Experimental study on RP3 aviation kerosene oblique detonation engine
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摘要: 在高马赫数飞行条件下，斜爆轰发动机热力学循环效率高，燃烧室长度短，是近些年国内外研究热点。但是，目前斜爆轰发动机试验研究都是使用氢气或者乙烯燃料，还没有航空煤油的试验结果。为了研究RP3航空煤油在斜爆轰发动机上的应用可行性，在JF-12激波风洞上开展了冷态RP3航空煤油斜爆轰发动机自由射流试验研究，JF-12激波风洞有效试验时间50 ms。针对航空煤油点火延迟时间长的难点，提出了鼓包强制起爆新技术。模拟了飞行马赫数9的状态，试验气流总温3800 K，平均当量比为0.9。试验中获得了稳定的斜爆轰波，证明了RP3航空煤油在斜爆轰发动机上的应用可行性。Abstract: The oblique detonation engine has great potential application in high flight Mach number airbreathing vehicles because of its higher thermodynamic efficiency and smaller size. The research about the oblique detonation engine is renewed all over the world in recent years. However, all of the oblique detonation experiments are conducted with hydrogen fuel or ethylene. There is no experimental result about the kerosene oblique detonation. In order to examine the application feasibility of kerosene oblique detonation engine, the experimental study on the liquid RP3 aviation kerosene oblique detonation engine is conducted in JF-12 shock tunnel and the test time is about 50ms. The difficult issue for the initiation of kerosene oblique detonation is that the ignition delay time of kerosene-air is too long and the autoignition cannot occur in the combustor. A new forced detonation initiation method is put forth to deal with this key issue. The total temperature of JF-12 shock tunnel is 3800 K and the global equivalence ratio is 0.9, which replicates Mach 9 flight-equivalent condition. The steady-state oblique detonation is obtained successfully during the experiments, which demonstrates the application feasibility of the kerosene oblique detonation engine.
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图 1 斜爆轰发动机示意图（a）外喷射型（b）内喷射型
Figure 1. Schematic of oblique detonation engine （a） External injection （b） Internal injection
图 4 斜爆轰发动机模型和小支板照片
Figure 4. The pictures of oblique detonation engine model and two struts
图 5 满足当量比的氢气/空气和航空煤油/空气的点火延迟时间
Figure 5. The ignition delay time of stoichiometric H2/air and kerosene/air at 0.1 MPa
图 6 氢气/空气斜爆轰的诱导区长度（Test 20190710）
Figure 6. The induction length of H2/air oblique detonation （Test 20190710）
图 7 斜爆轰波强制起爆原理图 （a）自然起爆过程 （b）鼓包强制起爆过程
Figure 7. Schematic of ODW induced by a wedge with a small bump（a）conventional initiation（b）bump forced initiation
图 9 航空煤油/空气斜爆轰波的非定常起爆过程（Test 20220110）
Figure 9. The transient initiation process of RP3/air oblique detonation （Test 20220110）
图 10 氢气/空气斜爆轰波的非定常起爆过程（Test 20190710）
Figure 10. The transient initiation process of H2/air oblique detonation （Test 20190710）
图 11 斜爆轰波和斜激波的纹影照片（Test 20220110/ Test 20220114）
Figure 11. The flow field of oblique detonation and oblique shock wave（Test 20220110/ Test 20220114）
图 12 燃烧室上下壁面压力分布（Test 20220105）
Figure 12. The pressure distribution along the combustor wall（Test 20220105）
图 13 CJ爆轰波在不同初始温度下的压比
Figure 13. Pressure ratio of CJ detonation under different static temperatures
图 14 航空煤油/空气和氢气/空气斜爆轰波压比的比较（Test 20220110/ Test 20190710）
Figure 14. The pressure distribution along the combustor wall（Test 20220110/ Test 20190710）
表 1 风洞试验参数
Table 1. The experimental parameters
Cases Total temperature
（K）Total pressure
（MPa）StaticTemperature
（K）Static pressure
（Pa）Free stream
Mach numberFree stream
velocity （m/s）Test 20220105 3867 4.09 485 839 6.53 2884 Test 20220110 3865 4.08 484 829 6.54 2884 Test 20220112 3860 4.06 483 824 6.54 2882 Test 20220114 3799 3.78 474 768 6.55 2857 
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