• Title/Summary/Keyword: 하이브리드 연소기

Search Result 43, Processing Time 0.022 seconds

Reactive Fields Analysis of End-Burning Hybrid Combustor Using Tangential Oxidizer Injectors with Various Momentum Ratio (접선형 산화제 주입기의 운동량비에 따른 End-Burning 하이브리드 연소기의 연소유동장 해석)

  • Min, Moon-Ki;Kim, Soo-Jong;Kim, Jin-Kon;Moon, Hee-Jang
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.11 no.2
    • /
    • pp.37-46
    • /
    • 2007
  • In this study, combustion fields of the end-burning hybrid combustor with tangential oxidizer injectors are examined. Momentum ratio of oxidizer is used as a main parameter to analyse the combustion efficiency with temperature, pressure, swirl velocity and mixture fraction field. It was found that as momentum ratio decreases the overall combustion efficiency is enhanced with the pressure field being insensitive to momentum ratio keeping quasi-uniform distribution. Irrespective to the momentum ratio, annular hot region commonly occurred in the upper combustion chamber where this phenomenon was left for a future improvement to be followed.

Hybrid Rocket Instability II (하이브리드 로켓 불안정성 II)

  • Lee, Jung-Pyo;Rhee, Sun-Jae;Kim, Young-Nam;Moon, Hee-Jang;Sung, Hong-Gye;Kim, Jin-Gon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2012.05a
    • /
    • pp.86-90
    • /
    • 2012
  • In this paper, the combustion instabilities which may occur in the hybrid rocket were studied. The rocket combustor where the vortexes can be generated was designed, and the experiments were performed. The investigations about characteristics on the presence of the diaphragm, the length of the fuel, the diameter of the fuel port, the diameter of the diaphragm, the diameter of the nozzle throat, and the variation of the Ox massflow rate were conducted. The main resonant frequency of the combustion pressure is regarded by the Vortex shedding mode, and it is considered that the other resonant frequency of the pressure fluctuation is hybrid low frequency, or helmholtz mode.

  • PDF

Reactive Fields Analysis of Hybrid Combustor Under Different Arrangements of Oxidizer Injectors (하이브리드 연소기의 산화제 주입기 배열 특성에 따른 반응유동장 해석)

  • Cho Sung-Chan;Kim Soo-Jong;Lee Seung-Chul;Kim Jin-Kon;Koo Ja-Yae;Moon Hee-Jang
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.9 no.2
    • /
    • pp.78-88
    • /
    • 2005
  • The combustion characteristics of End-Burning hybrid combustor using different types of injector system are numerically investigated to visualize the temperature fields in the combustion chamber The basic characteristics of combustion with different O/F ratio is also analyzed in order to capture the main behavior of diffusion flame inside the swirl induced hybrid combustion chamber It was found that the arrangement of oxidizer injectors give strong effect on the temperature field dominating mixing between fuel and oxidizer. The results show that among five different oxidizer injectors arrangement, the counter flow injector has the highest mixing efficiency. However, the observed high wall temperature presence near the oxidizer injectors remains to be solved.

Study on Auto Ignition of Hybrid Rocket Using $N_2O$ Catalytic Decomposition ($N_2O$ 촉매 분해를 이용한 하이브리드 로켓 자연 점화 연구)

  • Yong, Sung-Ju;Kim, Tae-Gyu
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2010.05a
    • /
    • pp.202-205
    • /
    • 2010
  • Auto ignition of hybrid rocket using $N_2O$ catalytic decomposition was studied in the present study. The hybrid rocket consists of catalytic igniter, solid fuel, combustor, and nozzle. The Ru/$Al_2O_3$ catalyst for $N_2O$ decomposition was synthesized by an impregnation method, and $N_2O$ conversion as reaction temperatures was measured. The temperature change of the catalytic ignitor was measured at the operating condition, and the possibility for the auto ignition of hybrid rocket was validated.

  • PDF

Development of Hybrid/Dual Swirl Jet Combustor for a MGT (Part II: Numerical Study on Isothermal Flow) (마이크로 가스터빈용 하이브리드/이중 선회제트 연소기 개발 (Part II: 비반응 유동에 관한 수치해석))

  • Mun, Sun-Yeo;Hwang, Cheol-Hong;Lee, Kee-Man
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.17 no.5
    • /
    • pp.70-79
    • /
    • 2013
  • The isothermal flow structure and mixing characteristics of a hybrid/dual swirl jet combustor for micro-gas turbine (MGT) were numerically investigated. Location of pilot burner, swirl angle and direction were varied as main parameters with the identical thermal load. As a result, the variations in location of pilot nozzle, swirl angle and direction resulted in the significant change in turbulent flow field near burner exit, in particular, center toroidal recirculation zone (CTRZ) as well as turbulent intensity, and thus the flame stability and emission performance might be significantly changed. With the comparison of experimental results, the case of swirl angle $45^{\circ}$ and co-swirl flow including optimum location of pilot burner were chosen in terms of the flame stability and emissions for the development of hybrid/dual swirl jet combustor.

Fuel-Rich Combustion Characteristic of a Combined Gas Generator (혼합식 가스발생기의 연료과농 연소특성)

  • Lee, Dongeun;Lee, Changjin
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.43 no.7
    • /
    • pp.593-600
    • /
    • 2015
  • In this study, a combined hybrid rocket system is newly introduced which has characteristics of both gas generators and afterburner type hybrid rockets. In particular, a combined gas generator utilizing solid fuel and liquid/gas oxidizer was designed as a primary combustor of the system. Combustion tests were carried out with various equivalence ratio affected by parameters such as fuel length, oxidizer flow rate, fuel port diameter and fuel type. In general, fuel-rich gas generator produces low combustion gas temperature to meet the temperature requirement and the target temperature was transiently set less than 1600 K. Since it was found that controlling parameters showed limited effects on the change of equivalence ratio, mixture of $O_2$ and $N_2$ as an oxidizer was additionally introduced. As a result, a combined gas generator successfully produced combustion gas temperature of less than 1600 K Future studies will carry out more combustion tests to attain fuel-rich combustion gas temperature less than 1200 K, which was a temperature requirement of a gas generator system in the previous studies.

A Study on Combustion Characteristic of the Hybrid Combustor with Non-Combustible Diaphragm Position (비연소성 다이아프램의 설치 위치에 따른 하이브리드 연소기의 연소 특성 연구)

  • Kim, Hak-Chul;Moon, Keun-Hwan;Moon, Hee-Jang;Sung, Hong-Gye;Kim, Jin-Kon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2012.05a
    • /
    • pp.163-166
    • /
    • 2012
  • The hybrid combustion were performed with the different diaphragm position for the experimental studies on characteristic of regression rate and combustion efficiency. The diaphragm was installed in 25% and 50% of fuel length from the front of solid fuel, respectively. As results of experiments, the position of diaphragm has small effect on the regression rate and combustion efficiency. It is considered that the diaphragm has local effect near the diaphragm.

  • PDF

Reactive Flow Fields Analysis of End-Bunting Combustor with Different Impinging Type Injectors (End-Burning 연소기의 충돌형 산화제 주입기 형상 변화에 따른 연소유동장 해석)

  • Min, Moon-Ki;Kim, Soo-Jong;Yoon, Chang-Jin;Kim, Jin-Kon;Moon, Hee-Jang
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.11 no.5
    • /
    • pp.51-59
    • /
    • 2007
  • The end-burning combustion field using impinging oxidizer injectors are analyzed with tangential type injectors in order to examine their mixing and combustion characteristics. The impinging type showed further improved mixing effect as well as the combustion efficiency compared to the previously studied tangential injector. A novel injector capable of delivering impinging and swirl effect is introduced in this study where it demonstrated that the grain coning effect can be avoided. It was found that the combined impinging and swirling flow would promote the radial mixing rate increasing the residence time and the turbulent intensity. However, the use of the step combustor which may augment the turbulent intensity did not show any notable difference compared to the basic combustor.

A Study on the Combustion Instability of the Hybrid Rocket Motor with a Diaphragm (다이아프램이 설치된 하이브리드 로켓 모터의 연소불안정 연구)

  • Lee, Jungpyo;Kim, Youngnam;Kim, Jinkon;Moon, Heejang
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.17 no.6
    • /
    • pp.1-10
    • /
    • 2013
  • In this paper, the main cause on excitation of the combustion instability which may occur in the hybrid rocket motor with a diaphragm was studied. Hybrid rocket motor propulsion tests considering various experimental conditions such as with a diaphragm or not, a diameter of diaphragm, oxidizer mass flow rate, fuel length, etc were performed, and the combustion visualization for the inside of a hybrid rocket motor with a diaphragm was performed. With these experimental results, it was confirmed that the main cause of a large excitation was the hole-tone, and it was shown that the hole-tone model can be predicted experimental primary pressure oscillation frequency quite well.

Visualization device of solid fuel combustion in hybrid rocket (하이브리드 로켓에서의 고체 연료 연소 가시화 장치)

  • Moon, Keun-Hwan;Cho, Jung-Tae;Kim, Soo-Jong;Lee, Jung-Pyo;Kim, Hak-Chul;Oh, Ji-Sung;Moon, Hee-Jang;Sung, Hong-Gye;Kim, Jin-Kon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2010.05a
    • /
    • pp.206-209
    • /
    • 2010
  • The visualization device for hybrid rocket is fabricated to investigate the combustion phenomena. Visualization device were composed with ignition system, oxidizer supply system, control system and data acquisition system, combustion visualization system. GOX as oxidizer and HDPE, Paraffin-LDPE Blending, Paraffin sd were used. As results, combustion phenomena and fuel droplet entrainment were observed.

  • PDF