Rocket engine cooling system
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Apr 24, 2001
Grant Date -
N/A
app pub date -
Mar 10, 2000
filing date -
Mar 10, 1999
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A rocket engine comprises first and second combustion chambers with respective combustion chamber liners bounding respective annular passages, wherein the first combustion chamber discharges into the second, and the respective annular passages are in fluid communication with one another. A portion of the effluent from the first combustion chamber flows from the first combustion chamber to the second combustion chamber through the respective annular passages via orifices in the respective combustion chamber liners, so as to provide for effusion cooling of a surface of the second combustion chamber. The first combustion chamber preferably operates fuel rich, reducing the temperature of the effusion cooling gases, which may be further cooled by a portion of unburned fuel. A flow restriction such as a turbine between the first and second combustion chambers provides a pressure differential therebetween that induces flow of effusion cooling gases.
First Claim
Other Claims data not available