RESEARCH AND DEVELOPMENT ON THE STEAM-JET CONDENSER FOR THE HYDRODUCTOR PROPULSION SYSTEM

A missile such as the Alclo hydroduct is propelled by a jet of high-velocity steam exhausting through a DeLaval nozzle. By condensing the exhaust with a steam-jet condenser, a low back pressure can be maintained on the steam nozzle and the performance of the missile can be increased and made relatively insensitive to depth. A direct-contract condenser can be applied to the system, since the exhaust of this hydroduct consists of steam and solid reaction products which are completely condensable. A theoretical analysis is presented of the functioning of the different components of the system. Tests showed that the water-inlet passages should have a length-to-diameter ratio of at least 51, and should be placed at an angle to the axis such that the point of convergence lies about 1 to 2 chamber-throat diameters upstream from the throat of the condensing chamber. For operation near the surface the water passage should be constant cross section to prevent separation of flow at the scoop entrance. Successful operation was achieved with a condensing chamber having a 51 ratio of length to throat diameter. Test data curves for a stream-jet condenser were extrapolated for a steam pressure of 300 psia. This curve indicated a system which was stable for all depths down to 1000 ft. With an area ratio R of 0.70 to 0.80, a mixture ratio Beta of 20 to 25, and a depth of 800 ft the system should produce about 65 of the net thrust available at the surface.