成功大學博碩士論文系統

簡易檢索 / 詳目顯示

回結果列表

研究生：	許庫瑪 Kumar, Naresh
論文名稱：	氣體中旋流同軸噴注器之燃燒特性數值分析 Numerical analysis on combustion characterization of gas centered swirl coaxial injector
指導教授：	趙怡欽 Chao, Yei-Chin
學位類別：	碩士 Master
系所名稱：	工學院 - 航空太空工程學系 Department of Aeronautics & Astronautics
論文出版年：	2018
畢業學年度：	106
語文別：	英文
論文頁數：	73
外文關鍵詞：	gas centered swirl coaxial injector, numerical analysis, non-premixed combustion model, volume of fluid model
相關次數：	點閱：58 下載：13
分享至:	分享至facebook 分享至twitter

查詢本校圖書館目錄查詢臺灣博碩士論文知識加值系統勘誤回報

Numerical analysis of gas centered swirl coaxial injector was investigated with Discrete phase species transport model. The gas–liquid injector, widely used in a high-performance combustor, consists of a central oxidizer post and peripheral fuel holes for fluid injection. Gas centered swirl coaxial injector is generally considered to have better performance for oxidizer rich staged combustion (ORSC) cycle rocket engines. With the inherent merits of smaller droplet size, excellent atomization and mixing quality, less chance to cause spray pulsation, superior performance than that for traditional shear coaxial injectors can be achieved. The commercial tool ansys fluent was used for the simulation. SST, K-Omega turbulent model was found to be most suitable for this simulation model. Water liquid was injected in discrete phases and air was used as the oxidizer. The parametric analysis was done using ansys fluent. From the numerical results calculated with this modeling it is found that the spreading angle is decreased for the higher momentum flux ratio. The numerical results are evaluated against the experimental results. The numerical results showed a negligible error because of the computational grids.

TABLE OF CONTENTS

ABSTRACT	……………………………………………………………………………………I
ACKNOWLEDGEMENT	II
DECLARATION OF SOFTWARE USAGE	III
LIST OF TABLES	VI
LIST OF FIGURES	VII
CHAPTER 1.	INTRODUCTION	1
1.1	Gas centred swirl coaxial injector	1
1.2	Motivation and objectives	4
1.3	Literature review	5
1.3.1.	Staged combustion cycle	5
1.3.2.	Atomization and mechanism of shear coaxial injector	6
1.3.3.	Numerical Simulation of Sprays	9
CHAPTER 2.	THEORY OF NUMERICAL SIMULATION	11
2.1	Basics of Computational Fluid Dynamics	11
2.1.1.	Importance of Computational Fluid Dynamics	12
2.1.2.	Physics of Fluid	12
2.2	The Governing Equation	13
2.2.1.	Mass conservation equation	13
2.2.2.	Momentum conservation equation	14
2.2.3.	Energy conservation equation	15
2.2.4.	General Form of Navier-Stokes Equation	16
2.3	Turbulence modeling	16
2.4	The Species Balance Equation	17
2.5	Discrete phase modelling	18
2.6	Particles in turbulent flow modelling	19
2.7	Injection types	20
2.8	Droplet Particle type	21
2.8.1.	Numerical Approach to Breakup Modeling	21
2.8.2.	Turbulent Dispersion	21
2.9	Grids	22
2.9.1.	Polyhedral mesh	23
CHAPTER 3.	NUMERICAL SETUP AND SIMULATION	25
3.1	Geometry	25
3.2	Meshing	25
3.3	Solution methods	26
3.3.1	Pressure velocity coupling	26
3.3.2	Spatial discretization	26
3.3.3	Convergence	27
CHAPTER 4.	RESULTS AND DISCUSSION	28
4.1	Spray angle	28
4.2	Turbulent intensity	28
4.3	Parametric analysis	29
4.4	Droplet variation	29
4.5	Improvements to turbulent modelling	29
CHAPTER 5.	CONCLUSION	30
REFERENCES	31
TABLES……………………………………………………………………………………...35
FIGURES….	38

 

LIST OF TABLES

Table 1: Details of the Injector	35
Table 2: Spray angel comparison	36
Table 3: Experimental test condition where gas velocity of 100m/s and 250m/s were used in simulation.	37

 
LIST OF FIGURES
Figure 1: Staged combustion cycle with oxidizer-rich preburners and split fuel pump, (b) Fuel-rich gas-generator cycle. (ref. Manski et al, 1998)	38
Figure 2: Disintegration of cylindrical jet caused by (a) axial symmetric waves (b) asymmetric waves (c) aerodynamic forces (ref. Bayvel, liquid atomization, 1993)	39
Figure 3: Swirl injection film fragmentation process. Ref bayvel liquid atomization 1993	40
Figure 4: Instantaneous flow visualization of the break-up of the liquid jet by the annular air jet. (ref.Lasheras et al. 1998)	41
Figure 5: Cross section view of shear coaxial injector with four tangential ports      (ref.jeon, 2011)	42
Figure 6:  Schematic diagram of swirl injector. ref Young jun kim 2014	43
Figure 7: Geometry and computational grids of the model chamber with a single injector (ref. Young jun kim 2014)	44
Figure 8: 2D grid domain	45
Figure 9: Structured and unstructured grids	46
Figure 10: Boundary condition for pipe flow	47
Figure 11: Simulation Model	48
Figure 12: Close section view of the injector with four tangential ports	49
Figure 13: Cut section of the injector	50
Figure 14: Polyhedral domain for the meshing	51
Figure 15: Injection properties for the DPM model	52
Figure 16: Swirl dominated flow	53
Figure 17: Nitrogen volume fraction	54
Figure 18: Nitrogen volume fraction at three different planes	55
Figure 19: Water liquid volume fraction	56
Figure 20: Water liquid particle diameter	57
Figure 21: Water liquid particle diameter	58
Figure 22: Particle diameter for 1000 tracks	59
Figure 23: Particle diameter for 2000 tracks	60
Figure 24: Water liquid mass fraction	61
Figure 25: Air mass fraction contour	62
Figure 26: Turbulent intensity contour	63
Figure 27: Particle data results on turbulent intensity	64
Figure 28: Water liquid particle mass	65
Figure 29: Water liquid particle diameter on XY plane	66
Figure 30: Water liquid molar concentration	67
Figure 31: Water liquid mass fraction	68
Figure 32: Mass fraction of air	69
Figure 33: Velocity profile for oxidizer velocity 100m/s	70
Figure 34: Turbulent intensity profile for oxidizer velocity 100m/s	71
Figure 35: Velocity profile for oxidizer velocity 250m/s	72
Figure 36: Turbulent intensity profile for oxidizer velocity 20m/s	73
 
 

                                    

