Готові списки джерел за темами / Aero-engine combustors

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Добірка наукової літератури з теми "Aero-engine combustors"

Автор: Grafiati
Опубліковано: 10 березня 2023

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Статті в журналах з теми "Aero-engine combustors"

1

Şöhret, Yasin, and T. Hikmet Karakoc. "Exergy indicators of a low-emission aero-engine combustor." Aircraft Engineering and Aerospace Technology 90, no. 2 (2018): 344–50. http://dx.doi.org/10.1108/aeat-03-2016-0045.

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Анотація:
Purpose It is essential to develop more environment-friendly energy systems to prevent climate change and minimize environmental impact. Within this scope, many studies are performed on performance and environmental assessments of many types of energy systems. This paper, different from previous studies, aims to prove exergy performance of a low-emission combustor of an aero-engine. Design/methodology/approach It is a well-known fact that, with respect to previous exergy analysis, highest exergy destruction occurs in the combustor component of the engine. For this reason, it is required to eva
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2

Li, J., X. Sun, Y. Liu, and V. Sethi. "Preliminary aerodynamic design methodology for aero engine lean direct injection combustors." Aeronautical Journal 121, no. 1242 (2017): 1087–108. http://dx.doi.org/10.1017/aer.2017.47.

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ABSTRACTThe Lean Direct Injection (LDI) combustor is one of the low-emissions combustors with great potential in aero-engine applications, especially those with high overall pressure ratio. A preliminary design tool providing basic combustor sizing information and qualitative assessment of performance and emission characteristics of the LDI combustor within a short period of time will be of great value to designers. In this research, the methodology of preliminary aerodynamic design for a second-generation LDI (LDI-2) combustor was explored. A computer code was developed based on this method c
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3

Marudhappan, Raja, Chandrasekhar Udayagiri, and Koni Hemachandra Reddy. "Combustion chamber design and reaction modeling for aero turbo-shaft engine." Aircraft Engineering and Aerospace Technology 91, no. 1 (2018): 94–111. http://dx.doi.org/10.1108/aeat-10-2017-0217.

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Purpose The purpose of this paper is to formulate a structured approach to design an annular diffusion flame combustion chamber for use in the development of a 1,400 kW range aero turbo shaft engine. The purpose is extended to perform numerical combustion modeling by solving transient Favre Averaged Navier Stokes equations using realizable two equation k-e turbulence model and Discrete Ordinate radiation model. The presumed shape β-Probability Density Function (β-PDF) is used for turbulence chemistry interaction. The experiments are conducted on the real engine to validate the combustion chamb
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4

ZIEMANN, J. "Low-NOx combustors for hydrogen fueled aero engine." International Journal of Hydrogen Energy 23, no. 4 (1998): 281–88. http://dx.doi.org/10.1016/s0360-3199(97)00054-2.

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5

Bake, Friedrich, Ulf Michel, and Ingo Roehle. "Investigation of Entropy Noise in Aero-Engine Combustors." Journal of Engineering for Gas Turbines and Power 129, no. 2 (2006): 370–76. http://dx.doi.org/10.1115/1.2364193.

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Анотація:
Strong evidence is presented that entropy noise is the major source of external noise in aero-engine combustion. Entropy noise is generated in the outlet nozzles of combustors. Low-frequency entropy noise, which was predicted earlier in theory and numerical simulations, was successfully detected in a generic aero-engine combustion chamber. It is shown that entropy noise dominates even in the case of thermo-acoustic resonances. In addition to this, a different noise generating mechanism was discovered that is presumably of even higher relevance to jet engines: There is strong evidence of broad
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6

Klose, G., R. Schmehl, R. Meier, et al. "Evaluation of Advanced Two-Phase Flow and Combustion Models for Predicting Low Emission Combustors." Journal of Engineering for Gas Turbines and Power 123, no. 4 (2000): 817–23. http://dx.doi.org/10.1115/1.1377010.

