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Mixing of Cryogenic Fluids in Rocket
Injectors
Investigators: Vivek
Gautam, Ahmed
Abdelhafez, Jakub
Gmurczyk
Overview
The objective of this research is to work with NASA engineers and researchers to
examine the mixing behavior of various cryogenic, non-cryogenic propellants and
their simulants from a realistic rocket engine injector. Our goal is to provide
detailed information on shear layer and other modes of mixing and its subsequent
effect on ignition, stability and performance in a single element of the rocket
injector under atmospheric pressure and simulated in-space conditions. The
detailed database will be used for model validation and model development. The
approach used is both experimental and theoretical.
Sample
Images from High Speed Cameras
High speed image of unconfined LN2/GN2 flow with no recess |
High speed image of unconfined LN2/GN2 flow with 0.2 inch recess |
Shlieren movie of LN2/GN2 flow |
High speed image of unconfined LN2/CO2 flow (MR = 12) |
High speed image of unconfined LN2/He flow (MR = 40) |
Distribution of centerline temperature for the IR thermal images |
Sample
Images from IR Thermal
IR thermal image of unconfined LN2/GN2 flow with no recess |
IR thermal image of unconfined LN2/GN2 flow with 0.2 inch recess |
Temperature distribution (°C) for unconfined LN2/CO2 flow with no recess (MR = 12) |
Temperature distribution (°C) for unconfined LN2/He flow with no recess (MR = 40) |
Sample Schlieren Images
LN2/CO2 (MR = 5.6) |
LN2/He (MR = 5.6) |
LN2/He (Swirl Number = 5 , MR = 5.6) |
Sample
Results on Ignition Behavior of H2/O2 and
CH4/O2 Mixtures
PIV Results
Flowfield distribution with He (inner pipe) / O2 (outer annulus) case |
Flowfield distribution with He (inner pipe) / CO2 (outer annulus) case |
Axial velocity distribution at a distance of Y = 0.16 D from the injector exit |
Shear strain distribution at a distance of Y = 0.16 D from the injector exit |
Last Edited: May 13, 2006