Fluid-structural interaction characteristics of serpentine nozzles with different offset ratios

ZHENG Haibo; GAO Chao; HE Chengjun; HUANG Jiangtao; SHU Bowen

doi:10.7638/kqdlxxb-2024.0116

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Fluid-structural interaction characteristics of serpentine nozzles with different offset ratios

更新时间：2026-05-28

- Fluid-structural interaction characteristics of serpentine nozzles with different offset ratios
- Vol. 43, Issue 11, Pages: 66-76(2025)
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710072
  2. 飞行器基础布局全国重点实验室,西安,710072
  3. 中国空气动力研究与发展中心空天技术研究所,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0116
  CLC： TK243.3
- Published：2025
- 稿件说明：
移动端阅览
郑海波, 高超, 何成军, 等. 不同偏径比S弯喷管流固耦合特性[J]. 空气动力学学报, 2025, 43(11): 66−76.

ZHENG Haibo, GAO Chao, HE Chengjun, et al. Fluid-structural interaction characteristics of serpentine nozzles with different offset ratios[J]. 2025, 43(11): 66-76.
郑海波, 高超, 何成军, 等. 不同偏径比S弯喷管流固耦合特性[J]. 空气动力学学报, 2025, 43(11): 66−76. DOI： 10.7638/kqdlxxb-2024.0116

ZHENG Haibo, GAO Chao, HE Chengjun, et al. Fluid-structural interaction characteristics of serpentine nozzles with different offset ratios[J]. 2025, 43(11): 66-76. DOI： 10.7638/kqdlxxb-2024.0116.

摘要

S弯喷管几何构型显著不同于传统轴对称喷管，其具有壁面曲率变化大，内部气动载荷分布不均匀程度高等特点，这导致具有薄壁结构的S弯喷管容易发生流固耦合现象。为深入探究S弯喷管的流固耦合现象及其对喷管推力性能的影响规律，本文设计了出口斜切的不同偏径比（

= 0.28～0.58）双S弯喷管，并构建了双向流固耦合模型，通过超声速平板颤振算例验证了模型准确性。结果表明，不同偏径比S弯喷管结构场与流场之间相互影响剧烈，耦合后，喷管变形呈由内向外、整体向下的变形形式，变形量随偏径比增大而逐渐减小，最大变形位置始终出现在喷管出口下壁面中间位置（在偏径比

= 0.34 时

方向最大变形位移占喷管出口高度的16.7%）。在气动性能方面，喷管沿程截面面积增大，并由初始收敛型转变为收敛-扩张型，喉道面积与偏径比近似呈线性分布，随偏径比增大而逐渐减小。流固耦合作用导致喷管第二S弯段与出口等直段连接处局部高速流动区扩大且向下游移动，进而使得下游压力峰值减小甚至消失。在推力性能方面，未耦合时，随喷管偏径比

从0.28增大至0.58，喷管推力系数由0.978 减小至 0.960；耦合后，相比未耦合工况喷管推力系数增加（

= 0.34时，推力系数增幅约为 0.6%），推力矢量角减小（

= 0.52 时，推力矢量角最大减幅约为 23.6%），但是两者随偏径比变化趋势与未耦合工况下一致，均随偏径比增大而逐渐减小。

Abstract

The geometric configurations of serpentine nozzles differ significantly from conventional axisymmetric nozzles

characterized by substantial variations in the wall curvature and an S-shaped centerline. This configuration results in uneven distribution of internal aerodynamic load. Serpentine nozzles are gen

erally thin-walled structures to reduce aircraft’s weight. Consequently

the fluid-structural interaction (FSI) becomes a prominent phenomenon in serpentine nozzles

playing an important role in aircraft design. To examine the FSI phenomenon in serpentine nozzles and its impact on thrust performance

this paper introduces double serpentine nozzles with varying offset ratios. A two-way FSI framework is then established and validated. Subsequent analysis focuses on the deformation characteristics of the nozzle and their effects on the aerodynamic loads on the nozzle wall. Furthermore

the influence of FSI on thrust performance is explored. The results reveal that the FSI phenomenon is evident under different offset ratios. There are two types of nozzle deformation: inward-outward and top-down

with the deformation decreasing gradually with the increase of offset ratio. Notably

the maximum deformation consistently occurs at the middle of the lower wall of the nozzle outlet. Regarding the aerodynamic performance

the nozzle's cross-sectional area expands

transitioning from an initial convergence configuration to a convergence-expansion one. Both the throat area and offset ratio decrease approximately linearly with the increase of the offset ratio. The FSI causes the local high-speed flow region at the junction of the second inflection and the outlet to expand and move downstream

leading to a reduction or even elimination of the downstream pressure peak. In terms of thrust performance

the thrust coefficient increases (when

= 0.34

the increase is approximately 0.6%)

and the thrust vector angle decreases (when

= 0.52

the reduction in thrust vector angle is approximately 23.6%). But the variation trend of both with the offset ratio is consistent with that under uncoupled conditions

and both decrease gradually with increasing offset ratio.

关键词

Keywords

references

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