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Анотація:
The development of low-emission aero-engine combustors strongly depends on the availability of accurate and efficient numerical models. The prediction of the interaction between two-phase flow and chemical combustion is one of the major objectives of the simulation of combustor flows. In this paper, predictions of a swirl stabilized model combustor are compared to experimental data. The computational method is based on an Eulerian two-phase model in conjunction with an eddy dissipation (ED) and a presumed-shape-PDF (JPDF) combustion model. The combination of an Eulerian two-phase model with a
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7

Zhu, M., A. P. Dowling, and K. N. C. Bray. "Self-Excited Oscillations in Combustors With Spray Atomizers." Journal of Engineering for Gas Turbines and Power 123, no. 4 (2000): 779–86. http://dx.doi.org/10.1115/1.1376717.

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Combustors with fuel-spray atomizers are susceptible to a low-frequency oscillation, particularly at idle and sub-idle conditions. For aero-engine combustors, the frequency of this oscillation is typically in the range 50–120 Hz and is commonly called “rumble.” In the current work, computational fluid dynamics (CFD) is used to simulate this self-excited oscillation. The combustion model uses Monte Carlo techniques to give simultaneous solutions of the Williams’ spray equation together with the equations of turbulent reactive flow. The unsteady combustion is calculated by the laminar flamelet p
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8

Corsini, A., F. Rispoli, and T. E. Tezduyar. "Stabilized finite element computation of NOx emission in aero-engine combustors." International Journal for Numerical Methods in Fluids 65, no. 1-3 (2010): 254–70. http://dx.doi.org/10.1002/fld.2451.

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9

Tietz, S., and T. Behrendt. "Development and application of a pre-design tool for aero-engine combustors." CEAS Aeronautical Journal 2, no. 1-4 (2011): 111–23. http://dx.doi.org/10.1007/s13272-011-0012-x.

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Hu, Bin, Yong Huang, Fang Wang, and Fa Xie. "CFD predictions of LBO limits for aero-engine combustors using fuel iterative approximation." Chinese Journal of Aeronautics 26, no. 1 (2013): 74–84. http://dx.doi.org/10.1016/j.cja.2012.12.014.

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Дисертації з теми "Aero-engine combustors"

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Vakil, Sachin Suresh. "Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aero-Engine." Thesis, Virginia Tech, 2002. http://hdl.handle.net/10919/36324.

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<p>The highly competitive gas turbine industry has been motivated by consumer demands for higher power-to-weight ratios, increased thermal efficiencies, and reliability while maintaining affordability. In its continual quest, the industry must continually try to raise the turbine inlet temperature, which according to the well-known Brayton cycle is key to higher engine efficiencies. The desire for increased turbine inlet temperatures creates an extremely harsh environment for the combustor liner in addition to the components downstream of the combustor. Shear layers between the dilution jet
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2

Jaegle, Félix. "LARGE EDDY SIMULATION OF EVAPORATING SPRAYS IN COMPLEX GEOMETRIES USING EULERIAN AND LAGRANGIAN METHODS." Phd thesis, Institut National Polytechnique de Toulouse - INPT, 2009. http://tel.archives-ouvertes.fr/tel-00452501.

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Анотація:
Dû aux efforts apportés à la réduction des émissions de NOx dans des chambres de combustion aéronautiques il y a une tendance récente vers des systèmes à combustion pauvre. Cela résulte dans l'apparition de nouveaux types d'injecteur qui sont caractérisés par une complexité géométrique accrue et par des nouvelles stratégies pour l'injection du carburant liquide, comme des systèmes multi-point. Les deux éléments créent des exigences supplémentaires pour des outils de simulation numériques. La simulation à grandes échelles (SGE ou LES en anglais) est aujourd'hui considérée comme la méthode la pl
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3

Elmi, Carlo Alberto. "Design system integration for multi-objective optimization of aero engine combustors." Doctoral thesis, 2022. http://hdl.handle.net/2158/1276939.

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Анотація:
The transformation towards a climate-neutral civil aviation is providing significant business opportunities to the aero engine market players. To meet this target and keep competitiveness, however, groundbreaking solutions must be introduced at the product’s level in the shortest possible time. Industry lead-ers are increasingly embracing lean and digital approaches for this purpose, by applying these concepts at all company’s levels. Considerable room for im-provements can be identified in the development of complex components as, for instance, the combustor. Due to the complexity of phenomen
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PICCHI, ALESSIO. "Experimental Investigations of Effusion Cooling Systems for Lean Burn Aero-Engine Combustors." Doctoral thesis, 2014. http://hdl.handle.net/2158/857503.

