• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.2
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• pp.52-59
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• 2014

The effect of ceramic thermal barrier coating thickness on the cooling performance of a liquid-propellant rocket engine combustor has been investigated through combustion/cooling performance analysis whose results verified against measured data from hot-firing tests. Also have been confirmed the effects of film cooling amount near the face plate on the coolant temperature and on the thermal barrier coating surface temperature. Some important points to be considered for designing cooling schemes for regeneratively cooled rocket engine combustor have been drawn and reviewed from present study and further verification of the analysis tool should be performed in the future.

• Journal of the Korean Society for Nondestructive Testing
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• v.36 no.3
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• pp.202-210
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• 2016

A thermal barrier coating (TBC) has been widely applied to machine components working under high temperature as a thermal insulator owing to its critical financial and safety benefits to the industry. However, the nondestructive evaluation of TBC damage is not easy since sensing of the microscopic change that occurs on the TBC is required during an evaluation. We designed an eddy current probe for evaluating damage on a TBC based on the finite element method (FEM) and validated its performance through an experiment. An FEM analysis predicted the sensitivity of the probe, showing that impedance change increases as the TBC thermally degrades. In addition, the effect of the magnetic shield concentrating magnetic flux density was also observed. Finally, experimental validation showed good agreement with the simulation result.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2012.10a
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• pp.547-548
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• 2012

• Journal of the Korean Society for Precision Engineering
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• v.30 no.8
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• pp.802-808
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• 2013

Thermal barrier coating (TBC) is used to protect substrates and extend the operating life of gas turbines in power plant and aeronautical applications. The major causes of failure of such coatings is spallation, which results from thermal stress due to a thermal expansion coefficient mismatch between the top coating and the bond coating layers. In this paper, the effects of the material properties and the thickness of the top coating layer on thermal stresses were evaluated using the finite element method and the equation for the thermal expansion coefficient mismatch stress. In addition, we investigated a design technique for the top coating whereby thermal resistance is exploited.

• Transactions of the KSME C: Technology and Education
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• v.4 no.2
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• pp.93-99
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• 2016

High pressure nozzles and turbines of a gas turbine engine should be required to be operated under extreme operating conditions in order to maximize the performance. Engine manufactures have utilized nickel-base superalloys, enhanced cooling design, and thermal barrier coating techniques to overcome them and furthermore, material modeling, finite element analysis, optimization techniques, and etc. have been utilized widely for elaborate predictions. We aim to evaluate the effects on the low cycle fatigue life of the high pressure turbine blade caused by thermal barrier coatings and the cooling design of the endwall of the first stage turbine nozzle. To achieve it, the structural analysis, which utilized the results of conjugate heat transfer analysis as loading boundary conditions, was performed and then the results were the input for the assessment of low cycle fatigue life at several critical zones.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.197-204
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• 2004

A design of regenerative cooling system of 30 ton level thrust combustion chamber for ground test has been performed. The 1-D design code has been validated by comparing with the heat flux of the NAL calorimeter for high chamber pressure and water-cooling performance of the ECC engine of MOBIS. The present design code has been confirmed to predict accurately the heat flux and water-cooling performance for high chamber pressure condition. The maximum hot-gas-side wall temperature is predicted to be about 720 K without thermal barrier coating and the coolant-side wall temperature is less than the coking temperature of RP-1. The coolant temperature rises nearly 100 K with thermal barrier coating when Jet-A1 is used as coolant.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.67-72
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• 2004

A regenerative cooling system has been designed through empirical 1-D analysis for a liquid rocket engine of 30-ton-level thrust. The hot-gas-side wall temperature from 1-D analysis shows 100K difference compared to 3D CFD analysis. Two variations of design with same cooling performance are suggested for different maximum channel widths i.e., 4mm and 2mm. The coolant pressure drop of the latter design is higher by 20%. The maximum liner temperature is about 700K when TBC and the thermal resistance of carbon deposit are considered. So film cooling is recommended to increase the cooling capacity as the present cooling capacity is insufficient

