• Title/Summary/Keyword: oxidizer

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KSR-III 액체 로켓엔진 설계점 연소시험

  • Kim, Seung-Han;Cho, Gyu-Sik;Han, Yeoung-Min;Seo, Seong-Hyun;Moon, Il-Yoon;Lee, Kwang-Jin;Kim, Jong-Kyu;Seol, Woo-Seok;Lee, Soo-Yong
    • Aerospace Engineering and Technology
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    • v.2 no.1
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    • pp.164-170
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    • 2003
  • KSR-III engine with film-cooled baffle was tested. The purpose of this test is to verify the effect of ablative baffle on avoiding combustion instability which occurred in the acoustic cavity case. The engine had expansion ratio of 5.04 and the test condition was design condition(oxidizer mass flow rate 42.04, and fuel 17.95 kg/s). In the test, combustion instability did not occur. So, the effect of film-cooled baffle on avoiding combustion instability was verified.

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Study on flow characteristics in entrained flow gasifier with high speed impinging jet (고속충돌노즐을 이용한 분류층 가스화기내의 유동특성에 관한 연구)

  • Lee, Hyo-Jin;Park, Tae-Jun;Lee, Jae-Gu;Kim, Jae-Ho;An, Dal-Hong
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.20 no.5
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    • pp.1735-1742
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    • 1996
  • An entrained flow gasifier simulating the cold mode was tested to estimate its performance for coal gasification and flow characteristics with a developed high speed impinging jet nozzle. The burner was designed for high temperature and high pressure(HTHP) conditions, especially for IGCC(Integrated Coal Gasification Combined Cycle). In order to get proper size of droplets for high viscous liquid such as coal slurry, atomization was achieved by impacting slurry with high speed (over 150m/sec) secondary gas (oxygen/or air)/ Formed water droplets were ranged between 100.mu.m to 20.mu.m in their sizes. The flow characteristics in the gasifier was well understood in mixing between fuel and oxidizer. Both external and internal recirculation zones were closely investigated through experimentation with visualization and numerical solutions from FLUENT CODE.

Influence of Propellant Mixture ]Ratio Variation near Chamber Wall (액체로켓엔진의 내부 벽면 근처에서의 추진제 혼합비 변화의 영향에 대한 연구)

  • Han Poong-Gyoo;Chang Haeng-Soo;Cho Yong-Ho;Kim Kyoungho
    • Proceedings of the KSME Conference
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    • 2002.08a
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    • pp.255-258
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    • 2002
  • Liquid rocket engines using liquefied natural gas (LNG) or methane as a fuel is known to have several good characteristics, such as high specific impulse compared to other hydrocarbon fuels, environment-friendly exhaust gas, low production cost, and re-usability with low soot generation in the cooling channel. In this study, experimental combustion chambers capable of using LNC and $CH_{4}$ are being researched through experimental firing tests, and within easy range of eyes' inspection, there are the periodical existence of soot or discoloration in the chamber wall surface. This result means that mixture ratio of oxidizer and fuel fluctuates periodically between outer-row injectors in the mixing head in the circumferential direction. Therefore, based on this phenomenon, the variation of mixture ratio near the chamber wall caused by the spill pattern of a shear coaxial injector was analyzed quantitatively and the thermal heat flux Into the cooling channel is modified. Then, the calculated and modified results are compared with the measured ones.

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Combustion Noise Characteristics in Gas and Liquid Flames (가스 및 분무화염의 연소소음 특성에 관한 실험연구)

  • 김호석;백민수;오상헌
    • Journal of Advanced Marine Engineering and Technology
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    • v.18 no.1
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    • pp.81-91
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    • 1994
  • Combustion noise involved with chemical heat release and turbulent process in turbopropulsion systems, gasturbine, industrial furnaces and internal engines is indeed noisy. The experimental study reported in this paper is made to identify a dominant combustion noise in jet flames. Gaseous propane and kerosene fuel have been used with air as the oxidizer in a different jet combustion systems. Combustion and aerodynamic noise are studied through far field sound pressure measurements in an anechoic chamber. And also mean temperature and velocities and turbulent intensities of both isothermal and reacting flow fields were measured. It is shown that axial mean velocity of reacting flow fields is higher about 1 to 3m/sec than that of cold flow in a gaseous combustor. As the gaseous fuel flow rate increases, the acoustic power increases. But the sound pressure level for the spray flame decreases with increasing equivalence ratio. The influence of temperature in the combustion fields due to chemical heat release has been observed to be a dominant noise source in the spray flame. The spectra of combustion noise in gaseous propane and kerosene jet flame show a predominantly low frequency and a broadband nature as compared with the noise characteristics in an isothermal air jet.

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Twin Spray Characteristics Between Two Impinging F-O-O-F Type Injectors

  • Kang, Shin-Jae;Lee, Eun-Sang;Kwon, Ki-Chul;Oh, Je-Ha;Yu, Myoung-Jong
    • Journal of Mechanical Science and Technology
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    • v.16 no.5
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    • pp.732-742
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    • 2002
  • This paper presents twin spray characteristics of two impinging F-O-O-F type injectors in which fuel and oxidizer impinge on each other to atomize under the various conditions. The droplet size and velocity in the impinging spray flow field were measured using PDPA. The droplet size and velocity were investigated at the mixture ratios of 1.5, 2.0, 2.47 and 3.0 for four injectors in which two single F-O-O-F injectors were arranged at the intervals of 20.8, 31.2, 41.6 and 62.4mm respectively. In general, the arithmetic mean diameter, SMD and standard deviation of droplet size in the interaction area (X=0 and Y=0mm) were smaller, while the axial velocity in the interaction area was slightly higher. An empirical correlation is obtained for the (D$\_$10/)$\_$D//(D$\_$10/)$\_$c/ value under the assumptions of two identical droplets and these with different size and velocity. The droplets with low Weber numbers below 40 have possibility to coalesce, while those over 40 tend to disintegrate after impingement in the interaction area.

