Experiment on buzz characteristics of two-dimensional,twin-duct supersonic inlet
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摘要:
对一种超声速双侧二元进气道在马赫数2.6条件下的喘振特性开展试验研究，通过分析进气道沿程不同位置的压力变化规律，获得了进气道从不起动到再起动过程的流动特性。结果表明：不同内流道堵塞度下，双侧布局的进气道喘振表现出了两种不同模式：双侧进气道同时喘振；一侧进气道喘振，另一侧进气道深度超临界工作。对比不同喘振模式下的进气道压力特性发现：双侧进气道喘振表现为低频振荡形式，内流道的压力变化与激波的周期性往复运动密切相关，喘振频率为21.5 Hz，喘振压力峰值约为来流总压的75%；单侧进气道喘振则表现为高频振荡形式，内流道的压力振荡由流动分离主导，喘振频率在325 Hz以上，为双侧进气道喘振频率的15倍，喘振压力峰值接近于来流总压。
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关键词:
- 超声速双侧二元进气道 /
- 风洞试验 /
- 喘振特性 /
- 振荡压力 /
- 喘振频率
Abstract:An experimental investigation on the buzz characteristics of a two-dimensional, twin-duct supersonic inlet was carried out at Mach number 2.6. By analyzing the pressure variation law at different positions of the inlet, the flow characteristics were attained while the inlet operation changed from unstarting to restarting. Results showed two modes of buzzing at different throttle choking ratios: both of the inlet ducts buzzed together; one of the inlet ducts buzzed while the other one worked at a highly supercritical operation. By comparing the inlet pressure characteristics under different buzzing modes, it was noted that low-frequency oscillation was observed when both of the inlet ducts buzzed together, and the pressure variation was closely related to periodic shock wave movement. The buzz frequency was 21.5 Hz, and the peak value of the fluctuating pressure was about 75% of the total pressure of free-stream flow. On the contrary, high-frequency oscillating was noted when only one inlet duct buzzed, and the pressure oscillation was dominated by flow separation. The buzz frequency reached over 325 Hz, which was about 15 times of the frequency for the first mode of buzzing, and the amplitude peak was found to be approximate to the total pressure of free-stream flow.
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图 3 进气道动态压力时域变化曲线（工况1，双侧喘振→再起动）
Figure 3. Dynamic pressure time history of the inlet （state 1，both inlet ducts buzzing→restarting）
图 4 进气道的沿程静压变化曲线（工况1，双侧喘振→再起动）
Figure 4. Static pressure distribution of the inlet（state 1，both inlet ducts buzzing→restarting）
图 5 进气道喘振过程的动态压力时域变化曲线放大图（工况1，Lc=41 mm）
Figure 5. Enlarged view of dynamic pressure time history in the buzzing duration of the inlet （state 1，Lc=41 mm）
图 6 进气道喘振第4个和第5个周期的动态压力时域变化曲线放大图（工况1，Lc=41 mm）
Figure 6. Enlarged view of dynamic pressure time history of the inlet during the fourth and the fifth buzzing cycle（state 1，Lc=41 mm）
图 7 进气道喘振过程的动态压力功率谱特性（工况1，Lc=41 mm）
Figure 7. Power spectrum characteristics of dynamic pressure in the buzzing duration of the inlet （state 1，Lc=41 mm）
图 9 进气道内流道空腔模型简化示意图
Figure 9. Simplified cavity model sketch of the inlet interior duct
图 10 进气道的动态压力时域变化曲线（工况2，单侧喘振→再起动）
Figure 10. Dynamic pressure time history of the inlet （state 2，one-sided inlet duct buzzing→restarting）
图 11 进气道的沿程静压变化曲线（工况2，单侧喘振→再起动）
Figure 11. Static pressure distribution of the inlet（state 2，one-sided inlet duct buzzing→restarting）
图 12 进气道的动态压力时域变化曲线放大图（工况2，Lc=41 mm）
