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Nomenclature
Symbols
= average specific impulse, s
= total impulse, s
= rocket mass ratio
= start launch vehicle mass, kg
= final launch vehicle mass, kg
= propellant mass (burning mass), kg
= engine mas, kg
= turbopump mass, kg
= engine burning time, s
= combustion chamber pressure, Pa
= oxidizer pump discharge pressure, Pa
= pressure drop in chamber fuel line, Pa
= pressure drop in oxidizer line, Pa
= pressure difference of turbine, Pa
= 1st fuel pump discharge pressure, Pa
= 2nd fuel pump discharge pressure, Pa
= preburner pressure, Pa
= pump inlet pressure, Pa
= propellant vapor pressure, Pa
= developed head of pumps, m
= turbopump rotational speed, rpm
= pump volumetric flow rate, m3/s
= critical net positive suction head, m
= pump suction specific speed coefficient
= pump efficiency
= pump specific speed, m/s
= specific power of turbine, J/kg
= specific power of oxidizer pump, J/kg
= specific power of fuel pump, J/kg
= turbine pressure ratio
= turbine efficiency
= ratio of specific heat
= working capability of gasses, J/kg
Definitions, acronyms and abbreviations
= fuel
= liquid rocket propulsion system
= oxidizer
= single-burner, oxidizer-rich staged combustion
Introduction
The engine with “staged combustion cycle” has the supreme energetics performance of all launch vehicle engine, especially when considered as a first stage for “liquid rocket propulsion systems (LRPS)” that deliver payload into low earth orbit. As the higher cost of launching satellites to space usually leads engineer to select “staged combustion” cycle and also optimizing engine’s parameters to increase the ratio of “total impulse” to “gross mass” of propulsion system.
One of the well-known Russian engines in this category is RD-180, equipped with oxidizer (ox)-rich pre-burner, which releases more energy than fuel (fu)-rich pre-burner at the same temperature. Therefore,...