Patent ID: 6834493
Filing Date: 2004-12-28
Classification: F02K,F04D

Abstract:
A system reducing pump cavitation in a rocket pump system comprising:a reservoir tank as a first fluid source operative to store a first fluid, said first fluid being a liquid; a heat exchanger; a rotary pump as a first pump; a first fluid path operative to enable passage of only said first fluid from said first fluid source through said heat exchanger to said first pump; a second fluid source operative to supply a second fluid which has a lower temperature than said first fluid; a second pump, and a second fluid path operative to enable passage of said second fluid from said second fluid source through said second pump to said heat exchanger; wherein said heat exchanger is operative to enable heat transfer from said first fluid to said second fluid and lowering the temperature of said first fluid at the inlet of said first pump for reducing pump cavitation in said first pump, and wherein said first and second fluids are liquid rocket engine propellants.