Combustion stabilized injector
Abstract
Abstract THIS DISCLOSURE RELATES TO IMPROVEMENTS IN ROCKET ENGINE INJECTORS. ACCORDING TO THE PRESENT DISCLOSURE, A ROCKET ENGINE INJECTOR IS CONSTRUCTED FROM A PLURALITY OF DISCRETE THIN WAFERS, EACH HAVING PLANAR SURFACES AND EDGE SURFACES. A CONTROLLED PATTERN OF FLOW PASSAGES IS FORMED IN ONE PLANAR SURFACE OF EACH WAFER, EACH FLOW PASSAGE TERMINATING AT AN EDGE SURFACE OF THE WAFER. THE WAFERS ARE JOINED TOGETHER IN A STACK AND THE PASSAGE TERMINATING EDGE SURFACES FORM THE INJECTOR FACE OF THE INJECTOR. THE FLOW PASSAGES ARE ADAPTED TO PASS LIQUID PROPELLANT THERETHROUGH. TO REDUCE HIGH FREQUENCY COMBUSTION INSTABILITY, SHORT BAFFLES OR COMBUSTION STABILIZERS ARE PROVIDED AS AN INTEGRAL PART OF THE INJECTOR FACE. ACCORDING TO ONE FORM OF THE INVENTION, THE LIQUID PROPELLANT IS DELIVERED TO THE INJECTOR FACE IN SUCH A MANNER THAT THE FUEL FLOWS THROUGH PASSAGES OF CERTAIN WAFERS AND THE OXIDIZER FLOWS THROUGH PASSAGES ON OTHER WAFERS.
Inventors
- 👤 Charles B Mcgough
Bibliographic Details
Claims Analysis
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