Endothermic Heat-Sink of Jet Fuels for Scramjet Cooling

Huang, He; Spadaccini, L. J.; Sobel, David R.

doi:10.2514/6.2002-3871

Cited by 122 publications

(103 citation statements)

References 2 publications

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“…However, the aerodynamic heat attributed to high-speed flight is still a challenge for current engine technology. Among the available cooling methods, the regenerative cooling technology using endothermic hydrocarbon fuel as the coolant is recognized as the most effective way [2].…”

Section: Introductionmentioning

confidence: 99%

Investigation on the Mechanism of Thermoacoustic Instability of n-Decane at Subcritical Pressure

Wang

Nie

et al. 2018

AIAA Journal

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Thermoacoustic instability of n-decane at subcritical pressure in a small-scale channel is investigated from three aspects: the flow pattern, the fluctuations of temperature and pressure, and the dynamic model. The results show that the thermoacoustic instability is a type of dynamic instability and experiences three stages: that is, appearance, development, and disappearance. Oscillations happen for the pressure drop, fluid temperature, and wall temperature when thermoacoustic instability appears. The thermoacoustic instability is driven by a positive and a negative feedback. When the outlet oil temperature reaches saturation temperature, the positive feedback loop is on, and the thermoacoustic oscillation happens. After that, the flow pattern near the outlet recovers to annular flow and then transforms to a single-gas flow, which leads the thermoacoustic oscillation to happen again.

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Section: Introductionmentioning

confidence: 99%

Investigation on the Mechanism of Thermoacoustic Instability of n-Decane at Subcritical Pressure

Wang

Nie

et al. 2018

AIAA Journal

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“…However, the large heat release from combustion in combustor as well as the high enthalpy of the inflow makes thermal protection a main challenge. Active cooling with hydrocarbon fuel such as kerosene is proved to be an effective way [3][4][5]. For the sake of injection, the pressure inside the cooling channels is usually higher than the critical pressure of kerosene; thus the kerosene would become supercritical when absorbing heat.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Supercritical Heat Transfer of RP3 Kerosene Flowing inside a Cooling Channel of Scramjet

Wang

Pan

Bao

et al. 2014

Advances in Mechanical Engineering

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Supercritical convective heat transfer characteristics of hydrocarbon fuel play a fundamental role in the active cooling technology of scramjet. In this paper, a 2D-axisymmetric numerical study of supercritical heat transfer of RP3 flowing inside the cooling channels of scramjet has been conducted. The main thermophysical properties of RP3, including density, specific heat, and thermal conductivity, are obtained from experimental data, while viscosity is evaluated from a commercial code with a ten-species surrogate. Effects of heat flux, mass flow rate, and inlet temperature on supercritical heat transfer processes have been investigated. Results indicate that when the wall temperature rises above the pseudocritical temperature of RP3, heat transfer coefficient decreases as a result of drastic decrease of the specific heat. The conventional heat transfer correlations, that is, Gnielinski formula, are no longer proper for the supercritical heat transfer of RP3. The modified Jackson and Hall formula, which was proposed for supercritical CO 2 and water, gives good prediction except when the wall temperature is near or higher than the pseudocritical temperature.

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“…In order to protect an engine flying with a high Mach number from being burnt out, regenerative cooling, film cooling, combined cooling, and so forth have been applied to cool the engine [1]. Supersonic film cooling, as one of the most promising cooling methods, has attracted researchers' attention for its potential usage on scramjet engine, which is one of the engines with extremely high heat load.…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis of Supersonic Film Cooling in Supersonic Flow in Hypersonic Inlet with Isolator

Zhang

Bao

Zhang

2014

Advances in Mechanical Engineering

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Supersonic film cooling is an efficient method to cool the engine with extremely high heat load. In order to study supersonic film cooling in a real advanced engine, a two-dimensional model of the hypersonic inlet in a scramjet engine with supersonic film cooling in the isolator is built and validated through experimental data. The simulation results show that the cooling effect under different coolant injection angles does not show clear differences; a small injection angle can ensure both the cooling effect and good aerodynamic performances (e.g., flow coefficient) of the hypersonic inlet. Under selected coolant injection angle and inlet Mach number, the cooling efficiency increases along with the injection Mach number of the coolant flow, only causing a little total pressure loss in the isolator. Along with the increase of the inlet Mach number of the hypersonic inlet, the cooling efficiency does not present a monotonic change because of the complex shock waves. However, the wall temperature shows a monotonic increase when the inlet Mach number increases. The mass flow rate of coolant flow should be increased to cool the engine more efficiently according to the mass flow rate of the main stream when the inlet Mach number increases.

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Endothermic Heat-Sink of Jet Fuels for Scramjet Cooling

Cited by 122 publications

References 2 publications

Investigation on the Mechanism of Thermoacoustic Instability of n-Decane at Subcritical Pressure

Investigation on the Mechanism of Thermoacoustic Instability of n-Decane at Subcritical Pressure

Numerical Investigation on Supercritical Heat Transfer of RP3 Kerosene Flowing inside a Cooling Channel of Scramjet

Numerical Analysis of Supersonic Film Cooling in Supersonic Flow in Hypersonic Inlet with Isolator

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