• Title/Summary/Keyword: 축소 노즐

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Numerical Analysis and Design of the 2-D Variable Convergent-Divergent Thrust Vectoring Nozzle (2-D 가변 추력편향 노즐 설계 및 유동해석)

  • Kim, Yoon-Hee;Kang, Hyung-Seok;Choi, Seong-Man;Chang, Hyun-Soo
    • Journal of the Korean Society of Propulsion Engineers
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    • v.15 no.5
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    • pp.27-34
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    • 2011
  • A numerical analysis was peformed for the supersonic aircraft with variable pitch thrust vector nozzle. Based on the requirement of the mixed turbofan engine of the supersonic aircraft, two dimensional thrust vector nozzle with variable pitch angle was designed. To investigate the effect of the thrust vectoring nozzle, the numerical analysis was conducted by using Fluent under the several pitch deflection angle.

축소 노즐에서의 슬롯 막냉각 열전달 특성에 관한 연구

  • 조용일;조형희
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2000.04a
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    • pp.33-33
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    • 2000
  • 고온의 연소가스로부터 노즐 표면을 보호하기 위하여 슬롯을 통하여 냉각 유체를 분사하는 슬롯 막냉각에 대하여 연구하였다. 냉각효율 및 열전달 특성은 주유동과 2차 유동의 분사율에 따라 크게 달라지며, 형상변화 및 유동가속에 의해서도 냉각 효과의 변화를 가져오게 된다. 따라서 본 연구에서는 실험을 통하여 면적비가 16:1인 축소노즐에서 압축성 효과를 배제할 수 있는 유동속도 범위 내에서 분사율 변화(0.5 $\leq$ M $\leq$ 3.0)에 따른 슬롯 막냉각 열전달 특성을 고찰하고, 평판 슬롯 막냉각 경험식의 결과와 비교하였으며, 수치해석을 통하여 축소노즐과 원형관에서의 냉각효율 및 열전달 특성을 비교함으로서 이를 검증하였다. 축소노즐에서의 슬롯 막냉각 열전달 특성은 단열벽면조건을 형성하여 노즐 표면을 따라 설치된 열전대를 이용하여 측정하였다. 그 결과 상대적으로 낮은 분사율(M=0.5, 1.0)에서 분사율 증가에 따른 냉각효율의 증가가 크게 나타났으며, 분사율이 높아짐(M $\geq$ 2.0)에 따라 냉각효율의 증가폭이 점점 감소하고, 일정 분사율 이상에서는 냉각 효율의 증가가 크게 둔화되었다. 분사율이 낮을 경우 평판 슬롯 막냉각 경험식으로 주어진 결과보다 상류에서는 높으나 하류로 진행하면 비슷한 냉각효율을 보였고, 분사율이 높은 경우 평판보다 전 범위에서 약간 높은 냉각효율을 나타냈다. 수치해석 결과에서는 분사율이 낮을 경우 축소노즐의 냉각효율이 원형관에서의 냉각효율 보다 낮거나 비슷하게 나타났으며, 분사율이 높아짐에 따라 축소노즐에서의 냉각효율이 오히려 높아지는 것으로 나타났다.타내었다. 액체 제트의 속도는 처음에는 일정하게 유지되다가 운동량을 보존하기 위해 가스로부터 운동량을 받아 점차 가속되어지는 것으로 나타났다.본 규격은 키, 총장, 어깨길이, 등길이, 머리길이, 머리둘레, 진동둘레, 목둘레, 가슴둘레, 허리둘레, 배둘레, 엉덩이둘레, 앞품, 뒤품, drop치를 포함하고 있고, 각 규격에서 호칭간 치수 간격도 함께 제시하고 있다. 본 연구 결과에서 보듯, 현행 8규격의 무진복의 각 호칭간 적정 허용범위를 고려해 합리적인 치수체계를 정립한다면 치수에 대한 적합도가 상당히 증가할 뿐 아니라 생산비용도 상당히 감축할 것으로 생각된다.나타났다. 4) 호감적 서비스능력 차원에서 세 독립변수간에 유의한 3원 상호작용이 존재하는 것으로 나타나( $F_{2,228}$=15.62, P<.001) 20대에 적합한 의복 착용시( $F_{2,228}$=3.98, P<.05)와 60대에 적합한 의복 착용시( $F_{2,228}$=16.55, P<.001) 점포유형과 격식차림간에는 유의한 상호작용이 존재하는 것으로 나타났다. 5) 호감을 구성하는 세 요인들이 구매의도에 미치는 영향을 조사한 결과 호감적 인상차원은 29%(P<.001), 호감적 서비스능력차원은 6%(P<.001)의 구매의도를 설명해 주는 것으로 나타났다. 본 연구결과 노년 소비자에게 호감을 주는 판매원의 외모는 구매의도에 영향을 주어 실버의류산업의 이익증대와 밀접한 연관을 갖는 서비스품질의 중요한 요인으로 밝혀졌다.중요한 요인으로 밝혀졌다.로운 단백질 EPSPS가 다른 여러 식물에 이미 존재하고 있는 단백질로서 우리가 이미 이러

