Accession Number : ADA316054
Title : Swirl Effects on Coaxial Injector Atomization.
Descriptive Note : Final technical rept. 1 Jun 93-31 May 96,
Corporate Author : PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL ENGINEERING
Personal Author(s) : Santoro, Robert J.
PDF Url : ADA316054
Report Date : AUG 1996
Pagination or Media Count : 96
Abstract : The focus of this AASERT grant was the investigation of atomization processes for swirl coaxial gas/liquid spray injection for rocket combustor applications. The work has included review and analysis of atomization literature for swirled and non-swirled gas/liquid sprays, design and fabrication of a rocket-scale swirl coaxial injector for research, and cold-flow and hot-fire characterizations of atomization and combustion with the designed injector. Two significant findings have emerged from the present studies; (1) our experiments in a windowed research combustor were the first to demonstrate that swirl coaxial injection allows for highly efficient propellant combustion (liquid oxygen/gaseous hydrogen) over a wide range of oxidizer-to-fuel ratios from 3 to 175. The result was of interest to industry in conceptual design of a novel rocket-engine cycle, for RLV application, relying upon very high oxidizer-to-fuel ratio combustion in a liquid oxygen preburner, and (2) optical diagnostics were applied to demonstrate a methodology for scaling spray drop size/velocity results based on liquid Weber number. This is of intrinsic value to the spray community, and of direct impact within the rocket-injector design community, where the scaling approach can be incorporated into injector sizing activities.
Descriptors : *COAXIAL CONFIGURATIONS, *INJECTORS, *ATOMIZATION, INJECTION, IMPACT, HYDROGEN, GASES, PROPELLANTS, COMBUSTORS, OPTICAL ANALYSIS, SCALING FACTOR, SPRAYS, ROCKETS, LIQUID OXYGEN.
Subject Categories : Physical Chemistry
Combustion and Ignition
Distribution Statement : APPROVED FOR PUBLIC RELEASE