Review on pressure swirl injector in liquid rocket engine

Kang, Zhongtao; Wang, Zhenguo; Li, Qinglian; Cheng, Peng

doi:10.1016/j.actaastro.2017.12.038

Cited by 74 publications

(9 citation statements)

References 126 publications

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“…(Xue et al, 2004) discusses the influence of some important geometric parameters on the performance of pressure-swirl atomizers, via the assessment of the discharge coefficient, the dimensionless film thickness and the spray cone half-angle through Computational Fluid Dynamics (CFD) simulations and through an inviscid analysis, from the work of (Giffen and Muraszew, 1953). (Kang et al, 2018) presents an extensive review on pressure swirl injectors in liquid rocket engines and how it affects the atomization steps of the liquid propellant. The main mechanisms of droplet formations and empirical data retrieved from other studies are displayed in a comprehensive overview.…”

Section: Injection Patterns and Atomization Modelsmentioning

confidence: 99%

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Injector and Combustion Chamber Design for a Nitrous Oxide and Ethanol Rocket Engine

Tavares¹,

Ceotto²

2021

Preprint

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This report presents the basic design of a rocket engine injector and combustion chamber for saturated nitrous oxide and liquid ethanol, as well as details of the construction and operation of the engine in which the injectors will be used. At first, an oxidant-fuel mixture is selected based on a thermochemical analysis that explores several existing options and other combinations that have not yet been studied. As a result, nitrous oxide is chosen as an oxidant and ethanol as fuel. Then a simplified methodology is proposed for the design of a pressure-swirl injector responsible for ethanol. Computational fluid dynamics is used to verify the validity of the above-mentioned analysis, using Volume of Fluid (VOF). For the nitrous oxide injector, the flash-boiling phenomenon is investigated, verifying its importance for the ongoing project. The effect is treated analytically using the Dyer model to account for non-equilibrium thermodynamics. Simplified zero-dimensional and one-dimensional combustion models are explored as tools to design the rocket combustion chamber. Furthermore, combustion instability due to acoustic phenomena is studied, with the first spinning tangential mode being computed for the herein developed motor and an ensemble of acoustic cavities being developed to suppress the aforementioned mode. Finally, a preliminary diagram of the static test bench which will be used to validate the injectors and the designed engine is also presented.

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Section: Injection Patterns and Atomization Modelsmentioning

confidence: 99%

“…The conservation of angular momentum yields the following relationship between tangential velocity w and radius r: Source: (Kang et al, 2018) Where i denotes inlet conditions. The tangential velocity at the inlet can be calculated by:…”

Section: Pressure-swirl Analytical Modelmentioning

confidence: 99%

Injector and Combustion Chamber Design for a Nitrous Oxide and Ethanol Rocket Engine

Tavares¹,

Ceotto²

2021

Preprint

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“…Kang et al. 24 reviewed the experimental and theoretical equations of the characteristics of a pressure-swirl injector spray. Rezaei et al.…”

Section: Introductionmentioning

confidence: 99%

Experimental comparison of the spray atomization of heavy and light fuel oil at different temperatures and pressures for pressure-swirl injector

Rostami

Mahdavy-Moghaddam

2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this study, the atomization of heavy fuel oil (Mazut) and diesel fuel at different pressures is compared experimentally. Also, the effects of temperature on the Mazut fuel atomization are investigated experimentally. Mass flow rate, discharge coefficient, wavelength, liquid film thickness, ligament diameter, spray angle, breakup length, and sature mean diameter are obtained for the Mazut and diesel fuel. Fuels spray images at different pressures and temperatures are recorded using the shadowgraphy method and analyzed by the image processing technique. Error analysis is performed for the experiments, and the percentage of uncertainty for each parameter is reported. The experimental results are compared with the theoretical results. Also, Curves are proposed and plotted to predict changes in the behavior of atomization parameters. Diesel fuel has less viscosity than Mazut fuel. Diesel fuel has shorter breakup length, wavelength, liquid film thickness, and sature mean diameter than Mazut fuel at the same pressure. Diesel fuel has a larger spray angle and a larger discharge coefficient than Mazut fuel at the same pressure. As the pressure and temperature increase, fuel atomization improves. The viscosity of Mazut fuel is decreased by temperature increase. As the fuel injection pressure and temperature increase, breakup length, wavelength, liquid film thickness, and sature mean diameter decrease; also, spray angle increases.

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“…In addition, the increase of viscosity and back pressure induced the decrease of spray cone angle. 2,[7][8][9] Atomizer structure parameters had a significant effect on spray cone angle. Spray cone angle became larger with the increase of nozzle diameter 10 and swirling groove angle, 11,12 and became smaller with the increase of nozzle length 11,13 and angle of main convergent section.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigations on atomization characteristics of dual-orifice atomizers part I: Optimization method formation

Fan

Liu

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this paper, influences of structure parameters on mass flow and atomization characteristics (spray cone angle, SMD, liquid film fusion and separation) of dual-orifice atomizers were investigated using Fraunhofer diffraction optical instrument and high-speed shadowgraph technique. The main influential structure parameters are obtained by structural parameter sensitivity analysis. Liquid film fusion and separation is an important atomization characteristic lacking of in-depth research. Results of liquid film fusion and separation illustrate that three patterns (separation-fusion-secondary separation) of main stage liquid film and pilot stage liquid film appear with the increase of Δ P. Liquid film fusion makes SMD larger, and there is a delay in liquid film separation when reduce Δ P after liquid film fusion. In addition, mass flow and spray cone angle are key factors which affect liquid film fusion pressure, liquid film secondary separation pressure and distance between two liquid films. The smaller the pilot stage mass flow is, the larger the effect of the main stage on pilot stage spray cone angle will be. Results in this paper could be used to the design and optimization of new dual-orifice atomizers.

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Review on pressure swirl injector in liquid rocket engine

Cited by 74 publications

References 126 publications

Injector and Combustion Chamber Design for a Nitrous Oxide and Ethanol Rocket Engine

Injector and Combustion Chamber Design for a Nitrous Oxide and Ethanol Rocket Engine

Experimental comparison of the spray atomization of heavy and light fuel oil at different temperatures and pressures for pressure-swirl injector

Experimental investigations on atomization characteristics of dual-orifice atomizers part I: Optimization method formation

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