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):

Report Date:

1966-03-07

Pagination or Media Count:

202.0

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 fluorinehydrogen propellants because of the interest in pump-fed F2H2 propulsion systems for Air Force maneuvering satellite applications. An analytical study involving evaluation of dual-orifice injectors for pressure-fed engines using fluorinehydrazine and fluorineammonia was also accomplished this study revealed that dual-orifice injectors could be used to provide deep throttling capability with both fluorinehydrazine and fluorineammonia propellants. For fluorinehydrogen 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 fluorinehydrogen engines. Altitude tests are recommended with fluorinehydrogen 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 fluorinehydrazine, are also recommended. Author

Descriptors:

Subject Categories:

  • Rocket Engines
  • Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE


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