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V. G. Grossman,B. G. Bazarov,Ts.T.Bazarova,L. A. Glinskaya,J. G. Bazarova,J. Temuujin 한양대학교 세라믹연구소 2017 Journal of Ceramic Processing Research Vol.18 No.12
Subsolidus phase relations in the Tl2MoO4-Ho2(MoO4)3-Zr(MoO4)2 system have been studied by X-ray diffraction anddifferential thermal analysis methods. The system has been shown to contain molybdates with the compositionsTl5HoZr(MoO4)6 (5 : 1 : 2) and Tl2HoZr2(MoO4)6.5 (2 : 1 : 4). A new ternary molybdate TlHoZr0.5(MoO4)3 was discovered bythe method of spontaneous solution-melt crystallization through spontaneous nucleation, and its crystal structure has beendetermined to be: sp. gr. R 3, a = b = 13.3665(2) Å, c = 11.9844(4) Å, V = 1854.31(7) Å3, Z = 6. The mixed three dimensionalframework of the crystal structure is composed of Mo tetrahedra sharing O vertices with (Ho,Zr)O6 octahedra. The thalliumatoms occupy wide channels in the framework. Crystals of binary molybdate of Ho2Zr2(MoO4)7 composition were grown bysolution-melt crystallization and their crystal structure were determined to be: sp. gr. С2/c, a = 20.6668(4), b = 9.8193(2), c =13.8187(3) Å, b = 113.678(1)о, .V = 2568.20(9)Å3, Z = 4. The crystal structure is composed of three types of polyhedra: МоО4tetrahedra, ZrO6 octahedra, and eight-vertex HoO8.
Experimental Study on Simplex Swirl Injector Dynamics with Varying Geometry
Chung, Yun-Jae,Khil, Tae-Ock,Yoon, Jung-Soo,Yoon, Young-Bin,Bazarov, V. The Korean Society for Aeronautical and Space Scie 2011 International Journal of Aeronautical and Space Sc Vol.12 No.1
The effects of swirl chamber's diameter and length on injector's dynamic characteristics were investigated through an experimental study. A mechanical pulsator was installed in front of the manifold of a swirl injector which produces pressure oscillations in the feed line. Pressure in the manifold, liquid film thickness in the orifice and the pressure in the orifice were measured in order to understand the dynamic characteristic of the simplex swirl injector with varying geometry. A direct pressure measuring method (DPMM) was used to calculate the axial velocity of the propellant in the orifice and the mass flow rate through the orifice. These measured and calculated values were analyzed to observe the amplitude and phase differences between the input value in the manifold and the output values in the orifice. As a result, a phase-amplitude diagram was obtained which exhibits the injector's response to certain pressure fluctuation inputs. The mass flow rate was calculated by the DPMM and measured directly through the actual injection. The effect of mean manifold pressure change was insignificant with the frequency range of manifold pressure oscillation used in this experiment. Mass flow rate was measured with the variation of injector's geometries and amplitude of the mass flow rate was observed with geometry and pulsation frequency variation. It was confirmed that the swirl chamber diameter and length affect an injector's dynamic characteristics. Furthermore, the direction of geometry change for achieving dynamic stability in the injector was suggested.
