Bibliografías temáticas / Rotating Detonation Engine, Feasibility Assessment

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Literatura académica sobre el tema "Rotating Detonation Engine, Feasibility Assessment"

Autor: Grafiati
Publicado: 10 de marzo de 2023

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Artículos de revistas sobre el tema "Rotating Detonation Engine, Feasibility Assessment"

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Deng, Li, Hu Ma, Can Xu, Xiao Liu y Changsheng Zhou. "The feasibility of mode control in rotating detonation engine". Applied Thermal Engineering 129 (enero de 2018): 1538–50. http://dx.doi.org/10.1016/j.applthermaleng.2017.10.146.

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A. Dairobi G, M. A. Wahid, M. A. Mazlan y M. H. Azeman. "Early Assessment of Asymmetric Vortex Small Rotating Detonation Engine". Evergreen 8, n.º 1 (marzo de 2021): 182–86. http://dx.doi.org/10.5109/4372276.

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Xue, Sainan, Zhuojun Ying, Hu Ma y Changsheng Zhou. "Experimental Investigation on Two-Phase Rotating Detonation Fueled by Kerosene in a Hollow Directed Combustor". Frontiers in Energy Research 10 (14 de julio de 2022). http://dx.doi.org/10.3389/fenrg.2022.951177.

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The operating characteristic of two-phase rotating detonation fueled by kerosene in a hollow combustor with the isolation section is experimentally studied. When the air mass flow rate is 1.5 kg/s, the equivalence ratio is 0.98, and the total temperature of the mixture is 650 K, the stable rotating detonation wave (RDW) is obtained, which verifies the feasibility of the designed two-phase rotating detonation combustor (RDC). It is found that there is a high-frequency oblique shock induced by the upstream rotating detonation wave in the isolation section. A series of experimental tests have been carried out by changing the total temperature of incoming air , which is an important factor affecting the initiation. When the equivalent ratio of reactants is between 0.950–1.152, a stable single-wave detonation is formed. With the increase of equivalent ratio, the time of detonation wave establishment decreases, the intensity and frequency of detonation wave increases, and the temperature of engine tail flame rises. The equivalent chamber pressure Δpφ was defined, and the curve of the performance of the RDC with the equivalent ratio was obtained. The velocity of the RDW increases with the increase of equivalent ratio, and the chamber pressure has an optimal value, a higher or lower equivalent ratio will lead to the decrease of equivalent chamber pressure and the combustion chamber performance.
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Tesis sobre el tema "Rotating Detonation Engine, Feasibility Assessment"

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Matteo, Poggiali. "Development of a new combustor liners thermal design procedure through low order codes and uncertainty quantification tools". Doctoral thesis, 2021. http://hdl.handle.net/2158/1238634.

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Turbomachinery plays an important role in the propulsion and heavy-duty industry. Improving the efficiency and reliability of gas turbines continue to be an important driver in the development of modern engines and power generation. There are two straightforward and effective methods for improving the performance of a gas turbine engine. One is increasing the engine pressure ratio to raise the thermal efficiency, the other is increasing the outlet temperature of a combustor to raise the specific thrust. Therefore, the gas turbine combustors working conditions are moving towards higher temperature rise and higher heat capacity. Therefore, the design requirements for a combustor become stricter, such as a wider working range, shorter length, and smaller distribution of outlet temperature. Simultaneously, the combustor is required to have a longer life and lower pollutant emission. In this scenario, a fundamental role is played by the cooling system. The definition of the most appropriate scheme represents one of the most challenging tasks in the combustor since it directly determines the components life. During the design and subsequent optimization phases of a combustor cooling system, the designer must consider several uncertainties related to manufacturing, geometry and operating conditions. These gaps can be very impacting on the system performance, so it is obvious that the design becomes a matter of optimization of the whole system. This requires an accurate assessment of trade-offs to meet all requirements. The design choices made in the first phases influence the following developments and it is essential to have a tool as efficient and flexible as possible to rely on. During the initial stages, 1-D codes are still widely used in industrial practice, and a low-order approach is preferred over high-fidelity simulations. These tools are important for designers because they allow having a good understanding of the problem, in relatively short times and with low general costs. Although these analyses have a good predictive level, they are often used when input quantities that characterize the problem are roughly known. These gaps lead to the inclusion of uncertainties within the code, which propagate and eventually influence the solution. The final common objective is to optimize the various components to find out the configuration in which the machine is independent from the uncertainties that may afflict it, thus arriving at a robust design. The aim of this thesis is the development of a numerical procedure for the preliminary thermal design of combustor liners (Therm-1D/Dakota). This procedure is based on the coupling of a one-dimensional tool (Therm-1D), developed by DIEF of the University of Florence, and a software that allows uncertainty quantifications analyses (Dakota). This has allowed the development of an innovative, faster, and more reliable procedure for the preliminary design and optimization of combustor cooling systems that is able to estimate the uncertainties affecting the results of this numerical simulations. In this way, the output quantities are as independent as possible from input uncertainties.
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Actas de conferencias sobre el tema "Rotating Detonation Engine, Feasibility Assessment"

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Paxson, Daniel E. "Preliminary Computational Assessment of Disk Rotating Detonation Engine Configurations". En AIAA Scitech 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-2157.

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Saha, Pankaj, Peter Strakey, Donald Ferguson y Arnab Roy. "Numerical Analysis of Detonability Assessment in a Natural Gas-Air Fueled Rotating Detonation Engine". En ASME 2019 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/imece2019-11728.