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Анотація:
Legislation limits concerning polluting emissions, for civil aircraft engines, are expected to become even more stringent in the future. To meet these targets, especially in terms of NOx, it is required to maintain the temperature in the combustion zone as low as possible. Lean burn swirl stabilized combustors represent the key technology to reduce NOx emissions. The high amount of air admitted through a lean-burn injection system is characterized by very complex flow structures such as recirculations, vortex breakdown and processing vortex core, that may deeply interact in the near wall regio
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5

Palanti, Lorenzo. "On the modelling of liquid fuel ignition and atomization in aero engine combustors." Doctoral thesis, 2021. http://hdl.handle.net/2158/1234766.

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Анотація:
A fast and reliable relight of aero engines burners is one of the most critical points to ensure aircraft safety. The so-called altitude relight is the process that allows the combustor to be re-ignited after a flame-out during flight. Several expensive tests must be carried out to obtain the required certifications, which makes important to fully understand the problem of the flame onset. To speedup the design process, Computational Fluid Dynamics established as valid alternative to the experiments to investigate the complex phenomena involved in the ignition process. In this work, a fully re
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6

Langone, Leonardo. "Numerical modelling of partially premixed low-swirl flames for aero-engine applications." Doctoral thesis, 2022. http://hdl.handle.net/2158/1277139.

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Анотація:
The development of innovative aero-engine combustors has been devoted to drastically reducing pollutants emissions and improving engine performances in recent years. These aspects are not only crucial to meet the severe regulations imposed by ICAO-CAEP, but also to enable potential new engine architectures. Especially considering Nitrogen Oxidizes (NOx) emissions, the most promising concept carried out so far is represented by Lean burn combustors, which however introduce several challenges in terms of ame stability. A possible solution to this problem is the novel burner concept proposed in
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GIUSTI, ANDREA. "Development of numerical tools for the analysis of advanced airblast injection systems for lean burn aero-engine combustors." Doctoral thesis, 2014. http://hdl.handle.net/2158/867029.

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Анотація:
The liquid fuel preparation has a strong impact on the combustion process and consequently on pollutant emissions. However, currently there are no validated and computational affordable methods available to predict the spray breakup process and to reliably compute the spray distribution generated after primary breakup. This research activity, carried out within the framework of the European project FIRST (Fuel Injector Research for Sustainable Transport), is aimed at developing reliable tools to be used in the industrial design process able to describe the processes involved in liquid fuel pre
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8

MAZZEI, LORENZO. "A 3D coupled approach for the thermal design of aero-engine combustor liners." Doctoral thesis, 2015. http://hdl.handle.net/2158/993808.

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Анотація:
The recent limitations imposed by ICAO-CAEP towards a drastic reduction of NOx emissions is driving the development of modern aeroengines towards the implementation of lean burn concept. The increased amount of air dedicated to the combustion process (up to 70%) involves several technological issues, including a signicant reduction of coolant available for the thermal management of combustor liners. This, from a design perspective, involves the continuous research for effective cooling schemes, such as effusion cooling, and the necessity of more accurate methodologies for the estimation of met
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INSINNA, MASSIMILIANO. "Investigation of the Aero-Thermal Aspects of Combustor/Turbine Interaction in Gas Turbines." Doctoral thesis, 2015. http://hdl.handle.net/2158/986426.

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Bacci, Tommaso. "Experimental investigation on a high pressure NGV cascade in the presence of a representative lean burn aero-engine combustor outflow." Doctoral thesis, 2018. http://hdl.handle.net/2158/1128260.

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Анотація:
Experimental Investigation of the effects of a modern lean burn combustor outflow on the performance of a film-cooled NGV cascade. Evaluation of chamber flow field, NGV inlet/outlet aerothermal field, turbulence decay and adiabatic effectiveness on the NGV profiles
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Книги з теми "Aero-engine combustors"

1

Panigrahi, Shashi Kanta, and Niranjan Sarangi. Aero Engine Combustor Casing. Taylor & Francis Group, 2020.

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2

Sarangi, Niranjan, and Sashi Kanta Panigrahi. Aero Engine Combustor Casing: Experimental Design and Fatigue Studies. Taylor & Francis Group, 2017.

