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Design and Study of a LOX/GH2 Throttleable Swirl Injector for Rocket ApplicationsA LOX/GH2 swirl injector was designed for a 10:1 propellant throttling range. To accomplish this, a dual LOX manifold was used feeding a single common vortex chamber of the swirl element. Hot-fire experiments were conducted for rocket chamber pressures from 80 to 800 psia at a mixture ratio of nominally 6.0 using steady flow, single-point-per-firing cases as well as dynamic throttling conditions. Low frequency (mean) and high frequency (fluctuating) pressure transducer data, flow meter measurements, and Raman spectroscopy images for mixing information were obtained. The injector design, experimental setup, low frequency pressure data, and injector performance analysis are presented. C* efficiency was very high (approx. 100%) at the middle of the throttleable range with somewhat lower performance at the high and low ends. From the analysis of discreet steady state operating conditions, injector pressure drop was slightly higher than predicted with an inviscid analysis, but otherwise agreed well across the design throttling range. Dynamic throttling of this injector was attempted with marginal success due to the immaturity of the throttling control system. Although the targeted mixture ratio of 6.0 was not maintained throughout the dynamic throttling profile, the injector behaved well over the wide range of conditions.
Document ID
20020075590
Document Type
Conference Paper
Authors
Greene, Christopher
(Pennsylvania State Univ. University Park, PA United States)
Woodward, Roger
(Pennsylvania State Univ. University Park, PA United States)
Pal, Sibtosh
(Pennsylvania State Univ. University Park, PA United States)
Santoro, Robert
(Pennsylvania State Univ. University Park, PA United States)
Date Acquired
August 20, 2013
Publication Date
April 1, 2002
Publication Information
Publication: 38th JANNAF Combustion Subcommittee Meeting
Volume: 1
Subject Category
Spacecraft Propulsion And Power
Funding Number(s)
CONTRACT_GRANT: NAG8-1732
Distribution Limits
Public
Copyright
Other

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IDRelationTitle20020075551Analytic Primary38th JANNAF Combustion Subcommittee Meeting
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