Accession Number : AD0372456

Title :   HYDROSTATIC COMBUSTION SEAL DEMONSTRATION FEASIBILITY PROGRAM.

Descriptive Note : Final progress rept,

Corporate Author : AEROJET-GENERAL CORP SACRAMENTO CALIF

Personal Author(s) : Fleischmann ,J. J. ; Reynolds ,C. J. ; Livingston ,R. A. ; Spencer ,B. B. ; Burkey,W. N.

Report Date : MAY 1966

Pagination or Media Count : 147

Abstract : The major objectives of the Hydrostatic Combustion Seal Demonstration Feasibility Program was the investigation of a seal concept, operating in an oxidizer-rich atmosphere with a turbine-shaft operating speed of 40,000 rpm. Additional objectives were: (1) the design and fabrication of testers and components in which this seal can be tested, (2)the fabrication of test seals, (3) water tests at reduced speeds and pressures, and (4) hot testing (under reduced pressure) of a thin static cross section of the seal. All the technical objectives of the program were attained. A hydrostatic combustion seal was designed, fabricated, and tested at speeds up to 28,000 rpm using water instead of propellant as a lubricant. Performance of the seal exceeded the design goals, with no damage to the hardware. Alternative seal concepts were analyzed and tested. Testers were designed and fabricated to permit seal tests under hydraulic and combustion conditions. A tester and seal-test segments were designed, and a test series was completed wherein the feasibility of the combustion concept was demonstrated at planned reduced pressures. (Author)

Descriptors :   (*FUEL SEALS, HYDROSTATIC PRESSURE), (*SEALS, HYDROSTATIC PRESSURE), PERFORMANCE(ENGINEERING), DESIGN, FEASIBILITY STUDIES, SEALING COMPOUNDS, COMBUSTION, COMBUSTION CHAMBER GASES (U) LIQUID ROCKET OXIDIZERS, PURGING, AXLE SHAFTS, TURBINES, LIQUID ROCKET PROPELLANTS, LIQUID PROPELLANT ROCKET ENGINES, FUEL PUMPS, LEAKAGE(FLUID), HYDRAZINE, TURBOPUMPS

Subject Categories : Adhesives, Seals and Binders
      Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE