• Title/Summary/Keyword: Cooling Kerosene

Search Result 67, Processing Time 0.023 seconds

Review on Kerosene Fuel and Coking (케로신 연료 및 코킹에 대한 검토)

  • Lee, Junseo;Ahn, Kyubok
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.24 no.3
    • /
    • pp.81-124
    • /
    • 2020
  • In liquid oxygen/kerosene liquid rocket engines, kerosene is not only a propellant but also plays a role as a coolant to protect the combustion chamber wall from 3,000 K or more combustion gas. Since kerosene is exposed to high temperature passing through cooling channels, it may undergo heat-related chemical reactions leading to precipitation of carbon-rich solids. Such kerosene's thermal and fluidic characteristic test data are essential for the regeneratively cooled combustion chamber design. In this paper, we investigated foreign studies related to regenerative cooling channel and kerosene. Starting with general information on hydrocarbon fuels including kerosene, we attempted to systematically organize sedimentary phenomena on cooling channel walls, their causes/research results, coking test equipments/prevention methods, etc.

A Study on the Cooling Mechanism in Liquid Rocket Engine of 10tf-thrust Level using Kerosene as a Fuel (케로신을 연료로 하는 10톤급 액체로켓엔진의 냉각 기구에 관한 연구)

  • 한풍규;조원국;조용호
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2003.10a
    • /
    • pp.83-88
    • /
    • 2003
  • An analytical study was carried out to evaluate the regenerative cooling characteristics in the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel. As a supplementary cooling method, a radiative cooling was applied to the nozzle extension. It was found out from this work that the cooling system with the regenerative and radiation cooling only is not adaptable as a cooling method for the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel for the 2nd stage of the space launch vehicle. So, additional cooling method, curtain cooling was introduced and analyzed. Curtain cooling was very effective to reduce the thermal and thermo-structural instability.

  • PDF

Evaluation on the Regenerative Cooling Characteristics in Liquid Rocket Engine of 10tf-thrust using Kerosene and Liquid Oxygen as a Propellant (케로신과 액체산소를 추진제로 하는 10톤급 액체로켓엔진의 재생냉각 특성 평가)

  • Han, Poong-Gyoo;Cho, Won-Kook;Cho, Yong-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.32 no.4
    • /
    • pp.111-117
    • /
    • 2004
  • An analytical study was carried out to evaluate the regenerative cooling characteristics in the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel. As a supplementary cooling method, a radiative cooling was applied to the nozzle extension. It was found out from this work that the cooling system with the regenerative and radiation cooling only is not adaptable for the liquid rocket engine of a 10tf-thrust level using kerosene as a fuel for the $2^{nd}$ stage of the space launch vehicle, with the viewpoint of the thermal and thermo-structural instability and the excessive pressure drop in the cooling channel.

A Study on Measurement and Elimination Methods of Dissolved Nitrogen in Kerosene (케로신 내 용존질소 측정 및 제거 방법 연구)

  • Lee, Wongu;Kim, Seong Lyong;Ahn, Kyubok
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.22 no.6
    • /
    • pp.142-148
    • /
    • 2018
  • To improve the performance of a launch vehicle, kerosene, a launch vehicle fuel, undergoes a densification process. Liquid nitrogen injection cooling is an effective densification method which has a simple system and is inexpensive. During the cooling process, however, nitrogen may dissolve in the kerosene, possibly resulting in changes to fuel properties. Therefore, it is essential to measure and eliminate the amount of dissolved nitrogen in the kerosene. In this study, the vacuum extraction principle is introduced to measure the content of dissolved nitrogen in the kerosene. In addition, the experimental results, which used a designed/manufactured nitrogen sampling device, are described. From the results, the validity of the nitrogen sampling device and the dissolved nitrogen measurement/elimination methods was demonstrated.

A Case Study on the Design of Kerosene-LOx Liquid-Propellant Rocket Engines for Performance Enhancement (케로신-액체산소 액체로켓엔진의 성능향상 설계안 사례 조사)

  • Lee, Seon-Mi;Moon, In-Sang;Lee, Soo-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2011.04a
    • /
    • pp.12-15
    • /
    • 2011
  • The most widely used kerosene-LOx liquid-propellant rocket engines in these days have a similar engine schematic to those of the past because of the development cost and the reliability. The efficiency of engines could be increased by the factors such as a cooling method, engine cycles, shape of cooling channels, additional coolant and so on. In this article, it is described that some design ideas for performance enhancement by exchange kerosene with LOx of a coolant.

