• Title/Summary/Keyword: Combustor Chamber

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CFD Numerical Calcultion for a Cavity Matrix Combustor Applying Biogas (바이오가스 적용 캐비티 매트릭스 연소기 CFD 수치연산)

  • CHUN, YOUNG NAM;AN, JUNE
    • Transactions of the Korean hydrogen and new energy society
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    • v.33 no.5
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    • pp.598-606
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    • 2022
  • With the advancement of industry, the use of various sustainable energy sources and solutions to problems affecting the environment are being actively requested. From this point of view, it is intended to directly burn unused biogas to use it as energy and to solve environmental problems such as greenhouse gases. In this study, a new type of cavity matrix combustor capable of low-emission complete combustion without complex facilities such as separation or purification of biogas produced in small and medium-sized facilities was proposed, and CFD numerical calculation was performed to understand the performance characteristics of this combustor. The cavity matrix combustor consists of a burner with a rectangular porous microwave receptor at the center inside a 3D cavity that maintains a rectangular parallelepiped shape composed of a porous plate that can store heat in the combustor chamber. As a result of numerical calculation, the biogas supplied to the inlet of the combustor is converted to CO and H2, which are intermediate products, on the surface of the 3D matrix porous burner. And then the optimal combustion process was achieved through complete combustion into CO2 and H2O due to increased combustibility by receiving heat energy from the microwave heating receptor.

Domestic and Foreign Research Trends in Rocket Combustor Instability (국내외 로켓연소기의 연소불안정 연구동향 분석)

  • Bae, Jinhyun;Jeong, Seokgyu;Yoon, Youngbin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.47-53
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    • 2017
  • One of the most common causes of failure of space launch vehicles is combustion instability. Combustion instability is a phenomenon that the pressure perturbation inside the combustion chamber is greatly amplified due to the interaction of the pressure perturbation inside the combustion chamber and the heat release perturbation. When this phenomenon becomes worse, an engine failure or launch vehicle crash occurs. In order to predict and avoid such combustion instability, understanding of the phenomenon is indispensable, and numerical, theoretical, and experimental approaches to combustion instability have been carried out worldwidely.

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The Low $NO_{x}$ Characteristics of a Lean Premixed Gas Turbine Combustor (희박연소를 이용한 가스터빈 연소기의 저 $NO_{x}$ 특성)

  • Son, M.G.;Ahn, K.Y.;Kim, H.S.;Kim, Y.M.
    • Proceedings of the KSME Conference
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    • 2001.06d
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    • pp.66-70
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    • 2001
  • The combustion characteristics have been investigated to develop the low $NO_{x}$ gas turbine combustor. The lean premixed combustion technology was applied to reduce the $NO_{x}$ emission. Also, the conventional combustor was designed and tested for the baseline of low $NO_{x}$ combustor performance. The test was conducted at the condition of high temperature and ambient pressure. The combustion air which has the temperature of 500K were supplied to the combustor through the air preheater. The temperature and emissions of $NO_{x}$ and CO were measured at the exit of combustor. The premixing chamber can be operated very lean condition of equivalence ratio around 0.35. The $NO_{x}$ was decreased with decreasing the equivalence ration. The CO was decreased with decreasing the equivalence ratio, but the CO was increased with decreasing the equivalence ratio below 0.45. But, at the very lean condition of equivalence ratio below 0.35 both NOx and CO were increased because of the flame unstability. The $NO_{x}$ was decreased slightly and CO was increased with increasing inlet air flowrate. This results can be used to determine the size of combustor. The low $NO_{x}$ combustor has lower values of $NO_{x}$ and CO compared with conventional one. Consequently the performance of combustor shows the possibility of the application to the gas turbine system.

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Hot- Fire Injector Test for Determination of Combustion Stability Boundaries Using Model Chamber

  • Sohn Chae Hoon;Seol Woo-Seok;Shibanov Alexander A.;Pikalov Valery P.
    • Journal of Mechanical Science and Technology
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    • v.19 no.9
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    • pp.1821-1832
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    • 2005
  • This study realizes the conceptual method to predict combustion instability in actual full-scale combustion chamber of rocket engines by experimental tests with model (sub-scale) chamber. The model chamber was designed based on the methodologies proposed in the previous work regarding geometrical dimensions and operating conditions, and hot-fire test procedures were followed to obtain stability boundaries. From the experimental tests, two instability regions are presented by the parameters of combustion-chamber pressure and mixture (oxidizer/fuel) ratio, which are customary for combustor designers. It is found that instability characteristics in the chamber with the adopted jet injectors can be explained by the correlation between the characteristic burning or mixing time and the characteristic acoustic time: In each instability region, dynamic behaviors of flames are investigated to verify the hydrodynamically-derived characteristic lengths of the jet injectors. Large-amplitude pressure oscillation observed in upper instability region is found to be generated by lifted-off flames.

Rocket Engine Test Facility Improvement for Hot firing test of a Combustor in the 30-tonf class (30톤급 연소기의 연소시험을 위한 설비 개량)

  • Lee Kwang-Jin;Seo Seonghyeon;Lim Byoungjik;Moon Il-Yoon;Han Yeoung-Min;Choi Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.313-317
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    • 2005
  • The facility improvement for hot firing test of combustion chamber having thrust of 30-tonf class and chamber pressure of 60bara were performed at ReTF in KARI. The KSR-III main engine having combustion pressure of 13bara and thrust of 12.5tonf had been successfully tested in this facility. To increase the capability of the facility, the feeding and the trust measurement system have been modified. The modification of the feeding system plays also a role of ensuring the stability of propellant supply and two step ignition sequence of combustion chamber. The one-axis thrust measurement system of up to 60tons has been newly manufactured and installed in test stand and the water/kerosene supply lines with high pressure vessel of $4m^3$ and gas nitrogen vessel of $10m^3$ have been designed for regenerative cooling system. The results of cold flow test show that this facility has been successfully improved to satisfy the requirement for hot firing test of high performance combustor.

