Accession Number : AD0370175

Title :   HIGH ENERGY ADVANCED THROTTLING CONCEPT STUDY.

Descriptive Note : Final rept. 1 Jul 64-30 Sep 65,

Corporate Author : PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FLA

Personal Author(s) : Mitchell,James P.

Report Date : 07 MAR 1966

Pagination or Media Count : 202

Abstract : The results of a study evaluating throttling capabilities of dual-orifice injectors with high energy propellant combinations are reported. Most of the work was devoted to fluorine/hydrogen propellants because of the interest in pump-fed F2/H2 propulsion systems for Air Force maneuvering satellite applications. An analytical study involving evaluation of dual-orifice injectors for pressure-fed engines using fluorine/hydrazine and fluorine/ammonia was also accomplished; this study revealed that dual-orifice injectors could be used to provide deep throttling capability with both fluorine/hydrazine and fluorine/ammonia propellants. For fluorine/hydrogen propellants, an injector design study followed by a sea level test program was accomplished. Combustion performance was evaluated with 1000-lb maximum thrust dual-orifice injectors and with 8500-lb maximum thrust injectors. The subscale injector program demonstrated injector durability and good performance over a thrust range of approximately 10 to 1. The 8.5K injectors gave essentially constant c* efficiency above 96% over a thrust range of approximately 30 to 1. Based on these results, it was concluded that dual-orifice injectors will provide high combustion performance in throttleable pump-fed fluorine/hydrogen engines. Altitude tests are recommended with fluorine/hydrogen to evaluate dual-orifice injector durability and performance over at least 50 to 1 thrust range. Dual-orifice injector tests with other high energy propellants such as fluorine/hydrazine, are also recommended. (Author)

Descriptors :   (*ROCKET ENGINES, THROTTLING), STABILITY (U) *LIQUID PROPELLANT ROCKET ENGINES), (*FUEL INJECTORS), FUEL SYSTEMS, LIQUID ROCKET PROPELLANTS, FLUORINE, HYDROGEN, THRUST, INJECTION, AMMONIA, HYDRAZINE, MIXTURES, VELOCITY, HYDRAZINE DERIVATIVES, COMBUSTION CHAMBERS, SATELLITES(ARTIFICIAL), MANEUVERABILITY

Subject Categories : Rocket Engines
      Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE