Influence of Fuel Characteristics in a Correlation to Predict Lean Blowout of Bluff-Body Stabilized Flames

Huelskamp, Bethany; Kiel, Barry; Gokulakrishnan, P.

doi:10.1115/gt2015-43433

Cited by 8 publications

(4 citation statements)

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“…Figure 7(b)). Huelskamp et al 70 have recently shown for a dataset of bluff-body stabilised prevaporised flames that ignition delay times provide an adequate representation of chemical time scale and correlate well with the equivalence ratio at lean blowout.…”

Section: Discussionmentioning

confidence: 99%

Investigation of differences in lean blowout of liquid single-component fuels in a gas turbine model combustor

Grohmann¹,

Rauch²,

Kathrotia³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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The influence of selected single-component hydrocarbons on lean blowout behaviour of swirl-stabilised spray flames was investigated. Additional information on the spray characteristics was collected by Phase Doppler Anemometry (PDA) and Mie scattering measurements. The measurements were accomplished in a gas turbine model combustor under atmospheric pressure and at two different air preheat temperatures. The combustor featured a dual-swirl geometry and a prefilming airblast atomiser. The combustion chamber provided good optical access and yielded well-defined boundary conditions. Three singlecomponent hydrocarbons were chosen: one short and one long linear alkane (n-hexane and n-dodecane) and one branched alkane (iso-octane). Kerosene Jet A-1 was used as a technical reference. Results show noticeable differences in the lean blowout limits of the various fuels, at comparable flow conditions. By using the results of the measurements, of additional modelling and of an assessment of the fuel properties it was concluded that fuel differences in lean blowout in this combustor can be due to differences in the physical properties as well as in the chemical properties.

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Section: Discussionmentioning

confidence: 99%

Investigation of differences in lean blowout of liquid single-component fuels in a gas turbine model combustor

Grohmann¹,

Rauch²,

Kathrotia³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

show abstract

“…6(b)). Huelskamp et al [56] have recently shown for a dataset of bluff-body stabilized prevaporized flames that ignition delay times provide an adequate representation of the chemical time scale and correlate well with the equivalence ratio at lean blowout.…”

Section: Discussionmentioning

confidence: 99%

Influence of Single-Component Fuels on Gas-Turbine Model Combustor Lean Blowout

Grohmann

Rauch

Kathrotia

et al. 2018

Journal of Propulsion and Power

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The influence of selected single-component hydrocarbons on lean blowout behavior of swirl-stabilized spray flames was investigated. Additional information on the spray characteristics was collected by Phase Doppler Interferometry (PDI) and Mie scattering measurements. The measurements were accomplished in a gas turbine model combustor under atmospheric pressure and at two different air preheat temperatures.The combustor featured a dual-swirl geometry and a prefilming airblast atomizer. The combustion chamber provided good optical access and yielded well-defined boundary conditions. Three single-component hydrocarbons were chosen: one short and one long linear alkane (n-hexane and n-dodecane) and one branched alkane (iso-octane).Kerosene Jet A-1 was used as a reference. Results show noticeable differences in the lean blowout limits of the various fuels, at comparable flow conditions. By using the results of the measurements, of additional modelling and of an assessment of the fuel properties it was concluded that fuel differences in lean blowout in this combustor can be due to differences in the physical properties as well as in the chemical properties. \phi = global equivalence ratio (-) P th = thermal power (W) \rho = density ( \mathrm{ \mathrm{ /\mathrm{ 3 ) Re = Reynolds number (-) \sigma = surface tension ( \mathrm{ /\mathrm{ ) S = geometrical swirl number (-) t e = total evaporation time (s) T = temperature (K) u, v, w = velocities in reference coordinate system ( \mathrm{ /\mathrm{ ) x, y, z = reference coordinate system (m) I. IntroductionProduction pathways for alternative aviation fuels offer the possibility to modify the chemical composition of the final product in order to improve physical and chemical properties for optimized combustion performance. Depending on feedstock (e.g. coal, natural gas or biomass) and process parameters, alternative fuels can contain hydrocarbons of significantly different types and chain lengths [1,2]. However, the influence of the chemical composition of the fuel on combustion performance is not fully understood [3].Four main processes govern the combustion of liquid fuels in gas turbine combustors: atomization, vaporization, turbulent mixing and chemical reaction. These processes happen simultane-

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“…The LBO prediction on gas turbine combustor based on correlation has been suggested by many researchers (Jarymowycz and Mellor, 1986;Xie et al, 2012;Huelskamp et al, 2015;Hu et al, 2015;Lei et al, 2021). Jarymowycz and Mellor (1986) developed a correlation to predict LBO in an annular combustor.…”

Section: Introductionmentioning

confidence: 99%

Prediction of lean blowout performance on variation of combustor inlet area ratio for micro gas turbine combustor

Kirubakaran

Shankar

2021

AEAT

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Purpose This paper aims to predict the effect of combustor inlet area ratio (CIAR) on the lean blowout limit (LBO) of a swirl stabilized can-type micro gas turbine combustor having a thermal capacity of 3 kW. Design/methodology/approach The blowout limits of the combustor were predicted predominantly from numerical simulations by using the average exit gas temperature (AEGT) method. In this method, the blowout limit is determined from characteristics of the average exit gas temperature of the combustion products for varying equivalence. The CIAR value considered in this study ranges from 0.2 to 0.4 and combustor inlet velocities range from 1.70 to 6.80 m/s. Findings The LBO equivalence ratio decreases gradually with an increase in inlet velocity. On the other hand, the LBO equivalence ratio decreases significantly especially at low inlet velocities with a decrease in CIAR. These results were backed by experimental results for a case of CIAR equal to 0.2. Practical implications Gas turbine combustors are vulnerable to operate on lean equivalence ratios at cruise flight to avoid high thermal stresses. A flame blowout is the main issue faced in lean operations. Based on literature and studies, the combustor lean blowout performance significantly depends on the primary zone mass flow rate. By incorporating variable area snout in the combustor will alter the primary zone mass flow rates by which the combustor will experience extended lean blowout limit characteristics. Originality/value This is a first effort to predict the lean blowout performance on the variation of combustor inlet area ratio on gas turbine combustor. This would help to extend the flame stability region for the gas turbine combustor.

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Influence of Fuel Characteristics in a Correlation to Predict Lean Blowout of Bluff-Body Stabilized Flames

Cited by 8 publications

References 0 publications

Investigation of differences in lean blowout of liquid single-component fuels in a gas turbine model combustor

Investigation of differences in lean blowout of liquid single-component fuels in a gas turbine model combustor

Influence of Single-Component Fuels on Gas-Turbine Model Combustor Lean Blowout

Prediction of lean blowout performance on variation of combustor inlet area ratio for micro gas turbine combustor

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