액체로켓에서 다단 접선 유입구를 갖는 스월인젝터의 음향학적 감쇠기능
김병선(Byungsun Kim),김동준(Dongjun Kim),김현성(Hyunsung Kim),윤영빈(Youngbin Yoon),V. G. Bazarov 한국항공우주학회 2006 韓國航空宇宙學會誌 Vol.34 No.10
액체로켓엔진에서 고주파 연소불안정을 제어하기 위하여 다단 접선 유입구를 갖는 스월 인젝터를 분석하였다. 음향흡수자로서 인젝터의 효과를 분석하기위하여 인젝터는 1/4 파장 공명기로 해석하였고, 상온에서 감쇠 효과의 적합성을 검증하였다. 이러한 인젝터는 모델 챔버의 고유주파수에 동조시킬 수 있는 고유주파수를 갖게 된다. 다단의 접선 유입구를 갖는 인젝터가 단일 유입구를 갖는 인젝터 보다 인젝터 내부의 air core가 안정되었다. 또한, 다단 접선 유입구를 갖는 인젝터를 사용하였을 때 불안정 모드에 동조되는 인젝터 길이가 계산된 길이와 잘 일치하였다. 이러한 실험 결과로부터 인젝터 내부의 air core가 안정되게 유지된다면, 동조된 스월 인젝터는 모델 챔버의 불안정 모드를 효과적으로 감소시킬 수 있고, 감쇠율을 증가시킬 수 있음을 확인하였다. Swirl injector with multi-stage tangential entry was analyzed to suppress high-frequency combustion instability in Liquid Rocket Engines. In order to analyze the effect of swirl injector as an acoustic absorber, swirl injector was regarded as a quarter-wave resonator and it's damping capacity is verified in atmospheric temperature. It has a finite mode of vibration and natural frequencies which can be tuned to the natural frequencies of a model combustion chamber. The interior air core shape of injector is more stable in the case of using the swirl injector with multi-stage entry than with single-stage entry. Also, when the swirl injector with multi-stage entry is used, tuned-injector length for unstable mode is well agreed with the calculated length. From the experimental data, it is proved that if the interior air core shape of swirl injector is stable, the fine tuned swirl injector can decrease the unstable mode of model chamber effectively and increase the damping rate.
Experimental Study on Simplex Swirl Injector Dynamics with Varying Geometry
Yunjae Chung,Taeock Khil,Jungsoo Yoon,Youngbin Yoon,V. Bazarov 한국항공우주학회 2011 International Journal of Aeronautical and Space Sc Vol.12 No.1
The effects of swirl chamber’s diameter and length on injector’s dynamic characteristics were investigated through an experimental study. A mechanical pulsator was installed in front of the manifold of a swirl injector which produces pressure oscillations in the feed line. Pressure in the manifold, liquid film thickness in the orifice and the pressure in the orifice were measured in order to understand the dynamic characteristic of the simplex swirl injector with varying geometry. A direct pressure measuring method (DPMM) was used to calculate the axial velocity of the propellant in the orifice and the mass flow rate through the orifice. These measured and calculated values were analyzed to observe the amplitude and phase differences between the input value in the manifold and the output values in the orifice. As a result, a phase-amplitude diagram was obtained which exhibits the injector’s response to certain pressure fluctuation inputs. The mass flow rate was calculated by the DPMM and measured directly through the actual injection. The effect of mean manifold pressure change was insignificant with the frequency range of manifold pressure oscillation used in this experiment. Mass flow rate was measured with the variation of injector’s geometries and amplitude of the mass flow rate was observed with geometry and pulsation frequency variation. It was confirmed that the swirl chamber diameter and length affect an injector’s dynamic characteristics. Furthermore, the direction of geometry change for achieving dynamic stability in the injector was suggested.
김병선(Byungsun Kim),김동준(Dongjun Kim),차은선(Eunsun Cha),윤영빈(Youngbin Yoon),한영민(Yeoung-Min Han),최환석(Hwan-Seok Choi),V. G. Bazarov 한국항공우주학회 2006 韓國航空宇宙學會誌 Vol.34 No.8
액체로켓엔진에서 고주파 연소불안정을 제어하기 위하여 인젝터 길이 변화를 줄 수 있는 백홀 스월 인젝터를 분석하였다. 음향흡수자로서 백홀 인젝터의 효과를 분석하기위하여 백홀 인젝터는 1/4 파장 공명기로 해석하였다. 이론적 접근과 음향 실험의 결과로부터 가변적 변위를 갖는 백홀 스월 인젝터가 연소실의 불안정 모드를 감소시킴을 알 수 있었다. 실험적으로 감쇠율을 측정하여 감쇠효과를 측정하였다. Swirl injector with adjustable backhole length was analyzed to suppress high-frequency combustion instability in Liquid Rocket Engines. In order to analyze the effect of variable backhole injector as an acoustic absorber, backhole injector was regarded as a quarter-wave resonator. As a result of theoretical approaches and acoustic tests, backhole injector with adjustable length could decrease the unstable modes of combustion chamber. And the damping efficiency was estimated by measuring damping rates experimentally.