异型喷口的多维偏转S弯喷管设计方法

doi:10.7527/S1000-6893.2023.28930

Abstract

Abstract:

The aerodynamic profile design of multi-dimensional deflected serpentine nozzles with high aerodynamic performance and complex configurations is one of the crucial technologies for stealth aircraft with integrated wing-body layouts. By improving the Lee curve method and multiparametric coupled method， we propose a design method for multi-dimensional deflected serpentine nozzles with an abnormal exit， and realize the multi-dimensional deflected serpentine centerline design with vector angles and the cross-sectional transition from the circular inlet to the abnormal exit. This method can be used for the aerodynamic profile design of multiple serpentine nozzles with conventional and space-confined layouts， such as multi-dimensional deflected serpentine nozzles， serpentine nozzles with vector angles， serpentine nozzles with unsymmetrical abnormal exits， and serpentine nozzles for single and twin aeroengine layouts. The proposed design method is verified by the numerical simulation method and the small turbojet engine test. The results show that the discharge and thrust coefficients of the ultra-compact serpentine nozzle designed with the space-confined layout reach 0.982 and 0.989， respectively， under the critical condition， and are no smaller than 0.984 and 0.992， respectively， under the overcritical condition. Those of the multi-dimensional deflected serpentine nozzle designed with the space-confined layout reach 0.980 and 0.986， respectively， under the critical condition and are no smaller than 0.981 and 0.990， respectively， under the overcritical condition. The total thrust of engine after installing the juxtaposition serpentine nozzles designed with the twin engine layout is no more than 4.58% lower than that with the original nozzle. The designed serpentine nozzles have better aerodynamic performance.

Key words: serpentine nozzle, unsymmetrical abnormal exit, multi-dimensional deflection, aerodynamic profile design, space-confined layout, twin engine layout

CLC Number:

V231.1

Yubo MENG, Jingwei SHI, Li ZHOU, Yi ZHANG, Zhanxue WANG. Design method for multi-dimensional deflected serpentine nozzle with abnormal exit[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 128930.

Figures/Tables 31

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References 25

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几何设计参数	数值
喷管进口直径D/m	0.807
喷管轴向长度L/m	1.614
第1弯轴向长度L₁/m	0.581
第1弯纵向偏距ΔY₁/m	-0.283
第1弯出口面积A_s1/m²	0.333
第1弯出口宽度W_s1/m	0.888
第1弯出口左底角角度β_1，s1/（°）	75
第2弯轴向长度L₂/m	0.872
第2弯纵向偏距ΔY₂/m	0.461
喷管出口面积A_ex/m²	0.238
喷管出口宽高比W_ex/H_ex	6
喷管出口左底角角度β_1，ex/（°）	40

几何设计参数	数值
喷管进口直径D/m	0.807
喷管轴向长度L/m	2.018
喷管展向偏距L/m	0.416
第1弯轴向长度L₁/m	0.710
第1弯纵向偏距ΔY₁/m	-0.242
第1弯出口面积A_s1/m²	0.333
第1弯出口宽度W_s1/m	0.888
第1弯出口左底角角度β_1，s1/（°）	75
第1弯出口右底角角度β_2，s1/（°）	85
第2弯轴向长度L₂/m	1.065
第2弯纵向偏距ΔY₂/m	0.534
喷管出口面积A_ex/m²	0.238
喷管出口宽高比W_ex/H_ex	6
喷管出口左底角角度β_1，ex/（°）	40
喷管出口右底角角度β_2，ex/（°）	60

喷管落压比	流量系数	推力系数
1.893	0.982	0.989
3	0.984	0.992
4.5	0.985	0.993

内侧喷管参数	数值	外侧喷管参数	数值
D/m	0.148	D/m	0.148
L/m	0.424	L/m	0.351
ΔY₁/m	0.069	ΔY₁/m	0.063
ΔZ/m	-0.162	ΔZ/m	-0.168
A_ex/A_in	0.507	A_ex/A_in	0.507
W_ex/H_ex	4.1	W_ex/H_ex	4.1
β_1，ex/（°）	90	β_1，ex/（°）	37
β_2，ex/（°）	30	β_2，ex/（°）	90

参数	最大量程/N	精度/%FS
x方向推力F_x	2 000	0.5
y方向推力F_y	500	0.5
z方向推力F_z	500	0.5

Design method for multi-dimensional deflected serpentine nozzle with abnormal exit

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