Accession Number : AD0378857

Title :   MULTISTAGE RADIAL IMPELLER PUMP PART I - DESIGN, FABRICATION, AND TEST.

Descriptive Note : Final rept.

Corporate Author : ROCKETDYNE CANOGA PARK CALIF

Report Date : JUL 1966

Pagination or Media Count : 163

Abstract : A high-pressure (5000 to 6000 psi) liquid hydrogen pump was designed, constructed, and tested. The pump consisted of a conventional inducer-impeller combination followed by two radial rows of stators and rotors and an impulse rotor. The impulse rotor discharged into a vaned diffuser where the flow was collected by 4 discharge cones. The pump was of the dual-entry type for the purpose of balancing the thrust resulting from the high pressures. The pump was tested up to 65 percent of its design speed, was (under normal running conditions) free of oscillations; no mechanical problems were evident. However, fixed orifices that were used at the discharge flanges of the cones to reduce the pressure to a value consistent with the stress limits of the facility ducting caused intolerable oscillations; consequently, testing was discontinued. The data obtained, when extrapolated by the affinity laws to design speed, indicated that a maximum pressure of 3100 psi would have been obtained. The peak efficiency was 53 percent. Analysis indicated that the diffuser downstream of the rotor did not function properly. The inducer impeller and the radial stages performed practically as predicted and also the discharge cone diffused efficiently. Practically all losses which account for the low discharge pressure occurred in the section between rotor discharge and the discharge cone. (Author)

Descriptors :   (*TURBOPUMPS, LIQUID PROPELLANT ROCKET ENGINES), DESIGN, IMPELLERS, ROTOR BLADES(TURBOMACHINERY), TURBINE STATORS, FRICTION, DIFFUSERS, DUCT INLETS, TEST EQUIPMENT, PERFORMANCE(ENGINEERING), OSCILLATION, VELOCITY, PRESSURE, THRUST, VIBRATION (U) HYDROGEN, LIQUEFIED GASES, ALUMINUM ALLOYS, TITANIUM ALLOYS, INCOMPRESSIBLE FLOW, HIGH PRESSURE

Subject Categories : Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE