Accession Number : AD0015932


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


Descriptive Note : Special rept.


Corporate Author : AEROJET-GENERAL CORP AZUSA CA


Personal Author(s) : Wilner, B M


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/015932.pdf


Report Date : May 1953


Pagination or Media Count : 39


Abstract : 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 5:1, 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 5:1 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.


Descriptors :   *LAVAL NOZZLES , *NOZZLE THROATS , *STEAM CONDENSERS , *LIQUID PROPELLANT ROCKET ENGINES , LOW PRESSURE , SENSITIVITY , MIXTURES , CROSS SECTIONS , CONVERGENCE , THRUST , REACTANTS(CHEMISTRY) , BACK PRESSURE , THEORY , HIGH VELOCITY , PERFORMANCE(ENGINEERING) , GUIDED MISSILES , DIAMETERS


Subject Categories : Liquid Propellant Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE