[논문]충격파 터널을 이용한 고속추진기관 시험 연구

박기수; 변종렬; 최호진; 진유인; 박철; 황기영

doi:10.6108/kspe.2014.18.5.043

충격파 터널을 이용한 고속추진기관 시험 연구
High Speed Propulsion System Test Research Using a Shock Tunnel 원문보기

한국추진공학회지 = Journal of the Korean Society of Propulsion Engineers, v.18 no.5, 2014년, pp.43 - 53

박기수 (School of Mechanical, Aerospace and Systems Engineering, Korea Advanced Institute of Science and Technology) , 변종렬 (Advanced Propulsion Technology Center, Agency for Defense Development) , 최호진 (Advanced Propulsion Technology Center, Agency for Defense Development) , 진유인 (Accurately Guided Vehicle System, University of Science and Technology) , 박철 (School of Mechanical, Aerospace and Systems Engineering, Korea Advanced Institute of Science and Technology) , 황기영 (Advanced Propulsion Technology Center, Agency for Defense Development)

초록
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충격파 터널은 초음속 및 극초음속 비행조건의 유동장을 지상에서 가장 유사하게 모사할 수 있는 시험설비로서, 거의 반세기 동안 전 세계적으로 유용하게 운용되고 있다. 국내의 극초음속 비행체에 대한 많은 관심의 결과로 충격파 시험장치에 대해 주목하고 있으며, 최근에 KAIST에서는 중간 크기의 충격파 터널을 갖추게 되었다. 본 논문은 개발된 충격파 터널의 성능과 최근 수행된 모델 스크램제트 시험자료를 제시하고 있다. 본 연구에서 모사된 자유흐름 유동조건은 마하수 5.7 비행속도에 해당하며, 이러한 비행조건에서 스크램제트의 초음속 연소기내에 유동 환경을 모사하였다.

Abstract ▼ AI-Helper

Shock tunnels are known to be capable of simulating flow-field environments of supersonic and hypersonic flights. They have been operated successfully world-wide for almost half a century. As a consequence of the strong interest in hypersonic vehicles in Korea, attention has been given on this type of facility and so an intermediate-sized shock tunnel has lately been built at KAIST. In the light of this, this paper presents our tunnel performance and some of the model scramjet test data. The freestream flow used in this work replicates a supersonic combustor environment for a Mach 5.7 flight speed.

주제어

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문제 정의

In this work, the overall design, manufacture, and performance testing skills of the high speed propulsion system using the shock tunnel are presented. At the low flow enthalpy with total temperature of 1610 K, the ethylene auto-ignition did not occur.
A series of experiments using the hydrocarbon fuel, ethylene, is now actively in progress. The aims of this work are to verify that the shock tunnel is capable of conducting scramjet combustion test and also to inform nationally the overall design, manufacture, and performance testing skills of high speed propulsion system using the shock tunnel. This paper covers three aspects: (1) the method of characterizing the tunnel flow condition, (2) our tunnel performance and, (3) some of the recent scramjet test data.

제안 방법

The steady laminar flow simulation without the fuel injection and cavity was performed using the Eilmer3 code. The purpose for this simulation was to validate the freestream flow condition and also to obtain base-line data to compare with the experiment.
The aims of this work are to verify that the shock tunnel is capable of conducting scramjet combustion test and also to inform nationally the overall design, manufacture, and performance testing skills of high speed propulsion system using the shock tunnel. This paper covers three aspects: (1) the method of characterizing the tunnel flow condition, (2) our tunnel performance and, (3) some of the recent scramjet test data.

대상 데이터

The mass, momentum, energy, and species flux between finite volume cells were calculated using an ADAPTIVE scheme. 791 x 63 (49,833) grid cells were used.
4 shows a computational domain of the scramjet model. In total, 50,490 grid cells were used.
The tunnel is about 13 m long. It consists of a shock tube, a nozzle, a test section, and a dump tank. The shock tube contains three axisymmetric chambers: a driver tube, a transition section, and a driven tube.
The scramjet consists of a contoured-wedge, a main flat body, a cowl, and a fuel injection module. The total length of the model was 390 mm.
It consists of a shock tube, a nozzle, a test section, and a dump tank. The shock tube contains three axisymmetric chambers: a driver tube, a transition section, and a driven tube. They are initially separated by the first and the second diaphragms.
The scramjet consists of a contoured-wedge, a main flat body, a cowl, and a fuel injection module. The total length of the model was 390 mm. The height of the main body was 68 mm.
The surface pressures were measured at four different locations. They were located at 0.22 m, 0.26 m, 0.29 m, and 0.32 m from the scramjet leading edge. Other locations shown in Fig.

