Film cooling by injection into a turbulent boundary layer

Volchkov, É. P.; Zaulichnyi, E. G.; Kutateladze, S. S.; Leont'ev, A. I.

doi:10.1007/bf00918038

Cited by 6 publications

(5 citation statements)

References 2 publications

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“…Aerodynamic correlations are used to determine the surface heat flux for a blunted cone geometry [46,47]. The cooling effect of local heat flux mitigation and downstream film effectiveness is taken into account using semi-empirical models [20,48,49]. The temperature of the fluid and solid phases in the heat shield material are calculated based on an impulse response convolution approach that solves the coupled fluid-solid heat conduction problem assuming an adiabatic back-wall of the plenum structure behind the transpiration cooled segment [44].…”

Section: Model Overviewmentioning

confidence: 99%

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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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Section: Model Overviewmentioning

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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“…For a given trajectory, the aerodynamic heat fluxes with no cooling are calculated from aerodynamic correlations or imported from an external database. The cooling effect of the local heat flux mitigation through blowing and downstream film effectiveness is then taken into account using semiempirical models [10,11].…”

Section: One-dimensional Pirate Modelmentioning

confidence: 99%

Numerical Simulation of Transpiration Cooling for a High-Speed Vehicle with Substructure

2021

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“…with the distance along the vehicle's surface from the injection point, s from injector , the streamwise length of the injector, W, and the dynamic viscosity, µ [18]. Values denoted by ( * ) are evaluated at the temperature…”

Section: Appendix Lee's Model For the Heat Flux Distribution Around A...mentioning

confidence: 99%

“…Although transpiration cooling was already recognised in the 1950s [15,16], and a significant amount of research has been conducted since [11,13,[17][18][19][20][21], very few vehicles have employed this technique. To date, only one hypersonic transpiration cooled flight experiment has been carried out, namely SHEFEX II [5].…”

Section: Introductionmentioning

confidence: 99%

Tool for Rapid Transient Transpiration-Cooled Reentry Simulation

2020

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This paper presents a numerical model intended for a system study of transpiration cooled thermal protection systems. The code PIRATE (Porous Impulse Response Analysis for Transpiration cooling Evaluation) enables rapid transient calculations for thermal protection systems of hypersonic flight vehicles. In the code, semi-empirical aerodynamic correlations are employed. However, the code could also be used by applying higher fidelity inputs from CFD calculations for more complicated vehicle geometries. The wall temperature distribution is calculated by utilising the thermal impulse and step responses of porous media, increasing the calculation speed significantly. A heat flux balance is considered for a one-dimensional porous material. The code is validated with experimental data of plasma wind tunnel tests and the SHEFEX II flight experiment. The transient heating of a flat plate model in a steady state flow condition in the L2K plasma wind tunnel is assessed for both un-cooled and transpiration cooled cases. The SHEFEX II flight simulation accounts for transient external flow conditions * Post-doctoral research assistant, Hypersonics group, Oxford Thermofluids Institute, AIAA Member.

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Film cooling by injection into a turbulent boundary layer

Cited by 6 publications

References 2 publications

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

Numerical Simulation of Transpiration Cooling for a High-Speed Vehicle with Substructure

Tool for Rapid Transient Transpiration-Cooled Reentry Simulation

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