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Experimental Study of the Thrust Vectoring Characteristics in a Two-Dimensional Convergent-Divergent Nozzle (2차원 축소확대노즐의 추력편향특성 실험연구)

  • Yu, Du Whan;Choi, Seong Man;Oh, Seong Hwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.2
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    • pp.84-93
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    • 2013
  • Stealthy, high maneuverability and super cruise abilities are required for the next generation fighter and unmanned aircraft. Thrust vector control technique currently come into use to meet these requirements. In this experimental study, axial and pitch thrust were measured and Schlieren visualization were carried out using the scaled two dimensional thrust vector nozzles under various pitch deflection angle, pitch flap length and height. From the study, we could get the supersonic flow characteristics and draw an optimum geometric configuration of the two dimensional thrust vector nozzle.

A Fundamental Study of Coaxial Supersonic Jets (동축 초음속 제트유동에 관한 기초적 연구)

  • 이권희;구병수;김희동
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2000.11a
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    • pp.37-37
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    • 2000
  • 일반적으로 노즐 입구의 압력과 배압의 비가 어떤 임계값보다 큰 경우에 축소확대 노즐을 통하는 유동은 노즐목에서 초크하며, 노즐출구에서는 용이하게 초음속으로 된다. 노즐을 통하여 초음속으로 방출되는 제트유동에 관해서는 현재까지 많은 연구가 수행되었다. 이들 연구에 의하면 노즐 압력 비에 따라 노즐출구에서의 유동상태(즉 과팽창, 적정팽창, 부족팽창상태)가 결정되며, 노즐출구로부터 하류의 초음속 제트유동에서 발생하는 충격파 구조 및 위치, 제트경계의 구조 그리고 제트의 코어 등 유동의 기구가 비교적 상세하게 알려져 있다.(중략)

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A Study on Jet Characteristic using a Coanda Effect in a Constant Expansion Rate Nozzle (코안다 효과를 이용한 제트 특성에 관한 연구)

  • Lee, Dong-Won;Lee, Sak;Kim, Byung-Ji;Kwon, Soon-Bum
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.8
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    • pp.706-713
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    • 2007
  • The jet structure issuing from a conventional convergent nozzle of variable expansion rate is compared with the result from the nozzle of a constant expansion rate using a normal type annular slit. In experiments, to investigate the jet characteristics between the two cases of jet, the mean velocity of nozzle exit is fixed to be 90m/s, the pressures along the jet axis and radial directions are measured by a scanning valve system moving with 3-axis auto-traverse unit, and the velocity distribution obtained by calculation from the measured static and total pressures is compared. Also to obtain the highly stable and convergence jets, it is turned out that the flow through a nozzle of constant expansion rate using the Coanda effect with an annular slit is the most preferable than that case through variable expansion rate nozzle. Furthermore, it is found that the pressure drop along the nozzle for the constant expansion rate nozzle is small relatively against to the case of variable expansion rate nozzle.

Performance Analysis and Configuration Design of the Thruster Nozzle for Ground-firing Test and Evaluation (지상연소시험평가용 추력기 노즐의 성능해석과 형상설계)

  • Kam, Ho-Dong;Kim, Jeong-Soo;Bae, Dae-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.16 no.2
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    • pp.10-16
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    • 2012
  • A computational analysis of nozzle flow characteristics and plume structure is conducted to examine performance of the supersonic nozzle employed in a thruster for ground firing test. At first, flow simulations in two-dimensional converging-diverging nozzle are performed for the verification of computational capability as well as turbulence model validity. Axisymmetric converging-diverging nozzles for ground firing test are analyzed with the k-${\omega}$ SST model. A performance penalty caused by flow separation in a diverging section is observed in initially-designed nozzle. The performance could be enhanced by the modification of the diverging section of nozzle contour.

