Rocket combustion chamber coating

Details Rocket combustion chamber coating Rocket combustion chamber coating

2000-01-19

2001-11-13

Thorpe, Timothy S. (Department: 3746)

Power plants

Reaction motor

Liquid oxidizer

C060S279000, C029S890010

Reexamination Certificate

active

06314720

ABSTRACT:

BACKGROUND OF THE INVENTION
1. Field of the Invention
In general, this invention pertains to rocket engines. Specifically, this invention pertains to a protective coating for the combustion chamber of a liquid-fueled rocket engine.
Although this invention was developed for rocket engines, the invention has application to parts of other apparatuses that utilize or are exposed to combustive or high-temperature environments (i.e., jet engines, gas turbines, incinerators, furnaces, heat exchangers, reactors, welders, etc.).
2. Background Information
The combustion chamber of a rocket engine is exposed to a very intense environment of heat and pressure during operation. In fact, the life of a rocket engine is highly dependent upon the ability of a combustion chamber to withstand the violent, combustive environment. Like many other high performance applications, several materials are combined to meet the demanding fabrication and performance requirements associated with a combustion chamber. For example, good thermal conductance is needed to keep the combustion chamber from getting too hot, and resistance to thermal corrosion and oxidation is needed to ensure a reasonable life expectancy of the chamber itself. A method of protecting the inside wall (i.e., lining) of a combustion chamber from thermal corrosion and oxidation consists of providing a thin protective coating on the lining of the combustion chamber. However, even with special intermediate adhesive or bond coatings, the protective coating has a strong tendency to delaminate in the combustive environment.
SUMMARY OF THE INVENTION
This invention has the ability to protect the inside wall (i.e., lining) of a rocket engine combustion chamber from the adverse effects of heat and oxidation. The novelty of this invention lies in the manner a protective coating is embedded into the lining.
An object of this invention is to protect the combustion chamber of a liquid-fueled rocket engine from the deleterious effects of thermal corrosion and oxidation.
Another object of this invention is to provide a protective coating for the combustion chamber of a rocket engine that is more durable than conventional coatings, and consequently, that extends the life of the rocket engine.
Still another object of this invention is to provide an insulative coating (i.e., thermal barrier) for the combustion chamber of a rocket engine that lowers the operating temperature of the combustion chamber and thereby extends the life of the rocket engine.
A further object of this invention is to provide a protective coating for parts of apparatuses that utilize or are exposed to combustive or high-temperature environments in order to protect such parts from corrosion associated with extreme heat and/or oxidation.


REFERENCES:
patent: 3250070 (1966-05-01), Milewski
patent: 6164060 (2000-12-01), Myers

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