Effects of back pressure on underexpanded jet behaviors of supercritical aviation kerosene
-
摘要:
对超临界RP-3航空煤油喷入加压准静止空气的射流特性进行了试验研究。在0.15～1.02 MPa的环境压力范围内，采用阴影成像技术记录了二维收缩喷嘴喷出的超临界RP-3射流的近喷嘴区域宏观射流形态。结果表明：超临界RP-3射流经历了与理想气体类似的欠膨胀射流过程，呈现出明显的桶形激波结构。通过十组分RP-3替代燃料的热力学相图进行的物理解释表明超临界RP-3射流在近喷嘴区域经历了一个或多个等熵膨胀、熵增压缩和等压混合过程。随着环境压力的升高，超临界RP-3射流形态从超高度欠膨胀状态转变成高度欠膨胀状态，射流扩张角、第一波节直径、第一波节马赫盘位置与直径均逐渐降低。
Abstract:The jet behaviors of supercritical RP-3 aviation kerosene injected with a pressurized quasi-quiescent air were experimentally investigated. Under the ambient pressure of 0.15—1.02 MPa, the near-nozzle macroscopic morphology of the supercritical RP-3 jets injected from a two-dimensional convergent nozzle was recorded by shadowgraph imaging. The results showed that supercritical RP-3 jets underwent an underexpanded jet process similar to that of an ideal-gas, exhibiting visible barrel shock structures. The physical interpretation performed through the thermodynamic phase diagram of a 10-component RP-3 surrogate showed that supercritical RP-3 jets underwent one or more isentropic expansion, entropy-increasing compression and isobaric mixing processes within the near-nozzle region. With the increase of the ambient pressure, the jet morphology of supercritical RP-3 changed from a very highly underexpanded state to a highly underexpanded state, and the jet expansion angle, the diameter of the first cell, and the position and diameter of the first cell Mach disk all decreased gradually.
-
图 3 不同环境压力下超临界RP-3射流阴影图像
Figure 3. Shadowgraph images of supercritical RP-3 jets at varying ambient pressures
图 4 $ {p_{{\text{chm}}}} = 0.38 $ MPa下RP-3射流物理解释
Figure 4. Physical interpretation of RP-3 jets at $ {p_{{\text{chm}}}} = 0.38 $ MPa
图 5 近喷嘴区域超临界RP-3高度欠膨胀射流示意图
Figure 5. Schematic illustration of a highly underexpanded jet for supercritical RP-3 in the near-nozzle region
图 6 射流扩张半角与喷嘴压比的函数关系
Figure 6. Jet expansion half angle as a function of the nozzle pressure ratio
图 7 第一波节直径与喷嘴压比的函数关系
Figure 7. Diameter of the first roll as a function of the nozzle pressure ratio
图 8 马赫盘位置与喷嘴压比的函数关系
Figure 8. Mach disk location as a function of the nozzle pressure ratio
图 9 马赫盘直径与喷嘴压比的函数关系
Figure 9. Mach disk diameter as a function of the nozzle pressure ratio
表 1 试验工况
Table 1. Test conditions
试验参数 数值 Tinj/K 720.0 pinj/MPa 2.88 Tamb/K 300 pamb/MPa 0.15, 0.38, 0.50, 1.02 ${\eta _0} = {p_{{\text{inj}}}}/{p_{{\text{amb}}}}$ 19.0, 7.6, 5.7, 2.8 
下载: 导出CSV
-
[1] SOBEL D R, SPADACCINI L J. Hydrocarbon fuel cooling technologies for advanced propulsion[J]. Journal of Engineering for Gas Turbines and Power, 1997, 119(2): 344-351. doi: 10.1115/1.2815581 [2] BRUENING G B, CHANG W S. Cooled cooling air systems for turbine thermal management[C]//Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration. American Society of Mechanical Engineers, 1999: V003T01A002: 1-7. [3] HUANG He, SPADACCINI L J, SOBEL D R. Fuel-cooled thermal management for advanced aeroengines[J]. Journal of Engineering for Gas Turbines and Power, 2004, 126(2): 284-293. doi: 10.1115/1.1689361 [4] EDWARDS T. USAF supercritical hydrocarbon fuels interests[R]. Reno, US: 31st Aerospace Sciences Meeting, 1993. [5] YANG V. Modeling of supercritical vaporization, mixing, and combustion processes in liquid-fueled