Experimental investigations of coaxial injectors in a laboratory-scale rocket combustor

Cai, Guobiao; Yang, Zhigang; Yu, Nanjia

doi:10.1016/j.ast.2016.10.013

Cited by 8 publications

(3 citation statements)

References 27 publications

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“…Because of the importance in liquid rocket engine, many experimental and numerical researches have been done on injectors in recent years [8][9][10]. The shear coaxial injector combines simple structure with high reliability, while the swirl coaxial injector has better droplet mixing and atomization ability, and they are suitable for gas-liquid injector and liquid-liquid injector in rocket engine [2,11].…”

Section: Introductionmentioning

confidence: 99%

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Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Jin

et al. 2021

International Journal of Aerospace Engineering

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The LOX/methane engine has an admirable performance under a supercritical state. However, the properties of methane change drastically with varying injection temperature. Because the injector can greatly affect the atomization and combustion, this study performed a three-dimensional numerical simulation of atomization, combustion, and heat transfer in a subscale LOX/methane engine to evaluate the effect of the main fluid parameters with different methane injection temperatures and different injectors on atomization performance and combustion performance. The results show that the larger propellant momentum ratio and Weber number can improve the heat flux and combustion stability in shear coaxial injector, while the influence in swirl coaxial injector is relatively small. Moreover, in shear coaxial injector and in swirl coaxial injector, the larger propellant momentum ratio and Weber number can reduce the droplet size, enhance atomization performance, and improve the combustion efficiency. The numerical model provides an economical method to evaluate the main fluid parameters and proposes new design principles of injectors in LOX/methane engine.

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Section: Introductionmentioning

confidence: 99%

“…In axial direction, some cross sections with an interval of dx = 1 mm are taken 13 International Journal of Aerospace Engineering and divided into one circular and several annular multiple subregions with same radial width of dr = mm. The SMD of each subregion is computed by Equation (11).…”

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confidence: 99%

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Jin

et al. 2021

International Journal of Aerospace Engineering

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“…Using numerical simulation, Li et al [14] found that a H 2 O 2 /kerosene coaxial shear injector causes the combustion chamber to be divided into the following zones: rapid high-temperature pyrolysis zone, oxidization zone and equilibrium flow zone. In a previous experiment, non-intrusive optical diagnostics was employed to study the combustion behaviors and flame stabilization of a coaxial swirl injector and a coaxial shear injector, including gaseous hydrogen/gaseous oxygen (GO 2 /GH 2 ) and gaseous methane/gaseous oxygen (GCH 4 /GO 2 ) [15,16]. The method may also be employed in H 2 O 2 /kerosene bipropellant.…”

Section: Introductionmentioning

confidence: 99%

The design and main performance of a hydrogen peroxide/kerosene coaxial-swirl injector in a lab-scale rocket engine

Liang

Wei

et al. 2017

Aerospace Science and Technology

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Future space missions are considering the use of green space propulsion, and H 2 O 2 /kerosene bipropellant is one of effective alternatives for rocket propellant. In addition, for a 100-N-class thruster of H 2 O 2 /kerosene, it is important to design the proper injector. In this study, according to different values of the geometric constant A which determines the initial swirl intensity of the injected fluid, five coaxial swirl injectors are designed to check the thruster's performance. From the test and experiment results, it is found that with an increase in A, coaxial-swirl injectors can aid in the mixing of oxidant and fuel but increase the average temperature of faceplate, thus significantly reducing the flame length. However, a large or small value of A is not conductive to improve the combustion efficiency. In addition, the pressure oscillation (P ins ) inside of the chamber gradually becomes intense. Among all cases, Case 3 ( A = 3.0), exhibits optimal performance for a 100-N-class H 2 O 2 /kerosene thruster.

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An experimental and modelling study of heat loads on a subscale methane rocket motor

Liu²,

Silvestri

et al. 2019

Acta Astronautica

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Experimental investigations of coaxial injectors in a laboratory-scale rocket combustor

Cited by 8 publications

References 27 publications

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

The design and main performance of a hydrogen peroxide/kerosene coaxial-swirl injector in a lab-scale rocket engine

An experimental and modelling study of heat loads on a subscale methane rocket motor

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