Rotating Detonation Combustor Research at the University of Cincinnati

Anand, Vijay; Gutmark, Ephraim

doi:10.1007/s10494-018-9934-2

Cited by 13 publications

(4 citation statements)

References 69 publications

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“…Inlet condition For this study, the designed turbine was assessed with the flow of a hollow RDC such as described by Stoddard et al [31] and Anand et al [32,33]. In the chosen setup the exhaust flow of the RDC was further accelerated by means of a divergent nozzle to finally achieve a mass flow averaged Mach number of 2.…”

Section: Unsteady Rdc Inflowmentioning

confidence: 99%

Design, Optimization, and Analysis of Supersonic Radial Turbines

Inhestern

Braun

Paniagua

et al. 2020

Journal of Engineering for Gas Turbines and Power

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New compact engine architectures such as pressure gain combustion require ad hoc turbomachinery to ensure an adequate range of operation with high performance. A critical factor for supersonic turbines is to ensure the starting of the flow passages, which limits the flow turning and airfoil thickness. Radial outflow turbines inherently increase the cross section along the flow path, which holds great potential for high turning of supersonic flow with a low stage number and guarantees a compact design. First, the preliminary design space is described. Afterward a differential evolution multi-objective optimization with 12 geometrical design parameters is deducted. With the design tool autoblade 10.1, 768 geometries were generated and hub, shroud, and blade camber line were designed by means of Bezier curves. Outlet radius, passage height, and axial location of the outlet were design variables as well. Structured meshes with around 3.7 × 106 cells per passage were generated. Steady three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) simulations, enclosed by the k-omega shear stress transport turbulence model were solved by the commercial solver CFD++. The geometry was optimized toward low entropy and high-power output. To prove the functionality of the new turbine concept and optimization, a full wheel unsteady RANS simulation of the optimized geometry exposed to a nozzled rotating detonation combustor (RDC) has been performed and the advantageous flow patterns of the optimization were also observed during transient operation.

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Section: Unsteady Rdc Inflowmentioning

confidence: 99%

Design, Optimization, and Analysis of Supersonic Radial Turbines

Inhestern

Braun

Paniagua

et al. 2020

Journal of Engineering for Gas Turbines and Power

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“…1,2 The discovery of transitory rotating detonation waves in combustors with a planar structure by Voitsekhovskii et al 3,4 in the 1960s laid the groundwork for the creation of RDEs. In recent years, scholars have conducted extensive and significant research on ignition detonation processes, 5,6 working modes, 7,8 injection and doping, 9,10 flow field structures, 11,12 combustion chamber configurations, 13,14 propulsion performances, 15,16 and other topics. Simultaneously, research institutions have conducted theoretical analyses, numerical simulations, and experimental research based on the rocket type, turbine combination, and ramtype RDEs, as well as the integration of rotating detonation combustors (RDCs) into various propulsion systems.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on the interactions between rotating detonation wave complex and planar turbine cascade

Xia

et al. 2022

Energy Science & Engineering

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Due to pressure gain characteristics, the rotating detonation combustor (RDC) can be integrated into gas turbines by further improving the system's performance. The matching of unsteady flows in the RDC and turbine is a key challenge. Here, interactions in an RDC and planar turbine cascade are investigated using the unsteady Reynolds time-averaged Navier-Stokes method. The effects of the blade profiles on interactions between the oblique shock wave (OSW) and turbine cascade are analyzed, and the suppression effect of the turbine cascade on high-frequency pressure oscillations is evaluated. The results show that the OSW interacts with the leading edge, pressure side, suction side, and trailing edge of the turbine stator and rotor blades, which generates complex wave systems in the cascade passage. The opposite propagation direction causes the OSW to be aligned or misaligned with the stator blade. The position of the OSW that operates on the turbine cascade changes, and two different wave system structures appear. The various pitches of the turbine cascade at different blade heights cause differing intensities and propagation directions in the reflected wave as generated by the action of the OSW and turbine cascade and the variable flow fields at different blade heights. The turbine cascade can significantly suppress the high-frequency pressure oscillations, while the pressure amplitude attenuation rate can reach over 80% when the OSW propagates through the turbine cascade. These findings expound on the interaction mechanism between the rotating detonation wave complex and the turbine stator and rotor blades.

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“…A small amount of carbon monoxide gas mixed in kerosene is conducive to detonation, but when its concentration exceeds 75%, it will also play a detonation-suppression role. Moreover, for blend gas-fueled detonation, it does not mean that the higher the contents of small molecular gases (such as hydrogen and ethylene) are, the better performance RDE will have [13,14]. Different operating conditions correspond to different optimum fuel compositions.…”

Section: Introductionmentioning

confidence: 99%

“…A lot of research has found that plasma can effectively decrease the DDT (deflagration to detonation transition) distance and reduce the initiation energy of detonation [21][22][23][24]. Claflin [25] proposed the plasma RDE patent in 2005 and the Cincinnati university conducted the experimental study of plasma RDE in 2018 [14]. It was found that the application of plasma can positively impact RDC operation at conditions that did not previously support rotating detonations and increase wave speed at some conditions.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on DBD plasma reforming hydrocarbon blends

Xu¹,

Wu²,

Song³

et al. 2021

Plasma Sci. Technol.

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To improve the ‘detonation-supporting’ performance of fuel-rich catalytic combustion products, DBD plasma, stimulated by adjustable nanosecond pulse power supply, was used to further regulate the components and concentrations of the hydrocarbon blends. In this paper, the parameters including load voltage, frequency, rising (falling) edge, pulse width and feeding flow rate were changed respectively, and the corresponding concentration and proportion change of the components in blend gas were investigated. According to the experiment result, it was found that when the discharge frequency is low, the plasma mainly promotes the transformation of light gaseous substances, while it mainly promotes the conversion to heavy hydrocarbons when the frequency is larger. Increasing load voltage will strengthen this trend. The controlling and reforming effect of plasma on the blend gas will decrease with the increase of voltage rising (falling) edge and the feeding flow rate. The regulation effect will be strengthened with the increase of pulse width under 200 ns. With the increase of discharge intensity, the ‘carbon’ settles on the walls of the reactor, which will change the dielectric constant, leading to the loss of control of the discharge.

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Rotating Detonation Combustor Research at the University of Cincinnati

Cited by 13 publications

References 69 publications

Design, Optimization, and Analysis of Supersonic Radial Turbines

Design, Optimization, and Analysis of Supersonic Radial Turbines

Numerical investigation on the interactions between rotating detonation wave complex and planar turbine cascade

Experimental investigation on DBD plasma reforming hydrocarbon blends

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