Spray Combustion Modeling in Lean Direct Injection Combustors, Part II: Multi-Point LDI

Dewanji, D.; Rao, Arvind Gangoli

doi:10.1080/00102202.2014.958476

Cited by 9 publications

(3 citation statements)

References 6 publications

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“…Dewanji and Rao. 14,15 conducted LES simulations of both a single and a nine-element LDI combustor at atmospheric pressure for an inlet air temperature of 776 K and equivalence ratios of 0.41 and 0.7. Formation of vortex structures in the gas phase such as the VBB and the PVC were found to be critical to fuel distribution and consequently the location of the flame front in the combustor.…”

Section: Introductionmentioning

confidence: 99%

Parametric investigation of combustion instabilities in a single-element lean direct injection combustor

Gejji

Huang

Fugger

et al. 2018

International Journal of Spray and Combustion Dynamics

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Self-excited combustion dynamics in a liquid-fueled lean direct injection combustor at high pressure (1 MPa) are described. Studied variables include combustor and air plenum length, inlet air temperature, equivalence ratio, fuel nozzle location, and fuel composition. Measured pressure oscillations were dependent on combustor geometry and ranged from about 1% of mean chamber pressure at low equivalence ratio, up to 20% at high equivalence ratio. In the most unstable cases, strong pressure modes were measured throughout the frequency spectrum including a band around 1.2-1.5 kHz representing the 4th longitudinal mode, and another band around 7 kHz. The oscillation amplitudes have a non-monotonic dependency on air temperature, and are affected by the placement of the fuel nozzle relative to the throat of the subsonic swirling air flow. The parametric survey provides a rich dataset suitable for validating high-fidelity simulations and their subsequent use in analyzing and interpreting the complex combustion dynamics.

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Section: Introductionmentioning

confidence: 99%

Parametric investigation of combustion instabilities in a single-element lean direct injection combustor

Gejji

Huang

Fugger

et al. 2018

International Journal of Spray and Combustion Dynamics

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“…Liu reported the simultaneous presence of both premixed, partially-premixed and non-premixed flames in the burner and confirmed the enhancement of spray particle dispersion hinted by Patel and Menon [115] as a consequence of the PVC. Meanwhile, Davoudzadeh et al [123] and Dewanji and Rao [124,125] also investigated the non-reacting and reacting flow in the single-element [36] and multi-point [60] NASA LDI combustors through U-RANS and LES approaches. On the one hand, the mean velocity components exhibited by Davoudzadeh et al [123] showed some discrepancy with experimental data at the entrance of the combustion chamber due to a poor grid refinement (0.86 million cells).…”

Section: Computational Studies On Ldi Burnersmentioning

confidence: 99%

“…On the one hand, the mean velocity components exhibited by Davoudzadeh et al [123] showed some discrepancy with experimental data at the entrance of the combustion chamber due to a poor grid refinement (0.86 million cells). On the other hand, the simulations of Dewanji and Rao [124,125] captured the unsteady turbulent flow structures at the border of the neighbouring swirlers and evaluated the spray velocity and drop size distribution for several spray models. In this way, they showed how the shear layers emerging from adjacent swirlers in the multi-point LDI configuration played a major role in the spray dispersion and mixing when compared to the single-element LDI burner.…”

Section: Computational Studies On Ldi Burnersmentioning

confidence: 99%

Computational study on the non-reacting flow in Lean Direct Injection gas turbine combustors through Eulerian-Lagrangian Large-Eddy Simulations

Gil¹

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Aeronautical gas turbine engines present the main challenge of increasing the efficiency of the cycle while keeping the pollutant emissions below stringent restrictions. This has led to the design of new injection-combustion strategies working on more risky and problematic operating points such as those close to the lean extinction limit. In this context, the Lean Direct Injection (LDI) concept has emerged as a promising technology to reduce oxides of nitrogen (NO x ) for next-generation aircraft power plants. ResumenEl principal desafío en los motores turbina de gas empleados en aviación reside en aumentar la eficiencia del ciclo termodinámico manteniendo las emisiones contaminantes por debajo de las rigurosas restricciones. Ésto ha conllevado la necesidad de diseñar nuevas estrategias de inyección/combustión que operan en puntos de operación peligrosos por su cercanía al limite inferior de apagado de llama. En este contexto, el concepto Lean Direct Injection (LDI) ha emergido como una tecnología prometedora a la hora de reducir los óxidos de nitrogeno (NO x ) emitidos por las plantas propulsoras de los aviones de nueva generación. ResumEl principal desafiament als motors turbina de gas utilitzats a la aviació resideix en augmentar l'eficiència del cicle termodinàmic mantenint les emissions contaminants per davall de les rigoroses restriccions. Aquest fet comporta la necessitat de dissenyar noves estratègies d'injecció/combustió que radiquen en punts d'operació perillosos per la seva aproximació al límit inferior d'apagat de flama. En aquest context, el concepte Lean Direct Injection (LDI) sorgeix com a eina innovadora a l'hora de reduir els òxids de nitrogen (NO x ) emesos per les plantes propulsores dels avions de nova generació.En els cremadors LDI, el combustible líquid s'injecta en unes proporcions de mescla pobre directament en la càmera de combustió, on es troba un flux d'aire coaxial arremolinat. Aquest flux altament turbulent promou l'atomització de la pel.lícula de combustible líquid i el mesclat l'esprai amb el aire. Al mateix temps també genera una zona de recirculació immediatament aigües avall del sistema d'injecció que incrementa de forma considerable incesante han sido indispensables para mí, y me resulta imposible explicar y agradecer con palabras la importancia que has tenido en la consecución de este logro. Tu manera de ver la vida, de ilusionarte y de ser feliz dándole valor a los pequeños detalles que muchas veces pasamos por alto pero que todos tenemos a nuestro alcance debería estudiarse en las escuelas. Estoy seguro de que de esta manera el mundo sería un lugar mucho mejor. Gracias por enseñarme tanto. Contents Contents i List of Figures v List of Tables xi Nomenclature xiiiA Full set of results for the L9 orthogonal array parametric study on the geometrical features 293 Global Bibliography 301x LIST OF FIGURES 7.7 Liquid spray penetration profiles for the simulations of the L9 array.262 7.8 Evolution of the Swirl Number along the swirler. . . . . . . . . . . 7.9 Dispersion values of some...

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FV-MP model to predict lean blowout limits for multi-point lean direct injection combustors

Sun

Huang

Wang

et al. 2019

Aerospace Science and Technology

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Spray Combustion Modeling in Lean Direct Injection Combustors, Part II: Multi-Point LDI

Cited by 9 publications

References 6 publications

Parametric investigation of combustion instabilities in a single-element lean direct injection combustor

Parametric investigation of combustion instabilities in a single-element lean direct injection combustor

Computational study on the non-reacting flow in Lean Direct Injection gas turbine combustors through Eulerian-Lagrangian Large-Eddy Simulations

FV-MP model to predict lean blowout limits for multi-point lean direct injection combustors

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