An overview on dry low NOx micromix combustor development for hydrogen-rich gas turbine applications

Funke, H. H.-W.; Beckmann, Nils; Abanteriba, Sylvester

doi:10.1016/j.ijhydene.2019.01.161

Cited by 117 publications

(36 citation statements)

References 13 publications

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“…The high energy per unit mass reduces the total fuel weight, thereby enabling more payload or flight range than jet fuel. However, the benefit of high energy per unit mass is countered by the low density of hydrogen, requiring high storage volume, which could erode aircraft performance relative to jet fuel [6][7][8].…”

Section: Introductionmentioning

confidence: 99%

“…However, unlike with jet fuel, the contrail effect depends on the altitude, and the residence time of water vapor is relatively short [10,11]. LH 2 also has a greater propensity to generate high NOx than jet fuel, due to its higher flame temperature at a given equivalence ratio [7,11]. Another important limitation of LH 2 is cost, which includes production, transporting and storage costs [12,13].…”

Section: Introductionmentioning

confidence: 99%

“…The investigation uses a set of mass and equivalence ratio variations at different temperatures and pressures to carry out exhaust gas analysis on combustion efficiency and stability. Other works on combustion design and mitigation for LH 2 are documented in the references [4,7,11,21,22]. Figure 1 provides the temperature characteristics of LH 2 and kerosene as a function of the equivalence ratio.…”

Section: Introductionmentioning

confidence: 99%

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Thermodynamic Performance and Creep Life Assessment Comparing Hydrogen- and Jet-Fueled Turbofan Aero Engine

et al. 2021

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There is renewed interest in hydrogen as an alternative fuel for aero engines, due to their perceived environmental and performance benefits compared to jet fuel. This paper presents a cycle, thermal performance, energy and creep life assessment of hydrogen compared with jet fuel, using a turbofan aero engine. The turbofan cycle performance was simulated using a code developed by the authors that allows hydrogen and jet fuel to be selected as fuel input. The exergy assessment uses both conservations of energy and mass and the second law of thermodynamics to understand the impact of the fuels on the exergy destruction, exergy efficiency, waste factor ratio, environmental effect factor and sustainability index for a turbofan aero engine. Finally, the study looks at a top-level creep life assessment on the high-pressure turbine hot section influenced by the fuel heating values. This study shows performance (64% reduced fuel flow rate, better SFC) and more extended blade life (15% increase) benefits using liquefied hydrogen fuel, which corresponds with other literary work on the benefits of LH2 over jet fuel. This paper also highlights some drawbacks of hydrogen fuel based on previous research work, and gives recommendations for future work, aimed at maturing the hydrogen fuel concept in aviation.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Thermodynamic Performance and Creep Life Assessment Comparing Hydrogen- and Jet-Fueled Turbofan Aero Engine

et al. 2021

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“…However, conventional mitigation measures are typically impractical or too expensive to implement when large quantities of pressurized nitrogen or steam are not readily available. Therefore, additional technology development is needed for gas-turbine combustion systems that achieve stable (no thermo-acoustic oscillations), clean (low N O x ), and efficient (dilution-free) combustion of fuels with high hydrogen content [5]. Ultimately, this is a key prerequisite to the viable implementation of power generation solutions in pre-combustion Carbon Capture and Storage (CCS) schemes and in large-scale energy storage based on the use of hydrogen as an energy carrier.…”

Section: Introductionmentioning

confidence: 99%

A skeletal mechanism for prediction of ignition delay times and laminar premixed flame velocities of hydrogen-methane mixtures under gas turbine conditions

Jiang

Alamo

Gruber

et al. 2019

International Journal of Hydrogen Energy

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The aim of this study is to eliminate unimportant steps from a detailed chemical-kinetic mechanism in order to identify a skeletal kinetic mechanism that can predict with sufficient accuracy ignition delay times and laminar premixed-flame velocities for H 2 -CH 4 mixtures under conditions of practical interest in gas-turbine applications, which pertain to high pressure, high reactant temperature, and primarily lean-tostoichiometric mixture compositions (although somewhat rich conditions also are considered for completeness). The accuracy of selected detailed chemical-kinetic mechanisms that are suited to represent combustion of hydrogen-methane mixtures in air was evaluated through comparison of computed and measured ignition delay times and laminar flame velocities, and because of its relative simplicity and sufficient accuracy, the San Diego mechanism was selected for the needed chemical-kinetic reduction. Under the pressure and temperature conditions of the mixture composition addressed, thirty nine reversible elementary steps involving eighteen species were found to suffice to describe with acceptable accuracy both the ignition delay time and the laminar burning velocities. The skeletal mechanism is given here, along with discussion of its derivation and characteristics, as well as comparison of its predictions with those of the detailed mechanism and, where possible, with experiment.

