• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.6
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• pp.17-23
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• 2009

The survivability of the temporary nozzle extension for an accurate thrust measurement in a full-scaled combustor has been investigated through thermal analyses. The effects of nozzle extension materials and the thickness of thermal barrier coating (TBC) have been elucidated. It has been found that thermal survivability cannot be guaranteed without TBC. The maximum temperature of the nozzle extension decreased with increasing TBC thickness. For hot firing tests, the TBC is thought to be indispensable to the thermo-structural survivability of the nozzle extension made of steel.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.271-275
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• 2010

Forming tool design is carried out for a manufacturing a outer shell structure of the nozzle extension of regenerative cooling thrust chamber. The method which manufactures outer shell structure of nozzle extension is a metal forming process using thin plate. Because the configuration of outer shell structure is changed after forming process by springback effect, the outer shell structure can't be exactly formed with the same forming tool as configuration of the nozzle extension. Therefore forming tool design considering springback effect is necessary for manufacturing the outer shell structure of the nozzle extension. In this study, new designed forming tool configuration was generated to decrease the errors between nozzle contour and formed structure. The analysis results show that the errors between nozzle contour and formed structure is significantly decreased using the new designed forming tool.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.291-295
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• 2011

Thermo-structural analysis was performed for a radiation-cooled nozzle extension of thrust chamber. A Niobium alloy that is known to be a high-performance refractory alloy was used. Since area ratio of the nozzle extension is larger than that of nozzle divergence part, its size also becomes larger. For this reason, it is important to minimize the thickness of nozzle extension to reduce its weight. For the purpose of weight minimization, the thickness of nozzle extension was varied from 1.0 mm to 0.4 mm and structural stability was evaluated for each case. Analysis results showed that nozzle extension with thickness of 0.4 mm is structurally stable for the operation condition. The effect of combustion-included vibration will be additionally considered in the future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.32-32
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• 2000

잠입노즐은 로케트 추진기관의 길이 및 중량을 감소시켜 체계설계의 관점에서 볼 때 많은 이점을 제공한다. 본 연구에서는 3단형 과학로케트 원지점 차넣기 모타(apogee kick motor)에 적용하기위한 잠입노즐의 기초기술 개발에 주안점을 두었다. 고고도에서 저속으로 회전하며 비행하는 원지점 차넣기 모타를 제작하기위해서 체계 요구성능에 의해 예상된 실물형의 50% 크기에 해당하는 축소형 잠입노즐을 제작하였다. 잠입노즐은 잠입부의 내외부가 고온의 추진제 연소가스에 노출된 상태에서 노즐 내부 압력 외에 연소실압에 의한 외부압력이 작용하므로 이를 고려한 열 및 구조설계가 중요하다. 본 연구에서는 노즐 수렴부와 목부에 일체형 그라파이트 소재를 적용하고 확장부 내열재 및 잠입부 배면내열재에 탄소/페놀 복합재를 노즐 내열재로 사용하였다. 그리고 이들의 구조적 지지를 위해 스틸구조물을 적용하였다. 적용된 스틸구조물에는 K형 열전쌍을 이용해 내열재와 구조물 온도를 측정할 수 있는 관통구멍 및 나사부를 구조물 외변에 가공하였다. 열전쌍은 노즐 목직경의 2, 4배 되는 확장부 내열재 단면위치의 2mm와 4mm 깊이와 구조물 내면 및 외면의 4개소에 열전쌍을 부착하여 지상연소시험시 노즐 내열재와 구조물의 온도분포를 관찰한다. 그리고 노즐 조립시 확장부 내열재와 구조물에 각 각 반원형 홈을 내어 여분의 접착제가 원형 홈에 밀려들어가 경화되어 노즐 기밀유지와 체결력을 향상시킬 수 있는 원형공간 접착제 충전 공법을 적용하여 실제모타에 대한 적용가능성을 지상연소시험을 통해 확인한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.428-432
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• 2010

A study on the forming characteristics of outer shell structure for thrust chamber nozzle extension has been performed. In order to identify anisotropy of cold rolled sheet metal, three types of tensile specimens according to the direction to the sheet rolling axis were prepared and tested, and Landford's values were obtained using the results and applied to structural analysis. Forming characteristics of the outer shell structure of the nozzle extension are investigated through manufacturing and forming of the full scale outer shell structures, and strain values obtained by the forming processes are compared to the numerical analysis results. The results obtained by this study will be utilized to design forming tools and processes for manufacturing other outer shell structures which have a bigger expansion area ratio.

• Current Industrial and Technological Trends in Aerospace
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• v.9 no.1
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• pp.139-149
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• 2011

The combustion chamber and nozzle of a liquid rocket engine need thermal protection against the high temperature combustion gas. The nozzle extension of a high-altitude engine also has to be compatible with high temperature environment and several kinds of cooling methods including gas film cooling, ablative cooling and radiative cooling are used. Especially for an upper-stage nozzle extension having a large expansion ratio, the weight impact on the launcher performance is crucial and it necessitated the development of light-weight refractory material. The present survey on the nozzle extension materials employed in the liquid rocket engines of USA, Russia and European Union has revealed a trend that the heavier metals like stainless steels and titanium alloys are being substituted with light weight carbon fiber or ceramic matrix composite materials.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.3
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• pp.97-103
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• 2012

The combustion chamber and nozzle of a liquid rocket engine should be protected from the high temperature combustion gas generated by the chamber. An upper-stage nozzle extension has a large expansion ratio, therefore, The light-weight refractory materials have been used since the weight impact on the launcher performance is crucial. Gas film cooling method was used before, but was not applicable nowadays. Ablative cooling method and radiative cooling method with niobium alloy, Ni-based superalloy and ceramic based composite have been used to this day.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.505-509
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• 2011

The combustion chamber and nozzle of a liquid rocket engine should be protected from the high temperature combustion gas generated by the chamber. An upper-stage nozzle extension has a large expansion ratio, therefore, The light-weight refractory materials have been used since the weight impact on the launcher performance is crucial. Gas film cooling and ablative cooling methods were used before, but were not applicable nowadays. Radiative cooling method with niobium alloy, Ni-based superalloy and ceramic based composite has been used to this day.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.3
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• pp.68-75
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• 2017

Dual bell nozzle is a type of altitude compensation nozzle, which is a nozzle that minimize the losses of the specific impulse at the off-design point of a typical bell nozzle. In this paper, numerical computations are performed to understand the transition characteristics of dual bell nozzles with fixed expansion ratios. The major design variables are the length of extension and the angle of inflection. As the length of the extension increased, the transition altitude and transition duration increased and the reduction of the thrust coefficient decreased. As the angle of inflection increased, the transition altitude and transition duration decreased and the reduction of the thrust coefficient increased.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.5
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• pp.11-23
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• 2022

For the design of the shortened ED(Expansion Deflection) nozzle, a numerical study of ED nozzle was performed according to the length reduction methods. The first method is to reduce the extension length of the ED nozzle with 80% bell nozzle length by 10%, 20% and 30%. The second method is to shorten the extension length by increasing the nozzle throat angle. Due to the increase in the curvature of the contour as the length shortened, the decrease in the nozzle exit velocity between the ED nozzle with 80% bell nozzle length and the ED nozzle in the first method was reduced, and the thrust become similar. The ED nozzle of the second method increased the thrust by increasing the nozzle exit velocity compared to the ED nozzle with 80% bell nozzle length.