Liquid-Propellant Rocket Engine Injector Dynamics

Bazarov, Vladimir G.; Yang, Vigor

doi:10.2514/2.5343

Cited by 167 publications

(74 citation statements)

References 2 publications

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“…The swirling motion of the injected fluid can improve flame stability by producing toroidal recirculation zones and reduce combustion length by inducing high rates of entrainment of the ambient fluid and fast mixing [4]. Injectors have strong effects on the stability characteristics of the combustion system because all feedback coupling of the combustion chamber with other engine components takes place through the injection process [5,6]. The situation becomes more complex when the engine operates at pressures higher than the critical pressures of the propellants [7].…”

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confidence: 99%

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Wang

Yang

2017

Journal of Propulsion and Power

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The mixing and combustion characteristics of liquid-oxygen/kerosene bi-swirl injectors are investigated under the supercritical conditions typical of contemporary rocket engines. The basis of the study is a large-eddy simulation technique combined with a unified treatment of real-fluid thermodynamics. The turbulence/chemistry interaction is treated using a laminar flamelet library approach. Emphasis is placed on the near-field flow and flame development downstream of the inner swirler. The flame is found to be stabilized by two counter-rotating vortices in the wake region of the liquid-oxygen post, which is covered by the kerosene-rich mixture. The width of the kerosene annulus is found to significantly affect the injector behavior. A wider annulus induces a larger spreading angle of the liquidoxygen stream, which intercepts the kerosene stream in a more efficient way. Increasing the annulus width, however, imposes a wake region in a broader zone. The resultant flame becomes relatively unstable if the flame thickness is larger than the liquid-oxygen post thickness. Variation of the kerosene annulus width has a negligible effect on the dominant frequency of the pressure fluctuation, but it changes the amplitude of fluctuation.

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confidence: 99%

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Wang

Yang

2017

Journal of Propulsion and Power

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“…This problem is important, since it can lead to a practical solution to the multiinjector system including crucial details of injector dynamics (see refs. [3,4,19] for the importance of including injector dynamics in this calculation; note that due to affordability for the most part, as in ref [23], the computational domain is truncated at this boundary). We consider the following finite volume expression in a cell that has a boundary interface being modeled by RBM, sketched in figure [13]:…”

Section: A 3d Flow With Hydrodynamic Instabilitymentioning

confidence: 99%

Model Reduction Opportunities in Detailed Simulations of Combustion Dynamics

Munipalli

Zhu

Menon

et al. 2014

52nd Aerospace Sciences Meeting

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Rocket and gas turbine combustion dynamics involves a confluence of diverse physics and interaction across a number of system components. Any comprehensive, self-consistent numerical model is burdened by a very large computational mesh, stiff unsteady processes which limit the permissible time step, and the need to perform tedious, repeated calculations for a broad parametric range. Predictive CFD models rely on very large scale simulations and advanced hardware. Reduced Basis Methods (RBM) have grown in usage during the past decade, as promising new techniques in making large simulations more accessible. These methods create models with far fewer unknown quantities than the original system, by generating "proper" fundamental solutions and their Galerkin projections, while guaranteeing accuracy and computational efficiency. RBMs seek to reproduce full CFD solutions, rather than solutions to a simplified or linearized set of equations. We present here some recent work in this area, focusing on approaches to model large scale combustor systems. The maturation of methods leading to LES-based turbulent combustion modeling is discussed, and model reduction goals and strategies are explored from the perspective of applicability in real life problems in both gas turbine, as well as rocket engines.

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“…. defined as: (12) and the corresponding value of the liquid vortex radius rm: (13) At the edge of the opened vortex chamber, the centrifugal pressure of the rotating liquid film will be transformed to axial acceleration of the liquid flow and axial velocity will be increased: (14) The radius of liquid film will "also be increased according to the mass conservation equation:…”

Section: -Rpmentioning

confidence: 99%

Main Chamber Injectors for Advanced Hydrocarbon Booster Engines

Long

Bazarov

Anderson

2003

39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Achieving the highest possible specific impulse has long been a key driver for space launch systems. Recently, more importance has been placed on the need for increased reliability and streamlined launch operations. These general factors along. with more specific mission requirements have provIded a new focus that is centered on the oxidizer rich staged combustion (ORSC) cycle. Despite a history of use in Russia that extends back to the 1960's, a proven design methodology for ORSC cycle. engines does not exist in the West. This lack of design expertise extends to the main chamber injector, a critical. subcomponent that largely determines the engine performance and main chamber life .. The goals ~f. the effort described here are to establIsh an empmcal knowledge base to provide a fundamental understanding of main chamber injectors and for verification of an injector design methodology for the ORSC cycle. The design of a "baseline" injector element, derived from information on Russian engines in the open literature, is presented. The baseline injector comprises a gaseous oxidizer core flow and an annular swirling fuel flow. Sets of equations describing the steady-state and the dynamic characteristics of the injector are presented; these equations, which form the basis of the design analysis methodology, will be verified in tests later this year. On~going cold flow studies, using nitrogen and water as simulants, are described which indicate highly atomized and symmetric sprays.

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Liquid-Propellant Rocket Engine Injector Dynamics

Cited by 167 publications

References 2 publications

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Supercritical Mixing and Combustion of Liquid-Oxygen/ Kerosene Bi-Swirl Injectors

Model Reduction Opportunities in Detailed Simulations of Combustion Dynamics

Main Chamber Injectors for Advanced Hydrocarbon Booster Engines

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