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3

Sarangi, Niranjan, and Sashi Kanta Panigrahi. Aero Engine Combustor Casing: Experimental Design and Fatigue Studies. Taylor & Francis Group, 2017.

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4

Sarangi, Niranjan, and Sashi Kanta Panigrahi. Aero Engine Combustor Casing: Experimental Design and Fatigue Studies. Taylor & Francis Group, 2017.

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5

Sarangi, Niranjan, and Sashi Kanta Panigrahi. Aero Engine Combustor Casing: Experimental Design and Fatigue Studies. Taylor & Francis Group, 2017.

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6

Aero Engine Combustor Casing: Experimental Design and Fatigue Studies. Taylor & Francis Group, 2017.

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Частини книг з теми "Aero-engine combustors"

1

"Introduction." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-1.

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"References." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-10.

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"Index." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-11.

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4

"Fatigue Design Philosophy of an Aero Engine Combustor Casing." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-2.

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"Development of Test Facility and Test Setup." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-3.

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"Manufacturing of an Aero Engine Combustor Casing, the Experimental Evaluation of Its Fatigue Life, and Correlation with Numerical Results." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-4.

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7

"Reassessment of Fatigue Life of the Modified Combustor Casing." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-5.

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8

"Safety Test on Modified Combustor Casing." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-6.

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9

"Effect of Fatigue on the Proof Strength of an Aero Engine Combustor Casing*." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-7.

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10

"Conclusions." In Aero Engine Combustor Casing. CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-8.

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Тези доповідей конференцій з теми "Aero-engine combustors"

1

Bake, Friedrich, Ulf Michel, and Ingo Roehle. "Investigation of Entropy Noise in Aero-Engine Combustors." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90093.

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Анотація:
Strong evidence is presented that entropy noise is the major source of external noise in aero-engine combustion. Entropy noise is generated in the outlet nozzles of combustors. Low frequency entropy noise — which was predicted earlier in theory and numerical simulations — was successfully detected in a generic aero-engine combustion chamber. It is shown that entropy noise dominates even in the case of thermo-acoustic resonances. In addition to this, a different noise generating mechanism was discovered that is presumably of even higher relevance to jet engines: There is strong evidence of broa
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2

Zelina, J., D. T. Shouse, J. S. Stutrud, G. J. Sturgess, and W. M. Roquemore. "Exploration of Compact Combustors for Reheat Cycle Aero Engine Applications." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90179.

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An aero gas turbine engine has been proposed that uses a near-constant-temperature (NCT) cycle and an Inter-Turbine Burner (ITB) to provide large amounts of power extraction from the low-pressure turbine. This level of energy is achieved with a modest temperature rise across the ITB. The additional energy can be used to power a large geared fan for an ultra-high bypass ratio transport aircraft, or to drive an alternator for large amounts of electrical power extraction. Conventional gas turbines engines cannot drive ultra-large diameter fans without causing excessively high turbine temperatures
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3

James, S., M. S. Anand, and B. Sekar. "Towards Improved Prediction of Aero-Engine Combustor Performance Using Large Eddy Simulations." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50199.

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The paper presents an assessment of large eddy simulation (LES) and conventional Reynolds averaged methods (RANS) for predicting aero-engine gas turbine combustor performance. The performance characteristic that is examined in detail is the radial burner outlet temperature (BOT) or fuel-air ratio profile. Several different combustor configurations, with variations in airflows, geometries, hole patterns and operating conditions are analyzed with both LES and RANS methods. It is seen that LES consistently produces a better match to radial profile as compared to RANS. To assess the predictive cap
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4

Hu, Bin, Yong Huang, and Jianzhong Xu. "A Hybrid Semi-Empirical Model for Lean Blow-Out Limit Predictions of Aero-Engine Combustors." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26271.

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Lean blow-out (LBO) is critical to operational performance of combustion systems in propulsion and power generation. Current predictive tools for LBO are based on decades-old empirical correlations that have limited applicability for modern combustor designs. Based on Lefebvre’s model for LBO and flame volume concept, an FV (Flame Volume) model was proposed by Authors in early study. The FV model adds two key parameters of α and β that represent the fraction of dome air and dimensionless flame volume defined as the ratio of flame volume and combustor volume. Due to the flame volume is obtained
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5

Rolt, Andrew, Victor Martínez Bueno, Mirko Romanelli, et al. "Numerical Studies of Novel Aero Engine Secondary Combustors for Low-NOx Emissions." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-16081.

