Lightweight rocket engine combustion chamber and associated method
AssigneeThe Boeing Company
InventorsJohn Wooten, Clifford Bampton
Life of this patent
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Abstract
A lightweight rocket engine combustion chamber and an associated method are provided. In one embodiment of the present invention, the combustion chamber includes an inner liner defining an inlet and an outlet, and at least one bonding strip attached to the liner. The combustion chamber also includes a structural jacket bonded to the bonding strip.
Claims28
A combustion chamber for containing and directing combustion of a propellant, the combustion chamber comprising:
- an inner liner defining an inlet and an outlet;
- at least one bonding strip attached to the liner;
- and
- a structural jacket bonded to the bonding strip.
A method for assembling a combustion chamber comprising:
- providing an inner liner defining an inlet and an outlet;
- attaching at least one bonding strip to the inner liner;
- and
- bonding a structural jacket to the bonding strip.
A combustion assembly comprising:
- a combustion chamber comprising:
- an inner liner defining an inlet and an outlet;
- and
- at least one bonding strip attached to the liner;
- and
- a structural jacket bonded to the bonding strip;
- and
- an injector assembly attached to the combustion chamber.
A method for providing thrust to a combustion chamber, the combustion chamber comprising a liner and a structural jacket, the method comprising:
- providing at least one bonding strip attached to the inner liner, and a structural jacket bonded to the bonding strip;
- injecting a coolant proximate to the inner liner;
- and
- injecting a propellant and an oxidizer proximate to an inlet of the inner liner, the oxidizer combusting the propellant to generate thrust through an outlet of the inner liner.
Dependencies are inferred from the claim text.