Abstract
A study was undertaken to develop swirl injectors for use with non -toxic hypergolic propellants. The goal of this effort was to establish a method to design swirl injectors operating in a thrust regime of 40 lbf-vac, with combustion chamber characteristic lengths of 30 in. Detailed are the development, design, and testing of a bi -centrifugal swirl injector for use with rocket grade hydrogen peroxide (RGHP) and non-toxic hypergolic miscible fuels (NHMF). This effort complements sister studies using pintle injectors for higher thrust applications. A literature review of existing inviscid swirl models is provided. Other design features of swirl injectors (oxidizer centered vs. fuel centered, multiple inlets vs. single inlets etc.) not addressed by inviscid theory are discussed. A total of eight injector iterations were designed, built, and subjected to cold flow and engine tests. Cold flow tests were conducted to measure the spray cone angle and discharge coefficient of the injector, and compared to theoretical predictions. Engine tests measured the characteristic velocity. Significant burning was observed inside of the injectors during each test. Characteristic exhaust velocity ( c*) efficiencies of 92% were measured in chambers with characteristic lengths (L*) of 72 inches, but fell to 70% in chambers with characteristic lengths of 30 inches. NOMENCLATURE A - Area, in 2
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