Modeling and Analytical Solution of Near-Field Entrainment in Suddenly Started Turbulent Jets

Feyz, Mohammad Ebrahim; Nalim, M. Razi; Hasti, Veeraraghava Raju; Gore, J. P.

doi:10.2514/1.j057612

Cited by 13 publications

(2 citation statements)

References 29 publications

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“…Numerical simulations of TJI have been limited in RANS (Xu et al 2017(Xu et al , 2018Chinnathambi et al 2015;Gentz et al 2015b;Thelen et al 2015;Thelen and Toulson 2017;Wang et al 2018), Large Eddy Simulations (LES) (Validi et al 2017;Feyz et al 2019a;Malé et al 2019) and more recently Direct Numerical Simulations (DNS) (Validi and Jaberi 2018;Qin et al 2018;Benekos et al 2020). Although some preliminary lower-order modelling efforts were focused on capturing the mass entrainment rate and temporal evolution of the temperature profile in suddenly started jets (Feyz et al 2019b(Feyz et al , 2018, with the scope of extending the model to ignition delay prediction, a formally derived and validated low-order ignition model for TJI is missing from the existing literature. In addition, while valuable insights were obtained in canonical configurations, they did not enable quantified predictions in applications of TJI.…”

Section: Introductionmentioning

confidence: 99%

A Novel One- and Zero-Dimensional Model for Turbulent Jet Ignition

Bardis

Kyrtatos²,

Barro

et al. 2021

Flow Turbulence Combust

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Turbulent jet ignition (TJI) is a promising combustion technology for burning highly diluted air-fuel mixtures. Computationally efficient models to assess the effect of the operating conditions and design parameters on the ignition propensity and timing are of paramount importance for the development of combustion systems employing TJI. To this end, a one-dimensional (1-D) jet model, which is based on the solution of the section integrated mass and momentum conservation equations, is derived in the present study. The model is extended with two additional transport equations for the turbulence intensity and the ignition precursor/tracer, that marks the ignition event. One-dimensional transient flamelet calculations are performed to generate tables for the ignition precursor source term that account for the turbulence and chemistry interaction. Further simplification of the model is carried out to obtain a novel penetration correlation and a computationally inexpensive Lagrangian ignition model. The extended jet model is hierarchically validated using available literature data for non-reactive and reactive jets, as well as experiments conducted in a state-of-the-art optically accessible prechamber. The derived model is able to reproduce both flow-related quantities (velocity and turbulence profiles, jet penetration) and the ignition delay time under different variations. This study also illustrates how numerical simulations in canonical configurations (one-dimensional flamelet) can be used in practical applications of TJI.

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Section: Introductionmentioning

confidence: 99%

A Novel One- and Zero-Dimensional Model for Turbulent Jet Ignition

Bardis

Kyrtatos²,

Barro

et al. 2021

Flow Turbulence Combust

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“…Hasti and Ranjan 18 used LES with autonomous meshing and AMR to examine the flame structure during a self-sustained longitudinal combustion instability in a high-pressure shear-coaxial single element combustor. Feyz et al [19][20][21][22] reported LES using autonomous meshing and AMR for the suddenly started transient non-reacting and reacting turbulent jets with different Reynolds numbers. The authors demonstrated the meshing approach for successfully capturing the turbulent shear layer dynamics during the hot jet ignition processes.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulations and analysis of the turbulent flow field in a practical gas turbine engine combustor

Hasti

Kundu

Som

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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The turbulent flow field in a practical gas turbine combustor is very complex because of the interactions between various flows resulting from components like multiple types of swirlers, dilution holes, and liner effusion cooling holes. Numerical simulations of flows in such complex combustor configurations are challenging. The challenges result from (a) the complexities of the interfaces between multiple three-dimensional shear layers, (b) the need for proper treatment of a large number of tiny effusion holes with multiple angles, and (c) the requirements for fast turnaround times in support of engineering design optimization. Both the Reynolds averaged Navier–Stokes simulation (RANS) and the large eddy simulation (LES) for the practical combustor geometry are considered. An autonomous meshing using the cut-cell Cartesian method and adaptive mesh refinement (AMR) is demonstrated for the first time to simulate the flow in a practical combustor geometry. The numerical studies include a set of computations of flows under a prescribed pressure drop across the passage of interest and another set of computations with all passages open with a specified total flow rate at the plenum inlet and the pressure at the exit. For both sets, the results of the RANS and the LES flow computations agree with each other and with the corresponding measurements. The results from the high-resolution LES simulations are utilized to gain fundamental insights into the complex turbulent flow field by examining the profiles of the velocity, the vorticity, and the turbulent kinetic energy. The dynamics of the turbulent structures are well captured in the results of the LES simulations.

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High-fidelity numerical simulation of longitudinal thermoacoustic instability in a high-pressure subscale rocket combustor

Hasti,

Ranjan

2024

Aerospace Science and Technology

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Modeling and Analytical Solution of Near-Field Entrainment in Suddenly Started Turbulent Jets

Cited by 13 publications

References 29 publications

A Novel One- and Zero-Dimensional Model for Turbulent Jet Ignition

A Novel One- and Zero-Dimensional Model for Turbulent Jet Ignition

Numerical simulations and analysis of the turbulent flow field in a practical gas turbine engine combustor

High-fidelity numerical simulation of longitudinal thermoacoustic instability in a high-pressure subscale rocket combustor

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