Variable Transpiration Cooling Effectiveness in Laminar and Turbulent Flows for Hypersonic Vehicles

Brune, Andrew J.; Hosder, Serhat; Gulli, Stefano; Maddalena, Luca

doi:10.2514/1.j053053

Cited by 20 publications

(11 citation statements)

References 14 publications

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“…In transpiration cooling, Glass et al ( 7 ) simulated heat transfer cooling on the refractory composite material as used on engine combustor walls using a boundary layer method on a 2D configuration. Brune et al ( 8 ) further investigated the effects of variable transpiration cooling in a 2D simulation to show that adjusting the injection velocity along the surface gave better results. Henline ( 9 ) too showed in a 2D axisymmetric simulation that the fluid is injected uniformly into the flow from a porous surface has led to heat transfer alleviation.…”

Section: Introductionmentioning

confidence: 99%

Heat alleviation studies on hypersonic re-entry vehicles

Khalid

Juhany

2018

Aeronaut. j.

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A numerical simulation has been carried out to investigate the effects of leading edge blowing upon heat alleviation on the surface of hypersonic vehicles. The initial phase of this work deals with the ability of the present CFD-based techniques to solve hypersonic flow field past blunt-nosed vehicles at hypersonic speeds. Towards this end, the authors selected three re-entry vehicles with published flow field data against which the present computed results could be measured. With increasing confidence on the numerical simulation techniques to accurately resolve the hypersonic flow, the boundary condition at the solid blunt surface was then equipped with the ability to blow the flow out of the solid boundary at a rate of at least 0.01–0.1 times the free stream (ρ∞u∞) mass flow rate. The numerical iterative procedure was then progressed until the flow at the surface matched this new ‘inviscid like’ boundary condition. The actual matching of the flow field at the ejection control surface was achieved by iterating the flow on the adjacent cells until the flow conformed to the conditions prescribed at the control surface. The conditions at the surface could be submitted as a ρ∞u∞at the surface or could be equipped as a simple static pressure condition providing the desired flow rate. The comparison between the present engineering approach and the experimental data presented in this study demonstrate its ability to solve complex problems in hypersonic.

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Section: Introductionmentioning

confidence: 99%

Heat alleviation studies on hypersonic re-entry vehicles

Khalid

Juhany

2018

Aeronaut. j.

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“…The study presented in this paper considers a single geometry (shown in Fig. 3) based on previous missions and numerical investigations [23,50]. The vehicle shape is representative of a generic hypersonic re-entry geometry, a 30…”

Section: Resultsmentioning

confidence: 99%

“…However, transpiration cooling offers a variety of additional advantages like re-usability, shape stability and the ability to optimise mass injection locally and temporally. The large amount of research that has been focused on this technique highlights its potential [11,13,[19][20][21][22][23].…”

Section: Introductionmentioning

confidence: 99%

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

2020

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This paper presents results of a system study of transpiration cooled thermal protection systems for Earth re-entry. The cooling performance for sustained hypersonic flight and transient re-entry of a blunt cone geometry is assessed. A simplified numerical model is used to calculate the transient temperature of a transpiration cooled heat shield. The performance of transpiration cooling is assessed by calculating the overall required coolant mass for different steady state and transient flight scenarios. Spatially and temporally optimised mass injection is presented for various flight conditions. The majority of the injection is required on the spherical nose segment of the blunted cone. Carbon/Carbon composite ceramic and the ultra high temperature ceramic Zirconium diboride are considered as wall materials. Both materials require similar amounts of coolant injection. In continuous hypersonic cruise, transpiration cooling is highly effective for flight conditions with velocities below 8 km s −1 and altitudes above 40 km. For transient re-entry, transpiration cooling is most viable for trajectories of entry velocities below 8.5 km s −1 and ballistic coefficients below 2.1 kg m −2. Nomenclature A Area, m 2 C D Drag coefficient c p Specific heat capacity, J kg −1 K −1

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“…In addition, front edge of bluff body has a better sweat cooling effect than flat plate, with a cooling efficiency about 8% higher than that of flat plate. Brune et al studied the effect of variable sweat cooling in advection and turbulent flow in hypersonic flow environments [46]. According to the numerical analysis, for common laminar and turbulent flows, variable transpiration cooling is more effective than uniform transpiration cooling, and the numerical analysis also verified that transpiration in turbulent boundary layer is less efficient than laminar flow.…”

Section: Latest Research Progress Of Active Thermal Protectionmentioning

confidence: 99%

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

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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Variable Transpiration Cooling Effectiveness in Laminar and Turbulent Flows for Hypersonic Vehicles

Cited by 20 publications

References 14 publications

Heat alleviation studies on hypersonic re-entry vehicles

Heat alleviation studies on hypersonic re-entry vehicles

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

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

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