• Proceedings of the Korean Vacuum Society Conference
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• 2000.02a
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• pp.36-36
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• 2000

KSTAR 토카막은 보조가열 장치로 2005년까지 1대(최종적으로는 2대)의 중성입자빔 입사장치(NBI)를 설치하여 장치의 기본 설계값에 도달할 예정이다. KSTAR NBI는 3개의 이온원을 가지고 있으며 총 수소 유입량은 70 Torr.L/s인 반면 고속 중성 입자빔량은 모두 11 Torr.L/s로 기체 배기량은 59 Torr.L/s에 달하고 압력은 장소에 따라 10-5~10-6 Torr로 유지되며 총배기속도가 1~2$\times$106 L인 펌프가 필요하다. 이때 크라이오 펌프(cryopump) 방식이 거의 유일한 해결책이라고 할 수 있다. 크라이오 펌프는 고속 입자빔 수송로의 양편에 각각 설치되는데 총면적 30m2 내외의 극저온 냉각판(cryo-pnael)들과 이를 상온 열복사로부터 보호하기 위한 열차폐(thermal shield) 및 흡기구 배플(baffle), 그리고 적절한 냉각장치로 구성된다. 시운전 단계에서는 15K GM 냉동기와 활성탄이 부착된 냉각판을 사용하는 방식과 4K GM 냉동기로 냉각하는 방식이, 최종 운전단계에서는 3.7K 액체 헬륨을 사용하는 방식이 고려되고 있다. 크라이오 펌프의 구조설계에 앞서 우선 배기속도, 흡？량, 작동압력, 냉각판 온도, 열손실량 등 설계사양을 확정하고 정리하는 일이 진행되고 있다. 또 냉각방식과 상관없이 동일한 개념으로 만들어지는 배플과 열차폐의 최적설계를 위한 몬테카를로 계산과 열전도 계산을 병행하고 있다. 이 곳에서는 KSTAR NBI 장치의 주배기계로서 사용될 크라이오 펌프의 설계방향과 전반적인 구조 및 예상성능 등에 대해 발표하려고 한다.

• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.226-226
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• 2012

국산 크라이오 펌프를 개발하는 사업이 1단계 3년을 지나 올해 2단계에 접어들었다. 그동안 기계연을 중심으로 맥동관형 냉동기 개발에 주력하면서 저온성능 향상에서 큰 진전을 보였고 2단계에서는 우성진공의 주도하에 펌프의 상용화를 목표로 하고 있다. 펌프는 냉동기 뿐만 아니라 활성탄 어레이와 열차폐 및 배플이 잘 설계되어야 최적의 배기성능을 나타낼 수 있다. 우선은 펌프의 목표성능을 좀 더 구체화할 필요가 있고, 각 부품들의 상세한 형상결정에 앞서 개략적인 배치설계에 대해 성능을 예측하여 목표성능과 비교하고 설계를 수정하는 것을 반복하여 전반적으로 구조설계의 최적화를 완성하는 것이 급선무이다. 본 발표에서는 이런 구조설계 최적화 작업의 처음 결과와 개발중인 크라이오 펌프의 최종 성능 목표치에 대해 소개한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.3
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• pp.1-6
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• 2007

A 3-tonf-class high pressure sub-scale combustor was designed and manufactured to study the performance improvement of combustor. The combustor consists of a combustion chamber with film cooling, thermal barrier coating and water cooling channels to prevent thermal demage of the hardware and an injector head with 37 coaxial swirl injectors. Hot-firing tests were carried out at the design point with varying flow rate for film cooling. The test result revealed that the increase of film cooling flow rate decreases the combustion performance, but in the cases of similar film cooling flow rates, the combustion performance is dependent on the mixture ratio of main injector excluding the film cooling flow rate.