Variable-area injectors are suitable choices for developing throttleable rocket engines
because it is difficult to efficiently control thrust when fixed-area injectors are used. A pintle …

Gas generator is an essential part of gas generator cycle Liquid Propellant Rocket Engine
(LPRE). While designing the Gas Generator (GG), the selection of an unoptimized …

This paper presents a numerical simulation analysis of the flow and combustion
characteristics of a fuel-rich LOX (liquid oxygen)/kerosene gas generator in an ATR (air …

The design of liquid-propellant engines (LPEs) has several challenges in setting the
performance parameters. Accordingly, optimizing the design of a thrust chamber is of …

The present paper strives for optimization of the cooling system of a liquid‐propellant engine
(LPE). To this end, the new synthetic metamodel methodology utilizing the design of …

A genetic algorithm was used to develop optimal design methods for the regenerative
cooled combustor and fuel-rich gas generator of a liquid rocket engine. For the combustor …

Optimum characteristic length of the combustion chamber of liquid rocket engine is very
important to get higher energy from the liquid propellants. Characteristic length is defined by …

A large portion of the wet and dry mass budget in any space system is assigned to the
propulsion system. Each of these depends on the engine system design values. Any effort to …

The role of the injector is atomization and mixing. It dictates the size and geometry of the
combustion chamber and gas generator. Experiments are conducted with water-cooled …

为了研究航天煤油的富燃燃烧特性, 设计了一个气氧/煤油富燃燃气发生器, 并进行了室压范围1~
4MPa, 混合比范围0.25~ 0.52 的燃烧试验, 获得了混合比和室压对特征速度 …