• 한국추진공학회지
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• 제23권4호
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• pp.104-111
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• 2019

다단연소사이클 엔진은 가스발생기 기반의 개방형 엔진에 비해 성능이 좋기 때문에 현재 한국형발사체사업(KSLV-II)의 후속사업의 일환으로 선행연구가 진행 중이다. 기술검증시제 명칭의 TDM0A, TDM0B를 통해 다단연소사이클 엔진의 시동 조건과 연소 특성을 이해하고, 산화제 과잉 예연소기와 연소기 개발을 위한 연소 성능 시험이 수행되었다. 시험 데이터를 토대로 엔진 형상 모델 TDM1A를 제작하여 연소 시험을 수행했으며, 주연소기 연소압 91 bar, 터보펌프 회전수 28,000 rpm의 안정적인 결과로 개발요구조건을 만족하였다. 본 논문에서는 TDM0A부터 TDM1A까지의 개발과정과 특징에 대해 논하고자 한다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2005년도 제31회 KOSCO SYMPOSIUM 논문집
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• pp.148-155
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• 2005

In this study, Development of 300,000kcal/hr high velocity Injection burner with fuel multi-stage was performed using experiments. The characteristics of NOx emission in multi fuel/air staged combustor have been experimentally studied. The design concept of multi fuel/air staged combustor is creation of two separate flame, a primary flame is largest access air combustion and the secondary flame is complete combustion zone, where most of fuel bums. Experiments were performed on an industrial scale in a laboratory furnace and Liquefied Natural Gas(LNG) was used as primary and secondary fuels. Comparison of outlet NOx and outlet Temperature under various air rate and primary/ secondary fuel ratio was performed. The test demonstrated that NOx emission con be reduced by 70% in accordance with operating conditions.

• 한국항공우주학회지
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• 제44권7호
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• pp.576-584
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• 2016

본 연구는 다단 하이브리드 로켓의 낮은 비추력 성능을 향상시키는 방법으로 AP 첨가 추진제를 제안하고 있다. 추진제에 첨가된 AP 첨가비율 변화에 따라 다단 하이브리드 로켓의 비추력 성능 변화와 연료과농 연소특성 변화를 살펴보았으며, 이때 AP 첨가비율은 하이브리드 로켓의 연소 특징을 유지하기 위해 최대 15 wt%로 제한하였다. 결과에 의하면, AP 15 wt% 추진제는 AP 0 wt% 추진제와 비교하여 비추력 성능이 약 3% 향상되었다. 또한, 동일한 연소온도를 유지함에도 불구하고, AP 첨가비율을 증가시키면 산화제 유입량, O/F비 변화량, 그리고 연소압력은 감소하며 반경반향 온도 분포가 좋아지는 등 다단 하이브리드 로켓의 성능향상에 긍정적인 효과가 나타났다. 그러나 오직 AP를 추진제에 첨가하는 것만으로 다단 하이브리드 로켓의 비추력 성능을 일반 화학로켓의 수준으로 향상시키는 것이 매우 어려운 일임을 고려할 때, 추가적으로 금속입자 첨가를 통해 비추력 성능을 향상시킬 계획이다.

• 한국항공우주학회지
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• 제47권7호
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• pp.517-524
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• 2019

진공추력 88톤급 다단연소 사이클 로켓엔진의 시스템 설계를 수행하였다. 엔진 구성품에 대한 성능 평가는 기존의 연구를 활용하였으며 수렴된 엔진 시스템 성능을 구할 수 있는 알고리즘을 제안하였다. 본 연구 방법은 RD-180에 대한 기존의 연구와 비교함으로써 검증하였다. 본 연구는 가격 경쟁력을 고려하면서 성능 개선을 달성하기 위하여 한국형발사체 75톤 엔진의 개발 이력을 최대한 승계하였다. 엔진의 제작 난이도, 비용 그리고 성능 개선을 고려하여 연소압력 12MPa을 적용하였고 결과로써 23.4s의 진공비추력 향상을 얻을 수 있었다.

• 한국추진공학회지
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• 제26권6호
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• pp.10-20
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• 2022

본 연구에서는 케로신 다단연소사이클 엔진용 예연소기를 설계하기 위해, 고압의 산화제 과잉 조건에서 예연소가스를 계산하고 냉각유로에서 극저온 유체의 복합열전달 및 수력 특성을 해석할 수 있는 설계코드를 개발하였다. 사용자 편의성과 범용성을 가진 오픈 소스 라이브러리 Cantera를 활용하였으며, 실제유체의 열역학/전달 상태량을 정확히 계산하기 위해 관련 소스 코드들을 새로 작성하여 Cantera에 추가하였다. 현재 예비설계 중인 100톤급 부스터 엔진용 예연소기에 적용하였으며, CFD 해석결과와 비교를 통해 설계코드로서의 예측 정확도와 활용성을 확인하였다.

