By Zhen-Guo Wang
This booklet concentrates on modeling and numerical simulations of combustion in liquid rocket engines, protecting liquid propellant atomization, evaporation of liquid droplets, turbulent flows, turbulent combustion, warmth move, and combustion instability. It provides a few state-of-the-art types and numerical methodologies during this area. The publication could be categorised into elements. half 1 describes the modeling for every subtopic of the combustion procedure within the liquid rocket engines. half 2 provides exact numerical technique and several other consultant functions in simulations of rocket engine combustion.
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This ebook concentrates on modeling and numerical simulations of combustion in liquid rocket engines, overlaying liquid propellant atomization, evaporation of liquid droplets, turbulent flows, turbulent combustion, warmth move, and combustion instability. It offers a few cutting-edge types and numerical methodologies during this quarter.
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Extra resources for Internal combustion processes of liquid rocket engines
025 s after being broken up into droplets of 50 μm diameter. Depending on the pattern of injection holes on the face of an injector, injectors can be categorized into several types. The commonly-used injecting units include impinging injectors, coaxial straight-flow injectors, and coaxial swirl injectors. Impinging injectors can be classified into unlike impinging injectors and self-impinging injectors. The unlike doublet impinging injectors are often used in rocket engines with storable propellants, such as low-thrust control rocket engines, apogee rocket engines, and ascent engines of Apollo lunar modules.
3 Development of Numerical Simulations of Combustion Process in Liquid Rocket Engines To maintain high reliability and reduce the test cost of liquid rocket engine design, usually several modifications are made to the current engine design based on engineering experience. Then these design modifications are evaluated using a large number of tests. However, the engine tests are always expensive and time-consuming. A single engine test may cost tens of thousands, hundreds of thousands, and even several million RMB Yuan.
For a long period, the design and development of a rocket engine relied on experiments. It has to go through many specific and full-scale engine tests, resulting in huge costs and long research periods. Numerical calculation of the combustion process in a liquid rocket engine can reproduce the practical combustion process on a computer. The unreasonable testing schemes can be abandoned based on simulation results. This can significantly reduce the number of tests and increase the testing success rate.