Numerical simulation for hypersonic vehicle on-board magnetohydrodynamic power generation

Harada, Naomi; Kikuchi, Takashi; Lineberry, J.T.

doi:10.1109/pecon.2008.4762588

Cited by 4 publications

(1 citation statement)

References 5 publications

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“…Magnetohydrodynamic (MHD) power generation has captured the attention of researchers, primarily due to its exceptional attributes including high power generation efficiency, rapid responsiveness, and seamless compatibility with scramjet systems [18]. Harada et al [19] conducted a comprehensive series of experiments for scramjet-driven MHD power generation, culminating in the successful extraction of a reasonable output of electric power. Furthermore, numerical simulations, spanning both one and three dimensions, were executed to elucidate and expound upon the experimental findings.…”

Section: Introductionmentioning

confidence: 99%

Performance Assessment of Closed-Brayton-Cycle and Thermoelectric Generator Combined Power Generation System Coupled with Hydrocarbon-Fueled Scramjet

Cheng,

Jing,

et al. 2023

Energies

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Closed-Brayton-cycle (CBC) is a potential scheme to provide high-power electricity for hypersonic vehicles, but finite cold source onboard limits its power level. A thermoelectric generator (TEG) combined with CBC is a feasible power enhancement approach by extending the available temperature range of cold source. In this study, a performance assessment of the CBC-TEG combined power generation system coupled with hydrocarbon-fueled scramjet is performed to exhibit its possible operation characteristics and performance limitations on hypersonic vehicles. Results indicate that, at a fixed flight Mach number, a larger fuel equivalence ratio (φ) leads to a higher total electric power and CBC power but a lower TEG power. There are three limitations on the fuel equivalence ratio, TEG temperature difference, and combustion heat dissipation adjustment for the operation of CBC-TEG. The total power of CBC-TEG can be adjusted by φ, but the adjustable range becomes smaller at higher Ma. The electric quantity at unit fuel mass increases with φ, mainly due to the higher thermoelectric conversion efficiency. Moreover, the maximum value of the electric quantity at unit fuel mass for CBC-TEG reaches 277.0 kJ/kg, which is about 33.4% higher than that of standalone CBC.

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Section: Introductionmentioning

confidence: 99%

Performance Assessment of Closed-Brayton-Cycle and Thermoelectric Generator Combined Power Generation System Coupled with Hydrocarbon-Fueled Scramjet

Cheng,

Jing,

et al. 2023

Energies

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Investigation of hydrocarbon fuel rotating flow considering the variation of physical properties

Sun

Qin

Huang

et al. 2019

International Journal of Heat and Mass Transfer

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Numerical Simulation of Flow and Heat Transfer in a Square Rotating U-Duct Using Hydrocarbon Fuel

Sun

Qin

Huang

et al. 2019

Journal of Heat Transfer

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Air turbine power generation system is considered as a feasible power generation system for hypersonic aircraft with Mach 6. However, the incoming air with high temperature cannot be used as coolant while turbine has to be cooled. Since hydrocarbon fuel is the only cooling source onboard, the scheme of fuel cooling air turbine is put forward. In this paper, square cooling channel, including inlet part, outlet part and U-duct, is established based on the typical air turbine. The hydraulic diameter of the channel is 2 mm and four types of U-ducts are used to compare the performance with simulation using k-Epsilon turbulence model. The density and specific heat capacity of fuel are considered as constant as the temperature difference in this study is small. The Reynolds number varies from 2760 to 16,559 and rotating number ranges from 0 to 6.9. The results show that the pressure distribution in radial direction is proportional to the square of radial distance and the square of rotating speed. The regulations of velocity and normalized Nusselt number distributions depend on rotating number. Furthermore, the heat transfer is enhanced with fin while the pressure loss is also increased. The position of fins cannot significantly influence pressure loss but can influence heat transfer obviously. The normalized Nusselt number of inlet-fin U-duct is higher than the outlet-fin U-duct both on leading side surface and trailing side (TS) surface, while the pressure losses for the two types of ducts are almost same.

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Numerical simulation for hypersonic vehicle on-board magnetohydrodynamic power generation

Cited by 4 publications

References 5 publications

Performance Assessment of Closed-Brayton-Cycle and Thermoelectric Generator Combined Power Generation System Coupled with Hydrocarbon-Fueled Scramjet

Performance Assessment of Closed-Brayton-Cycle and Thermoelectric Generator Combined Power Generation System Coupled with Hydrocarbon-Fueled Scramjet

Investigation of hydrocarbon fuel rotating flow considering the variation of physical properties

Numerical Simulation of Flow and Heat Transfer in a Square Rotating U-Duct Using Hydrocarbon Fuel

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