propulsion systems[J]. Proceedings of the Combustion Institute, 2000, 28(1): 925-942. doi: 10.1016/S0082-0784(00)80299-4 [6] BELLAN J. Supercritical (and subcritical) fluid behavior and modeling: drops, streams, shear and mixing layers, jets and sprays[J]. Progress in Energy and Combustion Science, 2000, 26(4/5/6): 329-366. [7] CHEN L D. Heat transfer, fouling, and combustion of supercritical fuels[R]. AFOSR TR-94-0321, 1994. [8] ROY A, JOLY C, SEGAL C. Disintegrating supercritical jets in a subcritical environment[J]. Journal of Fluid Mechanics, 2013, 717: 193-202. doi: 10.1017/jfm.2012.566 [9] WU Peikuan, CHEN T H, NEJAD A S, et al. Injection of supercritical ethylene in nitrogen[J]. Journal of Propulsion and Power, 1996, 12(4): 770-777. doi: 10.2514/3.24100 [10] WU Peikuan, SHAHNAM M, KIRKENDALL K A, et al. Expansion and mixing processes of underexpanded supercritical fuel jets injected into superheated conditions[J]. Journal of Propulsion and Power, 1999, 15(5): 642-649. doi: 10.2514/2.5488 [11] LIN K C, COX-STOUFFER S K, JACKSON T A. Structures and phase transition processes of supercritical methane/ethylene mixtures injected into a subcritical environment[J]. Combustion Science and Technology, 2006, 178(1/2/3): 129-160. [12] STAR A M, EDWARDS J R, LIN Kuocheng, et al. Numerical simulation of injection of supercritical ethylene into nitrogen[J]. Journal of Propulsion and Power, 2006, 22(4): 809-819. doi: 10.2514/1.16621 [13] XU Qinglin, SUN Zhe, WANG Shangning, et al. A morphological study of supercritical fuel flash-boiling spray[J]. Fuel, 2022, 310: 122365. doi: 10.1016/j.fuel.2021.122365 [14] LAMANNA G, STOTZ I, WEIGAND B, et al. Supercritical fluid injection: an experimental study[R]. Brugge, Belgium: Proceedings of the 7th European Symposium on Aerothermodynamics, 2011. [15] LAMANNA G, OLDENHOF E, BAAB S, et al. Disintegration regimes near the critical point[R]. Tours, France: 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conferences, 2012. [16] BAAB S, LAMANNA G, WEIGAND B. Two-phase disintegration of high-pressure retrograde fluid jets at near-critical injection temperature discharged into a subcritical pressure atmosphere[J]. International Journal of Multiphase Flow, 2018, 107: 116-130. doi: 10.1016/j.ijmultiphaseflow.2018.04.021 [17] LIU Fushui, GAO Yongli, ZHANG Zheng, et al. Study of the spray characteristics of a diesel surrogate for diesel engines under sub/supercritical states injected into atmospheric environment[J]. Fuel, 2018, 230: 308-318. doi: 10.1016/j.fuel.2018.05.050 [18] 高伟, 林宇震, 付镇柏, 等. 超临界正十烷喷射到大气环境的喷射特性[J]. 航空动力学报, 2010, 25(9): 1984-1988. GAO Wei, LIN Yuzhen, FU Zhenbai, et al. Injection characteristics of supercritical n-decane into atmospheric environment[J]. Journal of Aerospace Power, 2010, 25(9): 1984-1988. (in ChineseGAO Wei, LIN Yuzhen, FU Zhenbai, et al. Injection characteristics of supercritical n-decane into atmospheric environment[J]. Journal of Aerospace Power, 2010, 25(9): 1984-1988. (in Chinese) [19] 高伟, 林宇震, 梁获胜, 等. 超临界航空煤油喷射的射流结构及相变过程[J]. 航空动力学报, 2009, 24(12): 2661-2665. GAO Wei, LIN Yuzhen, LIANG Huosheng, et al. Jet structures and phase transition process of supercritical aviation kerosene fuel injection[J]. Journal of Aerospace Power, 2009, 24(12): 2661-2665. (in ChineseGAO Wei, LIN Yuzhen, LIANG Huosheng, et al. Jet structures and phase transition process of supercritical aviation kerosene fuel injection[J]. Journal of Aerospace Power, 2009, 24(12): 2661-2665. (in Chinese) [20] 梁获胜, 高伟, 许全宏, 等. 