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“…However, NO x emissions have significantly increased due to high temperature conditions. Funke et al [14] have worked experimentally and numerically on the optimization of a low NO x combustion chamber of the Micromix gas turbine. The developed method was aimed to be applied to industrial scale gas turbine chambers.…”

Section: Iintroductionmentioning

confidence: 99%

Mono-Blok Tipte Bir Doğal Gaz Yakıcının Sayısal Analizi ve Deneysel

Yılmaz

Uza²

2019

International Journal of Advances in Engineering and Pure Sciences

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Fossil fuels are still one the major sources of the energy production. Fuels, utilized in the power generation, especially in industrial scale applications, are almost hydrocarbons in gaseous, liquid or solid phases. In combustion of gaseous fossil fuels, besides the several other emissions carbon monoxide and nitric oxide which are identified as the main suspects of the environmental pollution are produced.In this study, the flow field and the emission statistics of an industrial scale gas burner were investigated numerically. The burner and the assembled combustion chamber have been modelled using ANSYS-Fluent software. The standards for flue gas emissions of gas burners defined in TSE EN 676:2000 Class-3 have been taken into account. One of the most important emissions of NO x level given in that standard, limited to be less than 80 mg/kWh, has been initially computed for the existing burner and then for the modified burner designs. Both the velocity and temperature fields are calculated and represented in terms of contour plots. The emission results are collected at the exit of the combustion chamber and the chamber wall temperatures have been also computed. The numerical model results were validated with the available experimental measurements obtained from on-site test facilities. ÖzFosil yakıtlar halen enerji üretiminin en önemli ana kaynaklarıdır. Enerji üretiminde, özellikle endüstriyel ölçekte uygulamalarda kullanılan yakıtlar büyük oranda gaz, sıvı veya katı fazlarda bulunan hidrokarbonlardır. Gaz fazındaki fosil yakıtların yanmasında, diğer bazı emisyonların yanı sıra çevre kirliliğinin ana şüpheli olarak nitelendirilen karbon monoksit ve nitrik oksit de üretilmektedir.Bu çalışmada, endüstriyel ölçekte bir gaz yakıcısının akış alanı ve emisyon istatistikleri sayısal olarak incelenmiştir. Yakıcı ve buna bağlı yanma odası ANSYS-Fluent yazılımı kullanılarak modellenmiştir. Gaz yakıcılarının gaz emisyonları için tanımlanan TSE EN 676:2000 Class-3 standardı göz önünde bulundurulmuştur. Bu standartta yer alan en önemli salımlardan birisi olan NO x seviyesi, ki 80 mg/kWh'den az olacak şekilde sınırlandırılmıştır, öncelikle varolan sonrasında ise iyileştirilen yakıcı tasarımları için hesaplanmıştır. Hız ve sıcaklık alan değerleri hesaplanmış ve kontur grafikleri olarak çizdirilmiştir. Salım sonuçları yanma odası çıkışında toplanmıştır ve ayrıca yanma odası duvar sıcaklıkları hesaplanmıştır. Sayısal model sonuçları firma bünyesinde var olan deneysel ölçme imkanları ile elde edilen verilerle doğrulanmıştır.

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An overview on dry low NOx micromix combustor development for hydrogen-rich gas turbine applications

Cited by 117 publications

References 13 publications

Thermodynamic Performance and Creep Life Assessment Comparing Hydrogen- and Jet-Fueled Turbofan Aero Engine

Thermodynamic Performance and Creep Life Assessment Comparing Hydrogen- and Jet-Fueled Turbofan Aero Engine

A skeletal mechanism for prediction of ignition delay times and laminar premixed flame velocities of hydrogen-methane mixtures under gas turbine conditions

Mono-Blok Tipte Bir Doğal Gaz Yakıcının Sayısal Analizi ve Deneysel

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