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Combustion Characteristics associated with a Swirl Chamber and Nozzle Length of Coaxial Swirl Injectors (동축스월분사기에서 와류실 유무 및 노즐길이에 따른 연소특성 변화)

  • Lim Byoung-Jik;Seo Seong-Hyeon;Choi Hwan-Seok;Choi Young-Hwan;Lee Seok-Jin;Kim Yoo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2005.11a
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    • pp.335-340
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    • 2005
  • A study on the variation of combustion characteristics by injector geometries was conducted. Coaxial swirl injectors were used. Existence of swirl chamber and variation of a nozzle length become key parameters. Injectors were identified as open, closed and mixed type by existence of swirl chamber. Variation of nozzle length was made extruding the both nozzle along the axis while other design parameters remain the same. A uni-element combustor with ablative material liner and a water cooled nozzle made by oxygen free copper with outer stainless steel casing were used.

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Combustion Characteristics of Sub-scale Combustors on the variation of propellant mass flow and injector arrangement (분사기 배열과 추진제 유량 변화에 의한 축소형 연소기의 연소특성)

  • Lee, Kwang-Jin;Seo, Seong-Hyeon;Kim, Seong-Gu;Han, Yeoung-Min;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.05a
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    • pp.168-172
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    • 2008
  • Hot firing tests of sub-scale combustors were carried out to study the characteristic velocity according to the variation of propellant mass flow and injector arrangement. Test results show that there exists an effective range of relative flow-rate density on the condition of similar combustion pressure and mixture ratio. Numerical analysis has also revealed that the increase of the distance between the outermost injector array and the cylindrical chamber wall with film cooling increases the region of low mixture ratio near combustion chamber wall and it decreases the characteristic velocity of the combustor. Thus, it was confirmed that these two factors play an important part in improving the performance of LRE combustor on a predetermined chamber pressure.

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STUDY ON PRE-MIXTURE COMBUSTION IN A SUB-CHAMBER TYPE CVC WITH MULTIPLE PASSAGE HOLES

  • PARK J. S.;YEOM J. K.;LEE T. W.;HN J. Y.;CHUNG S. S.
    • International Journal of Automotive Technology
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    • v.7 no.1
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    • pp.17-23
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    • 2006
  • An experimental study was carried out to obtain the fundamental data about the effect of sub-chamber on pre-mixture combustion. A eve (constant volume combustor) divided into a sub-chamber and a main chamber was used in this experiment. The volume of the sub-chamber was varid trom $0.45\%$ to $1.4\%$ about the whole combustion chamber. The sub-chamber has twelve narrow radial passage holes and a spark plug to ignite the pre-mixture. As the ignition occurs in the sub-chamber by a spark discharge, burned and unburned gas including a great number of radicals is injected into the main chamber, then the multi-point ignition occurs in the main chamber. The combustion pressure is measured to calculate the burning velocity mainly as a function of the sub-chamber volume, the diameter of the passage holes, and the equivalence ratio. In the case of RI (radical ignition) methods, the overall burning time became very short and the maximum burning pressure was slightly increased as compared with that of SI (spark ignition) method. The optimum design value of the sub-chamber is near 0.11 $cm^{-l}$ in the ratio of total area of holes to the sub-chamber volume.

On the Method for Hot-Fire Modeling of High-Frequency Combustion Instability in Liquid Rocket Engines

  • Sohn, Chae-Hoon;Seol, Woo-Seok;Valery P. Pikalov
    • Journal of Mechanical Science and Technology
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    • v.18 no.6
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    • pp.1010-1018
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    • 2004
  • This study presents the methodological aspects of combustion instability modeling and provides the numerical results of the model (sub-scale) combustion chamber, regarding geometrical dimensions and operating conditions, which are for determining the combustion stability boundaries using the model chamber. An approach to determine the stability limits and acoustic characteristics of injectors is described intensively. Procedures for extrapolation of the model operating parameters to the actual conditions are presented, which allow the hot-fire test data to be presented by parameters of the combustion chamber pressure and mixture (oxidizer/fuel) ratio, which are customary for designers. Tests with the model chamber, based on the suggested scaling method, are far more cost-effective than with the actual (full-scale) chamber and useful for injector screening at the initial stage of the combustor development in a viewpoint of combustion instabilities.

Design of a Model Combustor for Studying the Combustion Characteristics of O2/H2 Flames at Supercritical Conditions (O2/H2 화염의 초임계 조건 연소 특성 연구를 위한 모델 연소기 설계)

  • AHN, YEONG JONG;KIM, YOUNG HOO;KWON, OH CHAE
    • Transactions of the Korean hydrogen and new energy society
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    • v.31 no.1
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    • pp.96-104
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    • 2020
  • A model combustor has been designed and fabricated for studying the combustion characteristics of oxygen (O2)/hydrogen (H2) flames under supercritical conditions. The combustor is designed to allow combustion experiments up to 60 bar, the supercritical pressure condition of O2 and H2. Injectors can be replaced to study various types of flames and the combustion chamber is designed to visualize flames by installing optical windows. Through the preliminary tests, including a high-pressure (up to 60 bar) test using air and combustion tests for coaxial jet flames of liquid oxygen (LO2)/gaseous hydrogen (GH2) at elevated pressure, the reliability of the combustor has been demonstrated.