injector and on the other end to the metallic deposit.
Claims14
A rocket engine, comprising
- a combustion chamber comprising an annular wall with a chamber wall outer surface and a combustion chamber axis;
- an injector;
- and
- an attachment between the combustion chamber and the injector, the attachment comprising:
- an annular metallic deposit joined to a first region of the wall of the combustion chamber,
- an annular transition ring structure, wherein the transition ring structure comprises:
- an annular step collar,
- an annular adaptor ring, and
- a braze joint between at least a portion of the step collar and a portion of the adaptor ring,
- a first joint between the adaptor ring and the metallic deposit, and
- a second joint between the adaptor ring and the injector.
A rocket engine, comprising
- a combustion chamber comprising a generally cylindrical annular wall with a chamber wall outer surface, a chamber wall inner surface, and a cylindrical axis;
- an injector;
- and
- an attachment between the combustion chamber and the injector, the attachment comprising:
- an annular metallic deposit joined to the chamber wall outer surface,
- an annular transition ring structure including
- an annular step collar,
- an annular adaptor ring, and
- a braze joint between at least a portion of the step collar and a portion of the adaptor ring,
- a first weldment between a first welded portion of the adaptor ring structure and the metallic deposit, and
- a second weldment between a second welded portion of the adaptor ring structure and the injector.
A method for fabricating a rocket engine, comprising the steps of
- providing a combustion chamber comprising an annular wall with a chamber wall outer surface and a combustion chamber axis;
- depositing an annular metallic deposit on a first region of the wall of the combustion chamber;
- providing an attachment between the combustion chamber and the injector, the attachment comprising an annular transition ring structure comprising an annular adaptor ring and an annular step collar;
- welding the attachment to the metallic deposit;
- providing an injector;
- and
- welding the injector to the attachment.
Dependencies are inferred from the claim text.