• 한국자동차공학회논문집
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• 제11권6호
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• pp.73-79
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• 2003

The characteristics of NOx emission in multi fuel/air staged combustor have been experimentally studied. The design concept of multi fuel/air staged combustor is creation of two separate flame, a primary flame is act as a pilot flame for the secondary combustion stage combustion zone, where most of fuel burns. Experiments were performed on a semi-industrial scale (thermal input 0.233 ㎿) in a laboratory furnace and Liquefied Petroleum Gas(LPG) was used as primary and secondary fuels. The study included parametric study to identify the optimum operating conditions which are primary/secondary fuel ratio, primary/secondary air ratio, primary swirl intensity and secondary swirl intensity for reducing NOx emission. The test demonstrated that NOx emission can be reduced by >70% in accordance with operating conditions.

• 대한기계학회논문집B
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• 제28권4호
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• pp.389-394
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• 2004

An experimental study on the NOx formation of LNG flame in fuel staged combustor has been studied. The design concept of multi fuel/air staged combustor is creation of two separate flame, a primary flame is a act as a pilot flame for the secondary combustion stage combustion zone, where most of fuel bums. Experiments were performed on a semi-industrial scale (thermal input 0.233 MW) in a laboratory furnace and Liquefied Natural Gas(LNG) was used as a primary and secondary fuels. This study included parametric study to identify the optimum operating conditions which are primary/secondary fuel ratio, and primary/secondary air ratio for reducing NOx emission with two types of nozzle. The test demonstrated that NOx emission can be reduced by >70% in accordance with operating conditions.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.161-166
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• 2001

An Experimental study on the NOx formation of LNG flame in fuel staged combustor has been studied. The design concept of multi fuel/air staged combustor is creation of two separate flame, a primary flame is act as a pilot flame for the secondary combustion stage combustion zone, where most of fuel burns. Experiments were performed on a semi-industrial scale (thermal input 0.233 MW) in a laboratory furnace and Liquefied Natural Gas(LNG) was used as primary and secondary fuels. The study included parametric study to identify the optimum operating conditions which are primary/secondary fuel ratio, and primary/secondary air ratio for reducing NOx emission with two types of nozzle. The test demonstrated that NOx emission can be reduced by >70% in accordance with operating conditions.

• 연구논문집
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• 통권31호
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• pp.23-43
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• 2001

An experimental investigation on the reduction of nitrogen oxide emission from swirling, turbulent diffusion flames was conducted using multi air staged combustor, The combustor utilizes swirler to dampen fuel/air mixing, allowing an extended residence time for fuel pyrolysis and fuel-N conversion chemistry in an locally fuel-rich environment prior to burnout. This process also allow to reduce thermal NOx formation to lessen the temperature of reaction zone. The aerodynamic process therefore emulates the conventional staged combustion process, but without the need for the physically separate fuel-rich and -lean stages. Parametric studies on the ratios of each staged air and droplet size were carried out the feasibility of fuel/air mixing for low NOx combustion with diesel and pyridine mixed diesel fuel oil.

• 대한기계학회논문집B
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• 제25권11호
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• pp.1594-1605
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• 2001

In this study, a numerical simulation was developed which was capable of predicting the characteristics of NO formation in pilot scale combustor adopting the air-staged burner flame. The numerical calculation was constructed by means of establishing the mathematical models fur turbulence, turbulent combustion, radiation and turbulent nitric oxide chemistry. Turbulence was solved with standard k-$\xi$ model and the turbulent combustion model was incorporated using a two step reaction scheme together with an eddy dissipation model. The radiative transfer equation was calculated by means of the discrete ordinates method with the weighted sum of gray gases model for CO$_2$and H$_2$O. In the NO chemistry model, the chemical reaction rates for thermal and prompt NO were statistically averaged using the $\beta$ probability density function. The results were validated by comparison with measurements. For the experiment, a 0.2 MW pilot multi-air staged burner has been designed and fabricated. Only when the radiation was taken into account, the predicted gas temperature was in good agreement with the experimental one, which meant that the inclusion of radiation was indispensable for modeling multi-air staged gas flame. This was also true of the prediction of the NO formation, since it heavily depended on temperature. Subsequently, it was found that the multi-air staged combustion technique might be used as a practical tool in reducing the NO formation by controlling the peak flame temperature.