| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 1718851 | Aerospace Science and Technology | 2008 | 9 Pages |
Abstract
A novel injection concept for cryogenic liquid propellant rocket engines has been tested and verified successfully using an optically accessible combustion chamber. The injector consists of a porous faceplate made from sinter metal and five LOX posts arranged in a classical parallel showerhead configuration. While liquid oxygen is injected at similar velocities known from typical coaxial injector elements, the fuel enters the combustion chamber at much lower velocities. The flame stabilization for both LOX/H2 and LOX/CH4 propellant combination has been investigated at sub-, near-, and supercritical pressures.
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