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Now that we have our angles and our injector plate thickness, we need to start thinking about how to design a manifold. This is especially tricky since there can only be one inlet for oxidizer due to spacing constraints between the chamber assembly and tank (remember that this needs to fit inside of a rocket) so having two separate annular regions separated by a fuel annulus in the middle would be impossible. Since the length of the faceplate for fuel is smaller than the length of the faceplate for oxidizer, a clever way to design the manifold is to actually make it two parts. The fuel manifold can be the same height as the thickness of the ox faceplate minus the thickness of the fuel faceplate; placing it on the faceplate would thus create an even surface. Then, you can place the oxidizer manifold above this so that the oxidizer circulates above the fuel annulus. One can simply place O-rings where these two parts mate to prevent leakage. That probably is hard to visualize, so here's a photo (subject to change):
Here, you see that the region in which the fuel circulates (the annulus) is positioned below the region in which the oxidizer circulates. The cross-sectional area of a circulation flow region is optimized at 4 times the area of the orifices contained within that region, which we calculated to be TBD and TBD. The reason why the oxidizer annulus height is so small is because its x distance is very large.
We created a Jupyter Notebook to calculate parameters for the injector.
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