| 摘要 |
A self starting valved pulse jet particularly adapted to power pilotless aircraft in the subsonic speed range. This invention is somewhat related to my U.S. Pat. No. 3,823,554. The device continues to utilize a substantially cylindrical combustion chamber, a reduction cone and exhaust tube. The multiplicity of reverse flow air and fuel inlet tubes projecting through the reduction cone into the combustion chamber have been modified so each air and fuel inlet utilizes two tubes axially aligned with each other. The aft tube diameter is less than the forward tube. An opening between the tubes permits gas to flow to and from an annular plenum chamber surrounding the air inlet tubes. The plenum chamber also houses an equal number of shrouded valve assemblies in its outer wall. The small aft tube of the air and fuel inlet secures and penetrates through the aft annular wall of the plenum chamber. The aft end of the small diameter tube contains a one-way flow valve permitting air to flow through it only during engine start. After engine start all air flows through the one way flow valve assemblies housed horizontally in the outer wall of the aforementioned annular plenum chamber and into the large diameter forward tube and into the combustion chamber similar to my aforementioned patent. High pressure fuel is injected through the air and fuel inlets into the combustion chamber. Starting ignition in the combustion chamber insures a quick engine start with movement of one throttle lever.
|
