OXYGEN/HYDROGEN INJECTOR THRUST PER ELEMENT SIZE MAXIMIZATION.
Abstract
Results of the tests and evaluations performed on highly simplified, large thrust per element (LTE) injectors utilizing cryogenic propellants are presented. Phase II of Project Scorpio was conducted to determine the maximum thrust per injector element which could be utilized and still achieve high performance. High combustion efficiency, combustion stability, and heat transfer characteristics were the major items of concern. Twenty-nine test firings were conducted. The three injector patterns investigated were the: (1) single-element concentric pentad, (2) four-element concentric pentad, and (3) four-element concentric triplet. Two thrust chamber configurations, one uncooled and the other film cooled, were utilized. The basic characteristic length of 45 inches was varied to 75 inches by installing a section between the injector and thrust chamber. After a series of tests on each injector, modifications were made to the first two and the third one was fired reversed, i.e., fuel injected through oxidizer manifold and oxidizer injected through fuel manifold, to determine the effect on performance. Also, the injector film coolant holes and chamber film coolant passages were sealed to facilitate injector performance evaluation. Chamber stagnation pressure and mixture ratio were varied from 556 to 753 psia and 3.6/ 1 to 5.7/1, respectively. Combustion efficiency above 90% characteristic velocity was achieved with the four-element concentric pentad injector over a range of mixture ratios and chamber pressures.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1965
- Accession Number
- AD0372874
Entities
People
- Daweel George
- Howard V. Main
- Lester E. Tepe
- Vernon L. Mahugh