• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.10
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• pp.966-978
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• 2011

Transpiration cooling is the most effective cooling technique for the high-performance liquid rockets and air-breathing engines operating in aggressive environments with higher pressures and temperatures. When applying transpiration cooling, combustor liners and turbine blades/vanes are cooled by the coolant(air or fuel) passing through their porous walls and also the exit coolant acting as an insulating film. Practical implementation of the cooling technique has been hampered by the limitations of available porous materials. But advances in metal-joining techniques have led to the development of multi-laminate porous structures such as Lamilloy$^{(R)}$ fabricated from several diffusion-bonded, etched metal thin sheets. And also with the availability of lightweight, ceramic matrix composites(CMC), transpiration cooling now seems to be a promising technique for high-performance engine cooling. This paper reviews recent research activities of transpiration cooling and its applications to gas turbines, liquid rockets, and the engines for hypersonic vehicles.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.235-240
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• 2010

Transpiration cooling is the most effective cooling technique for liquid rocket and air-breathing engines operating in aggressive environments with higher pressures and temperatures. Combustor liners and turbine vanes are cooled by the coolant(air or fuel) passing through their porous walls and also the exit coolant acting as an insulating film. However, its practical implementation has been hampered by the limitations of available porous materials. The search for more practical methods of increasing the internal heat transfer within the walls has led to the development of multi-laminate porous structures, such as Lamilloy$^{(R)}$ and Transply$^{(R)}$. This paper reviews recent research activities of transpiration cooling for the propulsions of liquid rocket, gas turbine, and scramjet.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.224-227
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• 2011

In order to determine the enthalpy profile in the high temperature transpiration cooling test facility for the air-breating engine compartments, theoretical calculation and measurement for the flow of the test section are performed. The mass averaged enthalpy value determined by the heat balance and sonic throat methods is 10 MJ/kg. The centerline enthalpy value measured using the slug type copper calorimeter is 15 MJ/kg. Typically, the ratio of centerline and mass averaged enthalpy should be varies from 1.4 to 4. This facility has lower bound of enthalpy profile. It will be effective in testing of high temperature transpiration cooling.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.2
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• pp.46-56
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• 2013

The test facility with hot-air supply system is required to develop transpiration cooling materials and experimentally evaluate its performance. In the study, the facility consists of an arc-plasma generator, plenum chamber suppling cold air, and test section was designed and an internal flow analysis was executed. From CFD results, it was confirmed that the designed plenum chamber thermally safeties and ideally mixes with plasma gas and cold air in the chamber. In addition, validity of design for supplying homogeneous flow to the test section was confirmed by this analysis.

• Transactions of the Korean Society of Mechanical Engineers
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• v.12 no.5
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• pp.1130-1137
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• 1988

Heat transfer characteristics of evaporative transpiration cooling was investigated experimentally in the range of coolant mass flux, 0.002kg/m$^{2}$.sec~0.015m$^{2}$.sec. Glass beads, sand and copper particles were used as porous media and distilled water was used as a conant. The existence of evaporation zone was confirmed on this experimental conditions and its length increases with increasing article size and with decreasing mass flux. In order to get the low surface temperature, porous materials with high thermal conductivity is preferred when the panicle sizes are same, and small particles with low porosity is effective in case of the same material. Due to the relatively small coolant mass flux, evaporative transpiration cooling system could be stable by the capillary effect.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.1
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• pp.104-111
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• 1992

In this study, the heat transfer characteristics of the evaporative transpiration cooled system is analytically investigated considering the occurrence of the two-phase evaporation zone. Under the condition of the external heat input, analytical solutions of the three regions (i.e., vapor, liquid and two-phase evaporation zone) are respectively obtained using the matching conditions for the steady-state problem where properties are constant. As results, the length of the evaporation zone increases with increasing heat input and with decreasing mass flow rate. It also increases with increasing particle size, system porosity, thermal conductivity of material, inlet temperature and latent heat of coolant. The position of the lower interface of the evaporation zone have a lot of efforts on the evaporation zone length, the position of the upper interface penetrates deeper into the porous layer with lower thermal conductivity of porous material, higher system porosity and larger particle size.

• The KSFM Journal of Fluid Machinery
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• v.11 no.6
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• pp.64-68
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• 2008

막 냉각 연구를 위해 CFD를 이용할 때 적용 한계 및 그 타당성을 검증하고자 하였다. 이 글에서는 냉각공기공으로부터 분출된 냉각공기가 고온 고속으로 흐르는 주유동과 평판 사이에 벽면을 고온의 가스에 노출되는 것을 막기 위해 위치시킨 막냉각공기 흐름의 형태를 CFD를 이용하여 분석하였다. 모든 경계조건 및 격자계 그리고 검증 단계의 예까지 서술함으로써 이러한 CFD를 이용할 때 유용하게 적용될 방법들을 제공하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.7
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• pp.547-551
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• 2013

Mass averaged and core enthalpy in the arc jet flow are obtained experimentally. The experiment is made for the 150kW Huels type arc-jet applying the test condition for the research of gasturbine engine injection cooling technique. The mass averaged enthalpy value determined by the sonic throat method is 5.5MJ/kg. The core enthalpy value determined by the heat transfer rate method is 14.3MJ/kg. Based on result of experiment, the ratio of the core to mass averaged enthalpies is 2.6.

• Journal of Energy Engineering
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• v.23 no.3
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• pp.21-26
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• 2014

EU-APR1400, the Korean nuclear reactor design for European market adopts a so-called core catcher for ex-vessel molten corium retention and cooling as a severe-accident mitigation system. Sacrificial material, which controls melt properties and modifies melt conditions favorable for corium cooling and retention, is usually employed to protect core catcher body from molten corium. Since molten corium can be ejected through a breach of a reactor pressure vessel and impinged on the sacrificial material with enhanced heat transfer at a severe accident, it is very important to predict ablation rate of sacrificial material due to corium jet impingement accurately for core catcher design. In this paper, sacrificial-material ablation model based on boundary layer theory is suggested and compared with the experimental results by KAERI.

• Nuclear Engineering and Technology
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• v.26 no.2
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• pp.257-264
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• 1994

Experimental studies hate been peformed to investigate vapor explosion phenomena which may threaten the containment integrity during severe accidents in nuclear power plants. In this study, experimental equipment is constructed for vapor explosion experiments, and the vapor explosion experiments were conducted using water/R22. During the experiments, water/R22 interaction phenomena were observed using the high speed camera, and the explosion pressure and released mechanical energy were measured with pressure transducer and pressure relief tube. And the effects of some important parameters-hot liquid temperature, hot liquid injection velocity, hot liquid injection velocity, hot liquid injection time, and cold liquid depth-were investigated on the vapor explosion. Also, the experiment with grid was conducted to study reactor -vessel-lower-structure effect on fuel/coolant interaction. Water/R22 explosion conversion ratios were measured between 0.5∼1.6%.