Parametric Survey of a Natural Gas-Air Rotating Detonation Engine at Elevated Pressure

Walters, Ian V.; Journell, Christopher L.; Lemcherfi, Aaron; Gejji, Rohan; Heister, Stephen D.; Slabaugh, Carson D.

doi:10.2514/6.2019-1510

Cited by 11 publications

(4 citation statements)

References 17 publications

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“…Many researchers have concluded that the width is related to the detonation cell [30,48], and pointed out that the critical width is the cell size divided by π [48]. According to the latest research results for the quantitative relationship between the cell size and the initial pressure by Purdue University [49], as is shown in Figure 5, the cell size is greatly affected by the initial pressure. From their results we can see clearly for methane-air, in the initial pressure of 1 MPa, the detonation cell size was reduced to 30 mm, which means the width size of only 10 mm is suitable for the initial pressure of 1 MPa.…”

Section: Independence Test and Model Validationmentioning

confidence: 99%

Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor

Sun

Zheng

et al. 2019

Applied Sciences

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Featured Application: Provide basis for rotating detonation combustor applications on gas turbine.Abstract: In this study, three-dimensional numerical studies have been performed to investigate the performance of a rotating detonation combustor with a diverging nozzle downstream. The effects of a diverging nozzle on the formation and propagation process of a detonation wave and typical flow field parameters in a rotating detonation combustor are mainly discussed. The results indicate that the diverging nozzle downstream is an important factor affecting the performance and design of a rotating detonation combustor. The diverging nozzle does not affect the formation and propagation process of the rotating detonation wave, while the time of two key wave collisions are delayed during the formation process of the detonation wave. With increases of the diverging angle, the rotating detonation combustor with the diverging nozzle can still maintain a certain pressure gain performance. Both the diverging nozzle and diverging angle have great influence on the flow field parameters of the rotating detonation combustor, including reducing the high pressure and temperature load, making the distribution of the outlet parameters uniform, and changing the local supersonic flow at the outlet. Among them, the outlet static pressure is reduced by up to 88.32%, and the outlet static temperature is reduced by up to 32.12%. This evidently improves the working environment of the combustor while reducing the thermodynamic and aerodynamic loads at the outlet. In particular, the diverging nozzle does not affect the supersonic characteristics of the outlet airflow, and on this basis, the Mach number becomes coincident and enhanced.

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Section: Independence Test and Model Validationmentioning

confidence: 99%

Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor

Sun

Zheng

et al. 2019

Applied Sciences

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“…Several experimental programs have published detailed sweeps of geometry, injection schemes, and fueling conditions (for examples, see [6,[35][36][37]) that establish several characteristic modes of operation. These include wave co-rotation with varying counts and direction, wave counter-propagation (both with equal and different number of co-and counter-propagating waves), periodic wave nucleation and extinction ('slapping' modes), and pulsating plane waves.…”

Section: A Experiments Geometry and Dynamicsmentioning

confidence: 99%

Modeling Thermodynamic Trends of Rotating Detonation Engines

Koch,

Kutz

2020

Preprint

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The formation of a number of co-and counter-rotating coherent combustion wave fronts is the hallmark feature of the Rotating Detonation Engine (RDE). The engineering implications of wave topology are not well understood nor quantified, especially with respect to parametric changes in combustor geometry, propellant chemistry, and injection and mixing schemes. In this article, a modeling framework that relates the time and spacial scales of the RDE to engineering performance metrics is developed and presented. The model is built under assumptions of backpressure-insensitivity and nominally choked gaseous propellant injection. The Euler equations of inviscid, compressible fluid flow in one dimension are adapted to model the combustion wave dynamics along the circumference of an annular-type rotating detonation engine. These adaptations provide the necessary mass and energy input and output channels to shape the traveling wave fronts and decaying tails. The associated unit processes of injection, mixing, combustion, and exhaust are all assigned representative time scales necessary for successful wave propagation. We find that the separation, or lack of, these time scales are responsible for the behavior of the system, including wave co-and counterpropagation and bifurcations between these regimes and wave counts. Furthermore, as there is no imposition of wave topology, the model output is used to estimate the net available mechanical work output and thermodynamic efficiency from the closed trajectories through pressure-volume and temperature-entropy spaces. These metrics are investigated with respect to variation in the characteristic scales for the RDE unit physical processes.

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“…Recent developments in the RDE have heightened its potential integration with gas turbines [3][4][5][6], ramjets [7,8], rocket engines [9,10], etc. For example, Walters et al [11] investigated the characteristics and maintainability of rotating detonations with methane-air fuel at wide operating conditions where the mass flow rates range from 200-500 kg/m 2 ⋅ s and the equivalence ratios were 0.85-1.2. The research was aimed for landbased power generation systems and it was found that the characteristic exhaust velocity of the RDE could reach 97.5-99.5% of the theoretical value compared to the thermodynamic cycle of constant-volume combustion.…”

Section: Introductionmentioning

confidence: 99%

Effects of inlet and secondary flow conditions on the flow field of rotating detonation engines with film cooling

Yao

et al. 2023

International Journal of Hydrogen Energy

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Parametric Survey of a Natural Gas-Air Rotating Detonation Engine at Elevated Pressure

Cited by 11 publications

References 17 publications

Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor

Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor

Modeling Thermodynamic Trends of Rotating Detonation Engines

Effects of inlet and secondary flow conditions on the flow field of rotating detonation engines with film cooling

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