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Abstract Gas turbine thermal efficiency and fuel burn are very dependent on turbine entry temperature and overall pressure ratio (OPR). Unfortunately, increases in these two parameters compromise other key aspects of engine operation and tend to increase emissions of nitrogen oxides (NOx). The European Horizon 2020 ULTIMATE project researched advanced-cycle aero engines with synergistic combinations of novel technologies to increase thermal efficiency without increasing emissions. One candidate technology was the addition of secondary combustion to increase the mean temperature of heat additio
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Leung, Ho Yin, Efstathios Karlis, Yannis Hardalupas, and Andrea Giusti. "Evaluation of Blow-Off Dynamics in Aero-Engine Combustors Using Recurrence Quantification Analysis." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59484.

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Abstract The lean blow-out performance of an engine and the ability to re-ignite the flame, especially at high-altitude conditions, are important aspects for the safe operability of airplanes. The operability margins of the engine could be extended if it was possible to predict the occurrence of flame blowout from in-flight measurements and take actions to dynamically control the flame behaviour before complete extinction. In this work, the use of Re-currence Quantification Analysis (RQA), an established tool for the analysis of non-linear dynamical systems, is explored to reconstruct and stud
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7

Hu, Bin, Yong Huang, Fang Wang, and Fa Xie. "Numerical Simulation of Cold Flow Field of Aero-Engine Combustors for Lean Blow Off Analysis." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45467.

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Анотація:
Lean blow off (LBO) performance is critical to the operational performance of combustion system in propulsion and power generation. Current predictive tools for LBO are based on decades-old empirical correlations that have limited applicability for modern combustor designs. Recent advances in computational fluids dynamics (CFD) have provided new insight into the fundamental processes that occur in these flows. In this paper, it is envisaged a new methodology for the LBO predictions that is predicting the LBO fuel/air ratio based on the cold flow field of the combustor. Comparing to the traditi
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8

Franzelli, B., E. Riber, B. Cuenot, and M. Ihme. "Numerical Modeling of Soot Production in Aero-Engine Combustors Using Large Eddy Simulations." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43630.

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Анотація:
Numerical simulations are regarded as an essential tool for improving the design of combustion systems since they can provide information that is complementary to experiments. However, although numerical simulations have already been successfully applied to the prediction of temperature and species concentration in turbulent flames, the production of soot is far from being conclusive due to the complexity of the processes involved in soot production. In this context, first Large Eddy Simulations (LES) of soot production in turbulent flames are reported in the literature in laboratory-scale con
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Dauch, Thilo Ferdinand, Samuel Braun, Lars Wieth, et al. "Computational Prediction of Primary Breakup in Fuel Spray Nozzles for Aero-Engine Combustors." In ILASS2017 - 28th European Conference on Liquid Atomization and Spray Systems. Universitat Politècnica València, 2017. http://dx.doi.org/10.4995/ilass2017.2017.4693.

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Анотація:
Primary breakup of liquid fuel in the vicinity of fuel spray nozzles as utilized in aero-engine combustors is numericallyinvestigated. As grid based methods exhibit a variety of disadvantages when it comes to the prediction of multi- phase flows, the ”Smoothed Particle Hydrodynamics“ (SPH)-method is employed. The eligibility of the method to analyze breakup of fuel has been demonstrated in recent publications by Braun et al, Dauch et al and Koch et al [1, 2, 3, 4]. In the current paper a methodology for the investigation of the two-phase flow in the vicinity of fuel spray nozzles at typical op
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Venkatesan, Krishna, Arin Cross, and Fei Han. "Acoustic Flame Transfer Function Measurements in a Liquid Fueled High Pressure Aero-Engine Combustor." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-81769.

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Abstract This paper describes an experimental approach and study of thermo-acoustic flame transfer functions in a high-pressure liquid-fueled rich burn combustor. The presence of high background flame luminosity in high-pressure sooty flame combustors precludes the application of any direct optical flame transfer function method. Instead, an acoustic method based on multiple microphones was employed to characterize the combustor acoustic pressure and velocity responses to acoustic forcing. A high-pressure siren device was employed to acoustically excite the combustor air flow over a broad rang
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