  • PDF

Combustion Performance of a Full-scale Liquid Rocket Thrust Chamber Using Kerosene as Coolant (실물형 액체로켓엔진 연소기 케로신냉각 연소시험 성능결과)

  • Han, Yeoung-Min;Kim, Jong-Gyu;Moon, Il-Yoon;Seo, Seong-Hyeon;Choi, Hwan-Seok;Lee, Soo-Yong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2006.11a
    • /
    • pp.163-168
    • /
    • 2006
  • The combustion performance tests of a 30 tonf-class full-scale combustion chamber performed with kerosene as a coolant were described. The combustion chamber has chamber pressure of 53bara and propellant flow mass rate of 90kg/s. Since it was first firing test for 30tonf-class combustion chamber using kerosene cooling, kerosene coolant mass flow rate of 32kg/s which correspond to 120% of design mass flow rate were performed. Then, the firing test with kerosene mass flow rate of 25kg/s were successfully performed. The test results are described and the results showed that the kerosene cooling performance of this combustion chamber is sufficient and the firing test with regenerative cooling is feasible.

  • PDF

Experimental Study on Kerosene Heat Transfer Characteristics Using Simulating Cooling Channels (모사 냉각채널을 이용한 케로신 열전달 특성에 대한 실험적 연구)

  • Lee, Bom;Lee, Wongoo;Song, Yoonho;Hwang, Donghyun;Ahn, Kyubok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2017.05a
    • /
    • pp.643-646
    • /
    • 2017
  • In a liquid rocket engine using hydrocarbon fuels, cooling of the combustion chamber wall is necessary to prevent the combustion chamber wall from melting or structurally deforming due to high heat flux. Among the various methods, regenerative cooling, which uses fuel as a coolant and then injects it into the combustion process, has good performance. This study investigated the heat transfer characteristics of kerosene as a coolant by varying the copper cross-sectional area, the flow rate in the channel, and the current applied to the channel. Convective heat transfer occurred rapidly when the cross-sectional area of the copper channel was small and when the kerosene flow velocity was fast.

  • PDF

Numerical analysis on curtain cooling in Liquid Rocket Engine of 10tf-thrust Level using Kerosene as a Fuel (케로신을 연료로 하는 10톤급 액체로켓엔진의 막 냉각에 관한 해석적 연구)

  • 남궁혁준;한풍규;조원국
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2003.10a
    • /
    • pp.78-82
    • /
    • 2003
  • The cooling mechanism for a regenerative cooling liquid rocket engine of 10tf-thrust using kerosene as a fuel was studied from the viewpoint of curtain cooling. Based on the concept of a highly-stratified gas flow in the combustion chamber, the cross section of the combustion chamber was spilt into 2 independent parts, core and exterior part. Additional fuel is injected into the exterior section and gas temperature can be reduced in the exterior section. Consequently, the heat flux into the coolant and wall temperature are reduced and the thermal stability of a liquid rocket engine could be improved.

  • PDF

A Study on the Cooling Mechanism in Liquid Rocket Engine of 10tf-Thrust Level using Kerosene as a Fuel (케로신을 연료로 하는 10톤급 액체로켓엔진의 냉각 기구에 관한 연구)

  • Han, Pung-Gyu;Nam-Gung, Hyeok-Jun;Jo, Won-Guk
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.31 no.10
    • /
    • pp.66-72
    • /
    • 2003
  • The cooling mechanism for a liquid rocket engine of 10tf-thrust using kerosene as a fuel was studied from the viewpoint of both the regenerative and curtain cooling. Based on the concept of a highly-stratified gas flow in the combustion chamber, the cross section of the combustion chamber was spilt into 2 independent parts, core and exterior part. Additional fuel is injected into the exterior section and gas temperature can be reduced in the exterior section. Consequently, the heat flux into the coolant and wall temperature are reduced and the thermal stability of a liquid rocket en g i.ne could be improved.

Prediction for Heat Transfer Characteristics of Supercritical Kerosene Using Mixture Surrogate (대체 혼합물을 이용한 케로신의 초임계 열전달 특성 예측)

  • Lee, Sanghoon;Yang, Inyoung;Park, Boo-min;Lee, Jinhee
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2017.05a
    • /
    • pp.294-296
    • /
    • 2017
  • In this study heat transfer characteristics of kerosene at supercritical condition was predicted. And a sample heat transfer calculation was performed using this result. The prediction was done by assuming kerosene as a mixture of a number of pure substances, and combining the thermodynamic properties of them, using NIST SUPERTRAPP. A regeneratively cooled supersonic combustor will be desinged using the resultant thermophysical property data of supercritical kerosene. Comparing with the combustion test results of the regenerative cooling combustor, the predicted thermophysical property data will be verified.

  • PDF