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Abstract Rotating Detonation Engines (RDE) offer an alternative combustion strategy to replace conventional constant pressure combustion with a process that could produce a pressure gain without the use of a mechanical compressor. Recent numerical and experimental publications that consider air as the oxidizer have primarily focused on the ability of these annular combustors to sustain a stable continuous detonation wave when fueled by hydrogen. However, for this to be a viable consideration for the land-based power generation it is necessary to explore the ability to detonate natural gas and air within the confines of the annular geometry of an RDE. Previous studies on confined detonations have expressed the importance of permitting detonation cells to fully form within the combustor in order to achieve stability. This poses a challenge for natural gas–air fueled processes as their detonation cell size can be quite large even at moderate pressures. Despite the practical importance, only a few studies are available on natural gas detonations for air-breathing RDE applications. Moreover, the extreme thermodynamic condition (high temperature inside the combustor) allows limited accessibility inside the combustor for detailed experimental instrumentations, providing mostly single-point data. Recent experimental studies at the National Energy Technology Laboratory (NETL) have reported detonation failure at higher methane concentration in an air-breathing RDE fueled by natural gas-hydrogen fuel blends. This encourages to perform a detailed numerical investigation on the wave characteristics of detonation in a natural gas-air fueled RDE to understand the various aspects of instability associated with the natural gas-air detonation. This study is a numerical consideration of a methane-air fueled RDE with varying operating conditions to ascertain the ability to achieve a stable, continuous detonation wave. The simulations have been performed in a 2D unwrapped RDE geometry using the open-source CFD library “OpenFOAM” employing an unsteady pressure-based compressible reactive flow solver with a k–ε turbulence model in a structured rectangular grid system. Both reduced and detailed chemical kinetic models have been used to assess the effect of the chemistry on the detonation wave characteristics and the underlying flow features. A systematic grid sensitivity study has been conducted with various grid sizes to quantify the weakly stable overdriven detonation on a coarse mesh and oscillating features at fine mesh resolutions. The main focus of the current study is to investigate the effects of operating injection pressure on detonation wave characteristics of an air-breathing Rotating Detonation Engine (RDE) fueled with natural gas-hydrogen fuel blends. Wave speeds, peak pressures and temperatures, and dominant frequencies have been computed from the time histories. The flow structures were then visualized using 2D contours of temperature and species concentration.
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Paxson, Daniel E. y Andrew Naples. "Numerical and Analytical Assessment of a Coupled Rotating Detonation Engine and Turbine Experiment". En 55th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1746.

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Paxson, Daniel E. "Computational Assessment of the Impact of Wave Count on Rotating Detonation Engine Performance". En AIAA SCITECH 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-1290.

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Paxson, Daniel E. y Kenji Miki. "Computational Assessment of Inlet Backflow Effects on Rotating Detonation Engine Performance and Operability". En AIAA SCITECH 2022 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-1263.

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Hernandez-McCloskey, Joseph, Daniel I. Pineda, John W. Bennewitz, Blaine R. Bigler, Jason R. Burr, Stephen A. Danczyk, Eric J. Paulson y William A. Hargus. "Design and analysis of an additively manufactured rotating detonation rocket engine chamber for calorimetry and thermal management assessment". En AIAA SCITECH 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-0355.

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7

Bellocq, Pablo, Iñaki Garmendia y Vishal Sethi. "Preliminary Design Assessments of Pusher Geared Counter-Rotating Open Rotors: Part I — Low Pressure System Design Choices, Engine Preliminary Design Philosophy and Modelling Methodology". En ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43812.

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In this 2-part publication, the impact of the main low pressure system parameters of a pusher counter rotating Geared Open Rotor (GOR) on mission fuel burn, certification noise and emissions is presented for a 160 PAX medium haul class aircraft. Due to their high propulsive efficiency, GORs have the potential to significantly reduce fuel consumption and emissions relative to conventional high bypass ratio turbofans. However, this novel engine architecture presents many design and operational challenges both at engine and aircraft level. The assessment of the impact of the main low pressure preliminary design parameters of GORs on mission fuel burn, certification noise and emissions is necessary at preliminary design stages in order to identify optimum design regions. These assessments may also aid the development process when compromises need to be performed as a consequence of design, operational or regulatory constraints. Part I of this two-part publication describes the main low pressure (LP) system design choices for a GOR as well as the preliminary design philosophy and simulation framework developed for the assessments. Part II presents the assessment studies. The simulation framework described in this paper comprises the following models: engine and aircraft performance, engine mechanical design and weight, engine certification noise and emissions. A novel aspect of the presented simulation framework is that the design point efficiency and the design feasibility of the low pressure components are calculated for each engine design.
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8

Colmenares, Fernando, Daniele Pascovici, Stephen Ogaji, Pericles Pilidis, Alexander Garci´a y Luis Latorre. "Future Aero-Engines’ Optimisation for Minimal Operating Costs". En ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50127.

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While aircraft environmental performance has been important since the beginnings of commercial aviation, continuously increasing passenger traffic and a rise in public awareness have made aircraft noise and emissions two of the most pressing issues hampering commercial aviation growth today. The focus of this study is to determine the feasibility of vey-high bypass ratio, geared and contra-rotating aero engines (see figures 2–4) for short range commercial aircraft in terms of economics and environment. This involves optimising the engines’ design point to minimise the direct operating cost and evaluating the economic and environmental impact. The results present a great potential benefit of the geared turbofan compared to high BPR one (baseline) to reduce DOC; however this may involve NOx penalties, that is an increase of 11.6% in comparison to the baseline. The CRTF engine seems to be, at least according to the simulations, a very promising solution in terms of environmental and economical performance. This is one on the series of work that would be carried out using the design tool proposed. Further work on the assessment of more radical turbofans at different economical and environmental scenarios would be published when completed.
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