19th Aerospace Sciences Meeting 1981
DOI: 10.2514/6.1981-42
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On the structure of turbulence and a generalized eddy dissipation concept for chemical reaction in turbulent flow

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Cited by 505 publications
(330 citation statements)
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“…Details on the EDC model can be found in ref. [12] and [26], while examples of its use to model complex situations where non-premixed and premixed conditions co-exist are presented by Albrecht et al, [27] and Tang et al [28].…”
Section: Accepted Manuscriptmentioning
confidence: 99%
“…Details on the EDC model can be found in ref. [12] and [26], while examples of its use to model complex situations where non-premixed and premixed conditions co-exist are presented by Albrecht et al, [27] and Tang et al [28].…”
Section: Accepted Manuscriptmentioning
confidence: 99%
“…Mixing-based (Bray & Moss 1977;Magnussen 1981), or flamelet (Weller et al 1998;Pitsch 2006), models are unsuitable for this devoid of modifications, and we thus focus on finite-rate chemistry models (Magnussen 1981;Karlsson 1995;Colin et al 2000;Givi 2006;Porumbel & Menon 2006). Here, we use the eddy dissipation concept (EDC) model (Magnussen 1981) …”
Section: Large Eddy Simulation Combustion Modellingmentioning
confidence: 99%
“…Fureby (submitted) made an attempt to examine whether LES could be used to shed some light on annular multi-burner combustor dynamics using a model annular combustor derived from the General Electric (GE) LM600 laboratory combustor (Hura et al 1998), used in several swirl combustor studies (Kim et al 1999;Grinstein & Fureby 2004). This model annular combustor consists of 18 burners characterized by velocity and fuel mass-fraction profiles (Magnussen (1981) and adapted to LES as described above), TFM model (Colin et al 2000) and G-equation model ( Nogenmyr et al 2008). provided by GE (Hura et al 1998), and representative of the DACRS burner, used in the single burner laboratory experiments (Hura et al 1998), which will be used as reference. According to table 1, we present results for both CH 4 and n-C 10 H 22 combustion at fZ0.56, a combustor pressure of p 0 Z6.18!10 5 Pa, a reactant temperature of T 0 Z644 K and a centreline axial jet inflow velocity of v 0 Z110 m s K1 .…”
Section: Gas Turbine Combustor Applicationmentioning
confidence: 99%
“…(14) 본 모델은 연소반응이 대부분 난류 혼합에 의해 영향을 받는다고 가정을 하고, 화학반응에 따른 영향은 고려하지 않는다 이때 . , 휘발분의 연소반응은 다음과 같이 일반화된 연료 의 단 연소반응으로 근사 되었다 2 .…”
Section: Rate Parameters Numeric Valuesunclassified