BENCH FOR FIRING TESTS OF LIQUID-PROPELLANT ROCKET ENGINES Russian patent published in 2009 - IPC F02K9/96 G01M15/14 

FIELD: engine and pumps; blasting.

SUBSTANCE: specified bench comprises armor chamber with liquid-propellant rocket engine, cooled gas-dynamic tube having confusor, cylindrical and diffuser sections and facilities for creation of cocurrent flow of gaseous nitrogen and air supplied to gas-dynamic tube. Peculiar feature of proposed bench is application of annular vane swirler of cocurrent flow installed at the inlet to confusor section of gas-dynamic tube. Annular vane swirler is made from the following components connected to each other - force ring with flange, vanes and binding. Vanes of specified swirler are installed at the angle of 35-55° to axis of gas-dynamic tube, at that height of these vanes is selected to prevent inleakage of high-temperature supersonic jet, and pitch of vanes is defined to provide required flow of cocurrent flow from armor chamber and vanes cooling.

EFFECT: possibility to perform firing tests of liquid-propellant rocket engines (LRE) of low capacity in benches designed for firing tests of LRE of higher capacity.

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