预冷式超声速引射器启动和负载特性

doi:10.7527/S1000-6893.2024.30701

Abstract

Abstract:

In the field of aerospace engineering， supersonic ejectors find extensive applications， typically for suctioning secondary flows and generating low-pressure environments. To enhance the performance of supersonic ejectors， this paper proposes a novel design of a precooled supersonic ejector. The ejector adopts a dual-nozzle structure with strut and uses a precooler to precool the secondary flows with temperatures exceeding 1 100 K. Through a combined approach of experimental and numerical methods， the starting characteristics， operating characteristics， and the influence of precooling secondary flows on the performance of the precooled supersonic ejector are analyzed. The research findings indicate that when the total pressure of the primary flow exceeds 3.0 MPa， the precooled supersonic ejector can start completely， with the suction chamber pressure becoming stabilized at 3.46 kPa. However， in the critical starting state， the ejector flow channels do not achieve full supersonic flow， and shock trains affect the suction chamber. In the fully started state， the two jets collide after accelerating out of the nozzles， leading to an initial rise followed by a decrease in static pressure near the nozzle exit. Conversely， when the ejector is in the operating mode， there is an initial decrease followed by an increase in static pressure near the nozzle exit. Additionally， regardless of starting or operating conditions， shockwave intersections and reflections exist in the ejector flow channels， forming diamond-shaped regions. These regions gradually disappear with an increase in the secondary flow rate and temperature of the regions. Under the condition of low entrainment ratio， precooling secondary flows effectively enhance the mixing efficiency of the primary and secondary flows， but this advantage diminishes at high ejector coefficients. Furthermore， precooled passive flows can effectively increase the compression ratio of the ejector， with the enhancement exceeding 33.3%.

Key words: supersonic ejector, precooler, starting characteristics, operating characteristics, shock wave

CLC Number:

V434⁺.3

Tao LIANG, Wanwu XU, Zhiyan LI, Saiqiang ZHANG, Gang LI, Dongdong ZHANG. Starting and operating characteristics of precooled supersonic ejector[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130701.

Figures/Tables 32

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工况	主动流			被动流
工况	流量/（kg·s^-1）	总压/MPa	总温/K	介质	流量/（kg·s^-1）	总温/K
Case A	8.711	4.889	286.56	空气	0.52	303
Case B	9.631	4.960	273.20	预冷燃气	0.213	467.3

工况	主动流			被动流
工况	流量/（kg·s^-1）	总压/MPa	总温/K	介质	流量/（kg·s^-1）	总温/K	是否预冷	引射系数（ER）
Case 1	2.339	1.34	292.75					0
Case 2	3.607	2.08	289.0					0
Case 3	5.108	2.99	286.0					0
Case 4	5.847	3.27	285.30					0
Case 5	6.372	3.61	284.40					0
Case 6	7.651	4.34	283.20					0
Case 7	9.631	4.96	273.20	空气	0.194	279.7		0.020
Case 8	9.631	4.96	273.20	燃气	0.213	467.3	是	0.022
Case 9	9.631	4.96	273.20	燃气	0.213	1 132.0	否	0.022
Case 10	9.172	4.75	273.70	空气	0.277	295.3		0.030
Case 11	9.172	4.75	273.70	燃气	0.309	592.8	是	0.034
Case 12	9.172	4.75	273.70	燃气	0.309	1 378.0	否	0.034
Case 13	8.925	4.87	282.60	空气	0.385	295.8		0.043
Case 14	8.925	4.87	282.60	燃气	0.420	576.0	是	0.047
Case 15	8.925	4.87	282.60	燃气	0.420	1 210.0	否	0.047
Case 16	8.672	4.82	281.04	空气	0.51	297.7		0.059
Case 17	8.672	4.82	281.04	燃气	0.561	664.0	是	0.065
Case 18	8.672	4.82	281.04	燃气	0.561	1 245.0	否	0.065

工况	热流体			冷流体
工况	流量/（kg·s^-1）	入口压力/kPa	入口温度/K	流量/（kg·s^-1）	入口压力/MPa	入口温度/K	出口温度/K
Case 8	0.213	17.208	1 132.0	0.989	0.105	286.0	327.81
Case 11	0.309	21.063	1 378.0	1.157	0.209	286.28	351.33
Case 14	0.420	23.082	1 210.0	1.615	0.122	286.89	335.96
Case 17	0.561	26.830	1 245.0	2.100	0.144	287.0	334.06

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Starting and operating characteristics of precooled supersonic ejector

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