Combustion chamber/nozzle assembly and fabrication process there

Details Combustion chamber/nozzle assembly and fabrication process there Combustion chamber/nozzle assembly and fabrication process there

1998-08-14

2000-12-26

Thorpe, Timothy S.

Power plants

Reaction motor

Solid propellant

60271, F02K 900

Patent

active

061640603

ABSTRACT:
An integral, lightweight combustion chamber
ozzle assembly for a rocket engine has a refractory metal shell defining a chamber of generally frusto-conical contour. The shell communicates at its larger end with a rocket body, and terminates at its smaller end in a tube of generally cylindrical contour, which is open at its terminus and which serves as a nozzle for the rocket engine. The entire inner surface of the refractory metal shell has a thermal and oxidation barrier layer applied thereto. An ablative silica phenolic insert is bonded to the exposed surface of the thermal and oxidation barrier layer. The ablative phenolic insert provides a chosen inner contour for the combustion chamber and has a taper toward the open terminus of the nozzle.
A process for fabricating the integral, lightweight combustion chamber
ozzle assembly is simple and efficient, and results in economy in respect of both resources and time.

REFERENCES:
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patent: 3863442 (1975-02-01), Schmidt et al.
patent: 3871173 (1975-03-01), McKeena
patent: 4738100 (1988-04-01), Koorey
patent: 5212944 (1993-05-01), Martin et al.
patent: 5513489 (1996-05-01), Bussing
patent: 5579635 (1996-12-01), Miskelly, Jr. et al.
patent: 5613299 (1997-03-01), Ring et al.
Simpler Combustion Chamber, Nozzle, and Fabrication Process; NASA Tech Briefs; Apr. 1997, p. 68; vol. 21 No. 4; Associated Business Publications Co., Ltd.; NY, NY.

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