LIQUID-PROPELLANT ROCKET ENGINE-TEST STAND Russian patent published in 2009 - IPC F02K9/96 G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: invention relates to test stands intended for testing high-output liquid propellant rocket engines. The ejector prechamber communicates with the intake line, while its nozzle is connected to the multi-chamber pump outlet. Note that the ejector outlet is coupled with the pump inlet sucking water in from the reservoir, while the suck-in pipeline intake represents a branch pipe with its cylindrical surface furnished with a number of orifices. The said branch pipe end face is stopped with a plug, while the branch pipe is arranged in the pit made at the reservoir bottom center. There is a tapered cover fitted right above the said pit. Note that there is a gap between the tapered cover face and the reservoir bottom arranged inclined to the center at an acute angle.

EFFECT: higher efficiency of intake device removing deposits from reservoir bottom using ejector without draining water from test stand.

6 cl, 5 dwg