Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Dong, Yiwei; Wang, Ertai; You, Yancheng; Yin, Chunping; Wu, Zongpu

doi:10.3390/en12020240

Cited by 16 publications

(3 citation statements)

References 174 publications

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“…Redundant design based on limit deviation has been conventionally employed to address these uncertainties, leading to a heavy weight of the TPS and decreased system performance [2]. Therefore, developing a high-precision approach to TPS design that accounts for various uncertainties is a critical advancement in the field [3].…”

Section: Introductionmentioning

confidence: 99%

A Parametric Physics-Informed Deep Learning Method for Probabilistic Design of Thermal Protection Systems

Zhang

et al. 2023

Energies

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Precise and efficient calculations are necessary to accurately assess the effects of thermal protection system (TPS) uncertainties on aerospacecrafts. This paper presents a probabilistic design methodology for TPSs based on physics-informed neural networks (PINNs) with parametric uncertainty. A typical thermal coating system is used to investigate the impact of uncertainty on the thermal properties of insulation materials and to evaluate the resulting temperature distribution. A sensitivity analysis is conducted to identify the influence of the parameters on the thermal response. The results show that PINNs can produce quick and accurate predictions of the temperature of insulation materials. The accuracy of the PINN model is comparable to that of a response surface surrogate model. Still, the computational time required by the PINN model is only a fraction of the latter. Considering both computational efficiency and accuracy, the PINN model can be used as a high-precision surrogate model to guide the TPS design effectively.

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Section: Introductionmentioning

confidence: 99%

A Parametric Physics-Informed Deep Learning Method for Probabilistic Design of Thermal Protection Systems

Zhang

et al. 2023

Energies

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“…With the development of hypersonic vehicle and space technology, the necessity for thermal shielding has risen dramatically (Wang et al, 2021). When a hypersonic aircraft flies close to 10 Mach, the windward surface is exposed to an ultra-thermal environment, and the surface temperature of some parts exceeds 3500 K. Continuous aerodynamic heating is a problem for hypersonic cruise missiles (Dong et al, 2019). The research of OPEN ACCESS EDITED BY aircraft shape design and thermal protection materials is necessary for the development of spacecraft return technology (Ji et al, 2008;Hayashi and Wakayama, 2009).…”

Section: Introductionmentioning

confidence: 99%

Effects of particle diameter and plate thickness on transpiration cooling for double-layer porous plates

Zhang

Yan

et al. 2022

Front. Energy Res.

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Transpiration cooling is a highly efficient active thermal protection technology, which has a great application prospect in the thermal protection of hypersonic vehicles. Nevertheless, the problem of large injection pressure caused by porous structure in transpiration cooling system has been ignored in previous studies. In this work, the transpiration cooling performance of double-layer sintered metal particle plates with different particle diameter combinations and plate thickness were simulated. The results showed that the cooling effectiveness of double-layer plates was improved when the particle diameter of the porous plate in direct contact with the main stream decreased. The inner plate particle diameter and plate thickness had little effect on cooling performance. By increasing inner plate particle diameter, the coolant injection pressure can be lowered by 41% while the structural thickness was maintained. Further reducing the thickness of the outer plate to 1/4 of the total thickness can reduce the injection pressure to 38% of the single plate, which provided an optimization direction for reducing engine power consumption caused by heat dissipation.

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“…A new power generation scheme that can meet the scramjet power requirements and avoid quality penalties8, which derives from the expander cycle rocket engine9 and be called high temperature gaseous hydrocarbon fuel TPG method. The TPG method is based on the principle of expansion of high temperature hydrocarbon fuel after regenerative cooling process [10][11][12]. When hydrocarbon fuel gets gasified13 in cooling channel and cracks into small hydrocarbons14 which helps to enhance the fuel TPG capability.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Thermo-physical Characteristics of High Temperature Gaseous Hydrocarbon Fuel Thermal Power Generation for Regeneratively Cooled Hypersonic Propulsion System

Xu¹,

Li²,

Yan³

et al. 2019

Preprint

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The aspirated hypersonic air-breathing propulsion system requires a large amount of power generation, but its special structure makes it impossible to adopt common power generation methods. The high-temperature gaseous hydrocarbon fuel thermal power generation (TPG) system was developed to solve the power generation problem for hypersonic air-breathing propulsion system. But off-design operating conditions of the hypersonic propulsion system results in a more complex process for both propulsion system and the TPG system. To better analyzing the dynamic thermos-physical characteristics of hypersonic airbreathing propulsion system considering thermal-mechanical coupling process among cooling/TPG system, a dynamic analytical model was developed, and the dynamic thermos-physical characteristics of TPG system under different off-design working conditions were conducted. It can be concluded from the analytical results that the dynamic process of thermos-physical characteristics shows a complex trend under the flight Mach number and fuel equivalence ratio off-design working conditions. Such complexity of dynamic characteristics brings difficulties in fuel supply for the propulsion system.

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Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Cited by 16 publications

References 174 publications

A Parametric Physics-Informed Deep Learning Method for Probabilistic Design of Thermal Protection Systems

A Parametric Physics-Informed Deep Learning Method for Probabilistic Design of Thermal Protection Systems

Effects of particle diameter and plate thickness on transpiration cooling for double-layer porous plates

Dynamic Thermo-physical Characteristics of High Temperature Gaseous Hydrocarbon Fuel Thermal Power Generation for Regeneratively Cooled Hypersonic Propulsion System

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