REFERENCES
[1]. Bayvel L., Orzechowski, Liquid Atomization, Taylor & Francis, 1993
[2]. Bazarov, V.G., Yang, V., “Liquid -Propellant Rocket Engine Injector Dynamics,” Journal of Propulsion and Power, vol. no. 5, no. 5, 9-10 1998.
[3]. Cheng , G.C., Davis, R.D., Johnson, C.W., Jeffrey, A.M., Greisen, D.A., Cohn, R.K., “Development of GOX/Kerosene Swirl Coaxial Injector Technology,” in 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville Alabama. 20-23 July 2003.
[4]. Cheng, G.C., Johnson, C.W., Muss, J.A., Cohn, R.K., “Swirl Coaxial Injector Development Part 2: CFD modelling,” in JANNAF Joint Propulsion Meeting, Destion, FL, 2002.
[5]. Cohn, R.K., Strekey, P.A., Bates, R.W., Talley, D.G., “Swirl Coaxial Injector Development,” 44th AIAA Aerospace Sciences Conference, Reno, NV, 9-12 July 2003.
[6]. Dongjun Kim , Poonggyoo Han, Ji-Hyuk Im, Youngbin yoon, Bazarov, V.G., “Effects of Recess on the Spray Characteristics of Liquid-Liquid Swirl Coaxial Injector,” Journal of Propulsion and Power, vol. 23, no. 6, Nov-Dec 2007.
[7]. Fu Qing-fei, Yang Li-jun, Qu Yuan-yuan, “Measurement of Annular Liquid Film Thickness in an Open-end Swirl Injector,” Aerospace Science and Technology, vol. 15, pp. 117-124, 2011.
[8]. Gomi, H., “Pneumatic Atomization with Coaxial Injector,” 1984.
[9]. Gujeong Park, Ingyu Lee, Jungho Lee, Youngbin Yoon, “Measurement of Film Thickness in Gas-Centered Swirl Coaxial Injector,” in 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Clevelad, OH, 28-30 July 2014.
[10]. Ingebo, R., “Gas property Effects on Dropsize of Simulated Fuel Sprays,” Journal of Propulsion and Power, vol. 7, no. 4, pp. 467-472, 1991.
[11]. Ji-Hyuk Im, Seongho Cho, Youngbin Yoon, Insang Moon, “Comparative Study on Spray Characteristics of Gas-Centered and Liquid-Centered Swirl Coaxial Injector,” Journal of Propulsion and Power, vol. 26, no. 6, Nov-Dec 2010.
[12]. ]Kendrick, D., Herding, G., Socuflaire, P., Rolon, C., Candel, S., “Effect of a Recess on Cryogenic Flame Stabilization,” Combustion and Flame, vol. 118, no. 3, pp. 327-339, 1999.
[13]. Kenny, R.J., Hulka, J.R., Moser, M.D., Rhys, N.O., “Effect of Chamber Backpressure on Swirl Injector Fluid Mechanics,” Journal of Propulsion and Power, vol.25, no. 4, Jul-Aug 2009.
[14]. Kuo, K. K., Recent Advances in Spray Combustion, Volume I: Spray Atomization and Drop Burning Phenomena Volume I, AIAA, 1996.
[15]. Kuo, K. K., Recent Advances in Spray Combustion, Volume II: Spray Atomization and Drop Burning Phenomena Volume II, AIAA, 1996.
[16]. Lefebvre, A.H., Atomization and Sprays, Hemisphere Publishing Corporation, 1989.
[17]. Lesheras, J.C., Hopfinger, E.J., “Break-up and Atomization of a Round water Jet by a High-Speed Annular Air Jet,” Journal of fluid Mechanics, vol. 357, pp. 351-379, 1998.
[18]. Lesheras, J.C., Hopfinger, E.J., “Liquid Jet Instability and Atomization in a Coaxial Gas Stream,” Journal of Fluid Mechanics Annu. Rev., vol. 32, pp. 275-308, 2000.
[19]. Li Xuan, Tian Liang, Zhu Shaohua, Xu Xu, “The Preliminary Study of Oxygen-Centered kerosene-Swirl Coaxial Injector,” In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cleveland OH, 28-30 July 2014.
[20]. Lightfoot, M.D.A., Danczy, K.S.A., “Spray Nonuniformities in Gas-Centered Swirl-Coaxial Injectors,” in 11th Annual Conference on Liquid Atomization and Spray System, Vali, Colorodo, July 2009.
[21]. Lightfoot, M.D.A., Danczy, K.S.A., Talley, D.G., “Atomization in Gas-Centered Swirl Coaxial Injectors,” in ILASS America, 19th Annual Conference on Liquid Atomization and Spray System, Toronto, Canada, May 2006.
[22]. Lightfoot, M.D.A., Danczy, K.S.A., Talley, D.G., “Atomization Rate of Gas-Centered Swirl Coaxial Injector,” in ILASS America, 21 st Annual Conference on Liquid Atomization and Spray System, Orlando, Florida, May 2008.
[23]. Lightfoot, M.D.A., Schumaker, S.A., Danczyk, S.A., Villasmil, L., “The Effect Of Swirl on Gas-Centered Swirl Coaxial Injector Sprays,” in JANNAF Joint Meeting, Huntsville, AL, 5-9 Dec 2011.
[24]. Long, M.R., Anderson, W.E., “Oxidizer-Rich Staged Combustion Cycle Pre-burner and Main Chamber Injection Testing at Purdue University,” in 40 th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Lauderdale, Florida, 11-14 July 2004.
[25]. Meyer, T.R., Lightfoot, M.D.A., Gord, J.R., “Ballistic-Imaging Study of Liquid Breakup in Gas-Centered Swirl Coaxial Rocket Sprays,” in 11 th Triennial International Annual Conference on Liquid Atomization and Sprays, Vali, Colorado, July 2009.
[26]. Meyer, W., Krulle, G., “Rocket Engine coaxial Injector Liquid/Gas Interface Flow Phenomena,” Journal of Propulsion and Power, vol. 12, no. 6, Nov-Dec 1996.
[27]. Miller, K., Sisco, J., Nugent, N., Anderson, W., “Experimental Study Of Combustion Instabilities in a Single-Element Coaxial Injector,” in 41 st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Tucson, Arizona, 10-13 July 2005.
[28]. Young, J.K., Sohn, C.H., Hong, M., “An Analysis of Fuel-Oxidizer Mixing and Combustion Induced by Swirl Coaxial Jet Injector with a Model of Gas-Gas Injection,” Aerospace Science and technology vol. 37, no. 37, pp 37-47, 2014.
[29]. Huzel, D.K., Huang, D.H., “Modern Engineering for Design of Liquid-Propellant Rocket”, Progress in Astronautics and Aeronautics, vol.147, AIAA, Washington, DC, p.35, 1992.
[30]. Schumaker, S.A., Lightfoot, M.D.A., Danczy, K.S.A., “Effect of Cup Length on Film Profiles in Gas-Centered Swirl Coaxial Injectors,” in 47 th AIAA Aerospace Science Meeting, Orlando OL, 5-8 January 2009.
[31].http://www.afs.enea.it/project/neptunius/docs/fluent/html/ug/mainpre.htm

校內：2023-07-27公開
校外：2023-07-27公開

簡易檢索 / 詳目顯示

相關論文