Performance Analysis of the Supersonic Nozzle Employed in a Small Liquid-rocket Engine for Ground Firing Test (소형 액체로켓엔진 지상연소시험용 초음속 노즐의 성능해석)

  • Kam, Ho-Dong;Kim, Jeong-Soo;Bae, Dae-Seok;Lee, Jae-Won
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.321-324
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    • 2011
  • A computational analysis of nozzle flow characteristics and plume structure using Reynolds-averaged Navier-Stokes equations with $k-{\omega}$ SST turbulence model was conducted to examine performance of the supersonic nozzle employed in a small liquid-rocket engine for ground firing test. Computed results and experimental outcome of 2-D converging-diverging nozzle flow were compared for verifying the computational capability as well as the turbulence model validity. Numerical computations of 2-D axisymmetric nozzle flow was carried out with the selected model. As a result, flow separation with backflow appeared around the nozzle exit. This investigation was reported as a background data for the optimal nozzle design of small liquid-propellant rocket engine for ground test.

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Numerical Study of the Thrust Vectoring Characteristics in a Two-Dimensional Convergent Divergent Nozzle (2차원 축소확대노즐의 추력편향특성 수치해석연구)

  • Kang, Hyung Seok;Choi, Seong Man;Oh, Seong Hwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.2
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    • pp.94-104
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    • 2013
  • A numerical analysis has been conducted to determine the pitch thrust vectoring characteristics of a two-dimensional convergent divergent exhaust nozzle for supersonic aircraft application. The numerical analysis was done by using Fluent and verified by the experimental test results. Analysis was performed with pitch angle of $0^{\circ}$ and $20^{\circ}$ each at the ambient temperature condition. To see the effect of a ratio of pitch flap length and pitch flap height, the ratio was varied from 0.5 to 2.5. The numerical analysis shows that pitch thrust is changed greatly with pitch flap length. The big difference of the pitch thrust with pitch flap length is due to the shock interactions in the nozzle.

Characteristics of Entrainment Flow Rate in a Coanda Nozzle with or without Coaxial Contractor (코안다 노즐에서 중심 축소관 유무에 따른 유입량 특성)

  • Ha, Ji Soo;Shim, Sung Hoon
    • Journal of the Korean Institute of Gas
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    • v.18 no.2
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    • pp.21-27
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    • 2014
  • A MILD(Moderate and Intense Low oxygen Dilution) combustion, which is effective in the reduction of NOx, is considerably affected by the recirculation flow rate of hot exhaust gas to the combustion furnace. The present study used a coanda nozzle for the exhaust gas recirculation in a MILD combustor. A numerical analysis was accomplished to elucidate the effect of exhaust gas entrainment toward the furnace with or without a coaxial contractor. The result of the present CFD analysis showed that the entrainment mass flow rate without a coaxial contractor had 18% larger than that with a coaxial contractor when the mixed gas outlet pressure was ambient pressure. On the other hand, if the outlet pressure increased, the mass flow rate with a contractor was larger than that without a contractor. It could be analysed by the entrainment driving force composed with the nozzle throat pressure, inlet and outlet pressures and flow cross sectional area.

Performance Assessment of the Dual-Throat Nozzle Thrust Vector Control in a 3D Rectangular Nozzle (3D 직사각형 노즐에서 이중 스 로트 노즐 스러스트 벡터 제어의 성능 평가)

  • Wu, Kexin;Kim, Tae Ho;Kim, Heuy Dong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.24 no.4
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    • pp.12-24
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    • 2020
  • The dual-throat nozzle is an extremely effective method in the thrust vectoring control field, utilizing another convergent section to connect with the divergent part of the conventional convergent-divergent nozzle. In the present research, the numerical simulation is conducted to investigate the effects of the injection angle on thrust vectoring performance in a 3D supersonic nozzle. Five injection angles are discussed and core performance variations are analyzed, including the deflection angle, injected mass flow ratio, system resultant thrust ratio, efficiency, Mach number contour and streamline on the symmetry plane, and Mach number contours at different slices. Meaningful conclusions are offered for fighter jet designers.