Spray Characteristics in the cross region of twin spray between impinging F-O-O-F type injectors (충돌형 F-O-O-F 인젝터의 이중분무 중첩영역에서의 분무특성에 관한 연구)

  • Kwon, K.C.;Lee, E.S.;Kang, S.J.;Rho, B.J.
    • Proceedings of the KSME Conference
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    • 2001.11b
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    • pp.758-763
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    • 2001
  • This paper presents twin spray characteristics of two impinging F-O-O-F type injectors in which fuel and oxidizer impinge on each other to atomize under the various conditions. The droplet size and velocity in the impinging spray flow field were measured using a PDPA. The droplet size and velocity were investigated at mixture ratios of 1.5, 2.0, 2.47 and 3.0 for four injectors in which two single F-O-O-F injectors were arranged at intervals of 20.8, 31.2, 41.6 and 62.4mm respectively. In general, the arithmetic mean diameter, SMD and standard deviation of droplet size in the interaction area (X=0 and Y=0mm) were smaller. The axial velocity in the interaction area was slightly higher. Considering the behavior of impinged droplets using the We number calculated by using the axial velocity instead of the relative velocity in line C in Fig. 1(b) for four injectors, it is consumed that the We number over 500 had the possibility to disintegrate, and the We number below 500 had it to cohere after impingement of twin spray. The results of this study can be used for the design of a nozzle for liquid propellant rockets.

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Measurement of the fuel distribution in a scaled ATR combustor using PLIF (PLIF를 이용한 ATR 연소기 축소모형의 연료분포 측정연구)

  • Jin Yu-In;Yang In-Young;Choi Young-Hwan;Yang Soo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.9 no.4
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    • pp.55-65
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    • 2005
  • Mixing performance between fuel and oxidizer is a significant parameter of combustion efficiency and stability in an air-turbo ramjet combustor. Two types of petal mixer were experimented to research the mixing performance. Mixing performance and fuel distribution images were obtained for petal mixers. Planar laser-induced fluorescence(PLIF) was used to obtain 2-D fuel distribution. The obtained images were processed in order to make use of the image information to a quantitative level. The results of analyzing the fluorescence images could be useful to find better mixing performance between mixers.

Pogo Analysis on the KSR-III Propulsion Feeding System (KSR-III 추진기관 공급계 pogo 해석)

  • ;;O. M. Menshikova
    • Journal of the Korean Society of Propulsion Engineers
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    • v.6 no.3
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    • pp.45-52
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    • 2002
  • This article deals with the introduction of longitudinal instability of liquid rocket (pogo) and the analytical results on the frequency responses of Korean Sounding Rocket (KSR-III) propulsion feeding system. Both the stiffness of bellows and the cavitation volume of venturi affect the frequency response of the feeding system. Especially, bellows has a great roll to reduce the natural frequency of the feeding system. Also, oxidizer and fuel feeding systems of the KSR-III have natural frequencies of about 280Hz and 90Hz, respectively.

Surface Gas Temperature of Turbine Blade by Hot Gas Stream of Pyro Starter in Operation Condition (파이로 시동기의 고온 가스에 의한 터빈 블레이드의 표면 가스온도 발달과정 해석)

  • Lee, In-Chul;Kim, Jin-Hong;Koo, Ja-Ye;Lee, Sang-Do;Kim, Kui-Soon;Moon, In-Sang;Lee, Soo-Yong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.11a
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    • pp.63-67
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    • 2007
  • The high pressure turbopump carries out supplying the oxidizer in the liquid propulsion rocket in the combustion chamber. Because an LRE requires a very short starting time , the turbine at the turbopump experiences high torque that was produced by the high pressure and the high temperature. The purpose of this study is to evaluate a turbine blade surface temperature profiles at initial starting 0 ${\sim}$ 0.5 sec. Using $Fine^{Tm}$/turbo, three dimensional Baldwin-Lomax turbulence models are used for numerically analysis. The turbine is composed of 108 blades total, but only 7 rotors were considered because of periodic symmetry effect. Because of interaction with a bow shock on the suction surface, the boundary layer separates from suction surface at inner area of turbine blade. The averaged temperature of the turbine blade tip at 1000 rpm is higher than that of 9000 rpm. Especially at 1000 ${\sim}$ 9000 rpm, temperatures increases on the hub side of the turbine blade tip. Moreover at 9000 rpm, the temperatures from the hub to the shroud of the blade tip increase as well.

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Heating Apparatus Development and Tests for Cryogenic Gaseous Helium (극저온 헬륨가스 가열장치 개발 및 시험)

  • Chung, Yong-Gahp;Cho, Nam-Kyung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.15 no.1
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    • pp.63-68
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    • 2011
  • For the liquid rocket propulsion system using liquid oxygen as oxidizer, helium for pressurizing LOX is usually stored in the LOX tank with cryogenic temperature. For that kind of pressurizing system, cryogenic helium is discharged from the immerged pressurant cylinder and passes through the heat exchanger downstream of gas generator. During the process, helium pressurant is heated from cryogenic temperature to high one and supplied to the ullage of propellant tank. To develop the pressurizing system, a cryogenic heating apparatus is needed to simulate the heat exchanger. In this paper, the cryogenic heating apparatus for development of the pressurization system is presented along with its heating test results with cryogenic helium.