Investigation of Novel Configuration of Hydrogen Micromix Combustor for Low NOx Emission

Lei, Huanrong; Khandelwal, Bhupendra

doi:10.2514/6.2020-1933

Cited by 4 publications

(4 citation statements)

References 10 publications

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“…Finally, and still related with hydrogen injection methods, Lei and Khandelwal [39] proposed ways in their studies to reduce the combustion temperature in the chamber to reduce the NOx emissions. For this purpose, six cases of injection method and injector position effect were simulated to understand the combustion performance.…”

Section: Bibliographic Reviewmentioning

confidence: 99%

“…Several methods of gas injection employed in modern low-emission combustors are also described by Lefebvre and Ballal [41]. Some other studies about the development and comparison of prototypes of gaseous fuel injectors to employ in modern and future combustors with the aim of reducing even more the pollutant emissions are presented in the works of J. Ziemann et al [37], C. J. Marek et al [38], Lei and Khandelwal [39] and Reid Smith et al [24]. The most relevant examples of gaseous fuel injectors presented in these works are shown in Appendix I.…”

Section: Gaseous Fuel Injectionmentioning

confidence: 99%

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CFD Analysis of the Combustion of Hydrogen Fuel on a CFM56-3 Combustor

Domingues

Brójo

Oliveira

2022

Volume 3: Advanced Materials: Design, Processing, Characterization and Applications; Advances in Aerospace Technology

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In the present work is made an overview of the use of hydrogen in aviation, the modifications needed to convert a conventional gas turbine to use hydrogen and a CFD simulation of an existent gas turbine burning hydrogen. The CFD simulation was done in a CFM56-3 combustor burning Jet A (as a reference standard) and hydrogen, with the intention of evaluate the viability of conversion of existent gas turbines to hydrogen, in a combustion point of view, by analyzing the emissions through ICAO’s LTO cycle while burning this fuel. ANSYS Fluent 2020R2 was the software used to perform the numerical study. The RSM was the viscous model used. Only the NOx emissions were assessed as pollutant once the hydrogen combustion products are reduced to water vapor and NOx. These emissions were evaluated through a detailed mechanism and the NOx model available on ANSYS to get a better concordance with the ICAO’s values. During this study, several sensibility studies were carried out for hydrogen burn, for instance, the analysis of the air flow with/without swirl in the primary zone and different inlet pressure and temperature for fuel.

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Section: Bibliographic Reviewmentioning

confidence: 99%

Section: Gaseous Fuel Injectionmentioning

confidence: 99%

CFD Analysis of the Combustion of Hydrogen Fuel on a CFM56-3 Combustor

Domingues

Brójo

Oliveira

2022

Volume 3: Advanced Materials: Design, Processing, Characterization and Applications; Advances in Aerospace Technology

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“…Table 6 summarizes the exergy assessment, showing exergy efficiency of 24.1% and 25.4%, respectively. The turbofan engine's exergy efficiency is calculated from the ratio of the thrust exergy to the total exergy input, represented by Equation (19). Table 7 shows the exergy destruction factor, environmental effect factor and sustainability index.…”

Section: Exergy Estimationmentioning

confidence: 99%

“…Six cases of injection method and injector position effect were simulated to understand the combustion performance. Their result showed that the angled air inlet increased the airflow rotation, which improved the mixing intensity of hydrogen and air and reduced the chamber's peak temperature [19]. Robinson et al [20] performed a detailed study on the design and testing of a micromix combustor with recuperative wall cooling.…”

Section: Introductionmentioning

confidence: 99%

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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