이론/모형

Flow properties were calculated using a compressible Navier-Stokes solver Eilmer3 which is also an in-house code from The University of Queensland[18]. The code performs time integration of Navier-Stokes equations using cell-centered finite-volume formulation.
Flow direction is from left to right. Optical visualization images were obtained using a shadowgraph technique. The images were recorded using a high speed camera IDT XS4 with shutter speed of 0.
The freestream condition herein denotes the combustor entrance condition. The images for the fuel injection was captured using a Schlieren technique. The images were recorded using a high speed camera Photron FASTCAM SA-X type 324K-C2 with shutter speed of 10 μ sec.
The solver uses a multiple-block structured mesh. The mass, momentum, energy, and species flux between finite volume cells were calculated using an ADAPTIVE scheme. 791 x 63 (49,833) grid cells were used.
The steady laminar flow simulation without the fuel injection and cavity was performed using the Eilmer3 code. The purpose for this simulation was to validate the freestream flow condition and also to obtain base-line data to compare with the experiment.

참고문헌 (21)

Rowan, S.A. and Paull, A., "Performance of a Scramjet Combustor with Combined Normal and Tangential Fuel Injection," Journal of Propulsion and Power, Vol. 22, No. 6, pp. 1334-1338, 2006.

상세보기
Stalker, R.J., Paull, A., Mee, D.J., Morgan, R.R. and Jacobs, P.A., "Scramjets and Shock Tunnels - The Queensland Experience," Progress in Aerospace Sciences, Vol. 41, pp. 471-453, 2005.

상세보기
Hui, Y., Feng, L. and Baigang, S., "Trajectory Analysis of Fuel Injection into Supersonic Cross Flow Based on Schlieren Method," Chinese Journal of Aeronautics, Vol. 25, Issue 1, pp. 42-50, 2012.

상세보기
Razzaqi, S.A. and Smart, M.K., "Hypervelocity Experiments on Oxygen Enrichment in a Hydrogen-Fueled Scramjet," AIAA Journal, Vol. 49, No. 7, pp. 1488-1497, 2011.

상세보기
Kang, S.H., Lee, Y.J. Yang, S.S., Smart, M.K. and Suraweera, M.V., "Cowl and Cavity Effects on Mixing and Combustion in Scramjet Engines," Journal of Propulsion and Power, Vol. 27, No. 6, pp. 1169-1177, 2011.

상세보기
Osgerby, I.T., Smithson, H.K. and Wagner, D.A., "Supersonic Combustion Tests with a Double-Oblique-Shock Scramjet in a Shock Tunnel," AIAA Journal, Vol. 8, No. 9, pp. 1703-1705, 1970.

상세보기
McIntyre, T.J., Houwing, A.F.P., Palma, R.C., Rabbath, P.A.B. and Fox, J.S., "Optical and Pressure Measurements in Shock Tunnel Testing of a Model Scramjet Combustor," Journal of Propulsion and Power, Vol. 13, No. 3, pp. 388-394, 1997.

상세보기
Wendt, M.N. and Stalker, R.J., "Transverse and Parallel Injection of Hydrogen with Supersonic Combustion in a Shock Tunnel," Shock Waves, Vol. 6, Issue 1, pp. 53-59, 1996.

상세보기
Stalker, R.J., Morgan, R.G. and Paull, A., "A Shock Tunnel Investigation of Scramjet Performance with Partially Premixed Combustion," 7th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Norfolk, VA., U.S.A., AIAA-96-4534, Nov. 1996.
Ben-Yakar, A., Mungal, M.G. and Hanson, R.K., "Time Evolution and Mixing Characteristics of Hydrogen and Ethylene Transverse Jets in Supersonic Crossflows," Physics of Fluids, Vol. 18, No. 2, 026101, 2006.

상세보기
Ben-Yakar, A. and Hanson, R.K., "Ultra-Fast-Framing Schlieren System for Studies of the Time Evolution of Jets in Supersonic Crossflows," Experiments in Fluids, Vol. 32, pp. 652-666, 2002.

상세보기
Yang, I., "Design and Performance Evaluation of a Liquid-Fueled Scramjet Engine Model," PhD Dissertation, KAIST, Daejeon, Korea, 2013.
Jacobs, P.A., "Shock Tube Modelling with L1d," Report 13/98, Department of Mechanical Engineering, The University of Queensland, Brisbane, Australia, 1998.
Gollan, R.J., "Yet Another Finite-Rate Chemistry Module for Compressible Flow Codes," Report 9/2003, Department of Mechanical Engineering, The University of Queensland, Brisbane, Australia, 2003.
Mallinson, S.G., Mudford, N.R. and Gai, S.L., "Pitot Pressure Survey of the 1/2" Throat 12" Exit Conical Nozzle for the T3 Free-Piston Shock Tunnel," Aerospace Technical Report 92-1, University of New South Wales, Australian Defence Academy, Canberra, Australia, 1992.
Brieschenk, S., O'Byrne, S. and Kleine, H., "Laser-Induced Plasma Ignition Experiments in a Scramjet Inlet," 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, FL., U.S.A., AIAA-2011-504, Jan. 2011.
Park, G., "Hypervelocity Aerothermodynamics of Blunt Bodies Including Real Gas Effects," PhD Dissertation, The University of New South Wales, Canberra, Australia, 2010.
Jacobs, P.A., "Eilmer's Theory Book: Basic Models for Gas Dynamics and Thermochemistry," Report 2010-09, The University of Queensland, Brisbane, Australia, 2010.
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