Figure 12. Enlarged view of dynamic pressure time history of the inlet （state 2，Lc=41 mm）
图 13 进气道喘振过程的喉道测点动态压力功率谱特性（工况2，Lc=41 mm）
Figure 13. Power spectrum characteristics of dynamic pressure in the buzzing duration for the inlet throat measuring point（state 2，Lc=41 mm）
图 14 进气道的动态压力时域变化曲线放大图（工况2，Lc=41～45mm）
Figure 14. Enlarged view of dynamic pressure time history of the inlet （state 2，Lc=41～45mm）
图 15 右侧进气道的动态压力功率谱特性（工况2，Lc=45 mm）
Figure 15. Power spectrum characteristics of dynamic pressure of the right-sided inlet （state 2，Lc=45 mm）
图 16 进气道的动态压力时域变化曲线放大图（工况2，Lc=55 mm）
Figure 16. Enlarged view of dynamic pressure time history of the inlet （state 2，Lc=55 mm）
图 17 右侧进气道的动态压力功率谱特性（工况2，Lc=55 mm）
Figure 17. Power spectrum characteristics of dynamic pressure of the right-sided inlet （state 2，Lc=55 mm）
表 1 不同锥位下进气道的堵塞度（工况1）
Table 1. Throttle choking ratios of the inlet at different cone positions （state 1）
Lc/mm Ktr/% 29 32.9 30 33.8 31 34.8 32 35.7 41 44.9 
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表 2 进气道不同测点的压力稳定值及持续时间（工况1，左侧进气道）
Table 2. Stable value and continuance of the inlet pressure for different measuring points （state 1，left-sided inlet）
测点 x/H p/p0 δt2/s pl1 2.28 3.2 0.0257 pl2 3.35 5.3 0.0170 pl3 4.88 5.4 0.0077 pl4 8.09 0
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表 3 不同锥位下进气道的堵塞度（工况2）
Table 3. Throttle choking ratios of the inlet at different cone positions （state 2）
Lc/mm Ktr/% 27 31.1 34 37.7 41 44.9 45 49.2 55 60.7
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表 4 右侧进气道不同测点的压力振荡值对比（工况2，Lc=45 mm）
Table 4. Oscillatory value of the right-sided inlet pressure for different measuring points （state 2，Lc=45 mm）
测点 x/H pmax/p0 pmin/p0 △p/p0 pr1 2.28 11.8 3.2 8.6 pr2 3.35 16.5 4.1 12.4 pr3 4.88 15.8 3.2 12.6 pr4 8.09 11.4 6.5 4.9
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表 5 右侧进气道不同测点的压力振荡值对比（工况2，Lc=55 mm）
Table 5. Oscillatory value of the right-sided inlet pressure for different measuring points （state 2，Lc=55 mm）
测点 x/H pmax/p0 pmin/p0 △p/p0 pr1 2.28 14.4 3.4 11.0 pr2 3.35 18.2 4.2 14.0 pr3 4.88 19.9 5.6 14.3 pr4 8.09 14.0 9.4 4.6
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[1] OSWATITSCH K. Pressure recovery for missiles with reaction propulsion at high supersonic speeds: NASA TM 1140 [R]. Washington DC: NASA,1944. [2] FERRI A,NUCCI L M. The origin of aerodynamic instability of supersonic inlets at subcritical conditions: NASA RM L50K30 [R]. Washington DC: NASA,1951. [3] FISHER S A,NEALE M C,BROOKS A J. On the sub-critical stability of variable ramp intakes at Mach numbers around 2: ARC-R/M-3711 [R]. Farnborough,England: National Gas Turbine Establishment,1970. [4] DAILEY C L. Supersonic diffuser instability[D]. Pasadena,U S: California Institute of Technology,1955. [5] ORLIN W J,DUNSWORTH L C. A criterion for flow instability in supersonic diffuser inlets: Report NO. 5144 [R]. Cazenovia,US: Marquardt Aircraft Company,1951. [6] STERBENTZ W H,EVAVARD J C. Criterions for prediction and control of ram-jet flow pulsations: NACA TN 3506 [R]. Cleveland,US: NACA,1955. [7] NAGASHIMA T,OBOKATA T,ASANUMA T. Experiment of supersonic air intake buzz: Report NO. 481[R]. Tokyo,Japan: Institute of Space and Aeronautical Science,1972. [8] SOLTANI M R,FARAHANI M,ASGARI KAJI M H. An experimental study of buzz instability in an axisymmetric supersonic inlet[J]. Scientia Iranica,2011,18(2): 241-249. doi: 10.1016/j.scient.2011.03.019 [9] TRAPIER S,DUVEAU P,DECK S. Experimental study of supersonic inlet buzz[J]. AIAA Journal,2006,44(10): 2354-2365. doi: 10.2514/1.20451 [10] 李宏东,朱守梅,朱璞,等. 超声速颌下进气道亚临界振荡特性试验研究[J]. 推进技术,2015,36(11): 1601-1609. LI Hongdong,ZHU Shoumei,ZHU Pu,et al. Experimental investigation on sub-critical oscillation characteristics of supersonic chin inlet[J]. Journal of Propulsion Technology,2015,36(11): 1601-1609. (in ChineseLI Hongdong, ZHU Shoumei, ZHU Pu, et al. Experimental investigation on sub-critical oscillation characteristics of supersonic chin inlet[J]. Journal of Propulsion Technology, 2015, 36(11): 1601-1609. (in Chinese) [11] TRIMPI RL. A theory for stability and buzz pulsation amplitude in ram jets and an experimental investigation including scale effects: NACA-TR-1265 [R]. Cleveland,US: NACA,1956. [12] FISHER S A. On the mechanism of supersonic intake instability,with some thoughts for further work[R]. Melbourne,Australia: Aeronautical Research Labs,1970. [13] WIE D,KWOK F,WALSH R. Starting characteristics of supersonic inlets: AIAA-96-2914[R]. Lake Buena Vista,US: AIAA,1996. [14] LU P J,JAIN L T. Numerical investigation of inlet buzz flow[J]. Journal of Propulsion and Power,1998,14(1): 90-100. doi: 10.2514/2.5254 [15] NEWSOME R W. Numerical simulation of near-critical and unsteady,subcritical inlet flow[J]. AIAA Journal,1984,22(10): 1375-1379. doi: 10.2514/3.48577 [16] TRAPIER S,DECK S,DUVEAU P,et al. Delayed detached-eddy simulation of supersonic inlet buzz[C]//Proceedings of the 37th AIAA Fluid Dynamics Conference and Exhibit. Reston,US: AIAA,2007: 1-15. [17] 王玉峰,杨宝娥. 超声速进气道喘振的机理研究[J]. 火箭推进,2008,34(1): 17-22. WANG Yufeng,YANG Baoe. Study of the buzz mechanism of supersonic inlets[J]. Journal of Rocket Propulsion,2008,34(1): 17-22. (in Chinese doi: 10.3969/j.issn.1672-9374.2008.01.004WANG Yufeng, YANG Baoe. Study of the buzz mechanism of supersonic inlets[J]. Journal of Rocket Propulsion, 2008, 34(1): 17-22. (in Chinese) doi: 10.3969/j.issn.1672-9374.2008.01.004 [18] 代珂,郭峰,朱剑锋,等. 基于DMD方法的超声速进气道喘振特性分析[J]. 航空动力学报,2019,34(5): 1076-1084. DAI Ke,GUO Feng,ZHU Jianfeng,et al. Characteristics investigation on supersonic inlet buzz with dynamic mode decomposition method[J]. Journal of Aerospace Power,2019,34(5): 1076-1084. (in ChineseDAI Ke, GUO Feng, ZHU Jianfeng, et al. Characteristics investigation on supersonic inlet buzz with dynamic mode decomposition method[J]. Journal of Aerospace Power, 2019, 34(5): 1076-1084. (in Chinese) [19] SHI Wen,CHANG Juntao,WANG Youyin,et al. Buzz evolution process investigation of a two-ramp inlet with translating cowl[J]. Aerospace Science and Technology,2019,84: 712-723. doi: 10.1016/j.ast.2018.11.016 -
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