超临界航空煤油喷射到大气环境的喷射特性[J]. 航空动力学报, 2009, 24(6): 1258-1263. LIANG Huosheng, GAO Wei, XU Quanhong, et al. Injection characteristics of the supercritical jet fuel injected into the atmospheric environment[J]. Journal of Aerospace Power, 2009, 24(6): 1258-1263. (in ChineseLIANG Huosheng, GAO Wei, XU Quanhong, et al. Injection characteristics of the supercritical jet fuel injected into the atmospheric environment[J]. Journal of Aerospace Power, 2009, 24(6): 1258-1263. (in Chinese) [21] GAO Wei, LIN Yuzhen, HUI Xin, et al. Injection characteristics of near critical and supercritical kerosene into quiescent atmospheric environment[J]. Fuel, 2019, 235: 775-781. doi: 10.1016/j.fuel.2018.08.048 [22] 申帅, 范玮, 靳乐, 等. 超临界燃油喷射特性受喷嘴长径比影响的实验研究[J]. 推进技术, 2018, 39(10): 2363-2369. SHEN Shuai, FAN Wei, JIN Le, et al. Experimental study on characteristics of supercritical fuel injection affected by nozzle length-diameter ratio[J]. Journal of Propulsion Technology, 2018, 39(10): 2363-2369. (in ChineseSHEN Shuai, FAN Wei, JIN Le, et al. Experimental study on characteristics of supercritical fuel injection affected by nozzle length-diameter ratio[J]. Journal of Propulsion Technology, 2018, 39(10): 2363-2369. (in Chinese) [23] 葛浩, 范育新, 王伟利, 等. 近/超临界RP-3航空煤油的喷射特性试验研究[J]. 航空动力学报, 2024, 39(8): 20220614. GE Hao, FAN Yuxin, WANG Weili, et al. Experimental study on injection characteristics of near/supercritical RP-3 aviation kerosene[J]. Journal of Aerospace Power, 2024, 39(8): 20220614. (in ChineseGE Hao, FAN Yuxin, WANG Weili, et al. Experimental study on injection characteristics of near/supercritical RP-3 aviation kerosene[J]. Journal of Aerospace Power, 2024, 39(8): 20220614. (in Chinese) [24] FAN Xuejun, YU Gong, LI Jianguo, et al. Effects of entry conditions on cracked kerosene-fueled supersonic combustor performance[J]. Combustion Science and Technology, 2007, 179(10): 2199-2217. [25] HUBER M L. NIST thermophysical properties of hydrocarbon mixtures database (supertrapp), version 3.2[M]. Gaithersburg, US: National Institute of Standards and Technology, 2007. [26] ZHONG Fengquan, FAN Xuejun, YU Gong, et al. Heat transfer of aviation kerosene at supercritical conditions[J]. Journal of Thermophysics and Heat Transfer, 2009, 23(3): 543-550. doi: 10.2514/1.41619 [27] LIU Guigui, LIN Yuzhen, LI Jiaju, et al. Flow characteristics and phase transition of subcritical to supercritical kerosene injections in a convergent nozzle[J]. Fuel, 2023, 334: 126518. doi: 10.1016/j.fuel.2022.126518 [28] KISLYAKOV N I, REBROV A K, SHARAFUTDINOV R G. Structure of high-pressure low-density jets beyond a supersonic nozzle[J]. Journal of Applied Mechanics and Technical Physics, 1975, 16(2): 187-195. [29] CRIST S, GLASS D R, SHERMAN P M. Study of the highly underexpanded sonic jet[J]. AIAA Journal, 1966, 4(1): 68-71. doi: 10.2514/3.3386 [30] GIBBINGS C, J, INGHAM, et al. Flow in a supersonic jet expanding from a convergent nozzle: CP-1197[R]. London, England: Her Majesty’s Stationery Office, 1972. -
点击查看大图
计量
- 文章访问数: 553
- HTML浏览量: 293
- PDF量: 29
- 被引次数: 0