| 李 骁,贾超,江通通,吴祯龙.直二元喷管变形对涡扇发动机性能影响的计算及试验验证[J].航空发动机,2026,52(1):96-102 |
| 直二元喷管变形对涡扇发动机性能影响的计算及试验验证 |
| Calculation and Experimental Verification of the Influence of Straight 2-D Nozzle Deformation on the Performance of Turbofan Engine |
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| DOI：10.12482/ISSN.1672-3147.20240702002 |
| 中文关键词: 直二元喷管 变形规律 小偏差分析 性能匹配 涡扇发动机 |
| 英文关键词:straight 2-D nozzle deformation law small deviation analysis performance matching turbofan engine |
| 基金项目:国防工业重点研究项目资助 |
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| 中文摘要: |
| 为了研究出口截面为超椭圆的直二元喷管的变形规律以及工程研制中小涵道比涡扇发动机主机与超椭圆直二元喷管
的总体性能设计匹配要点，开展了二元喷管变形对发动机性能影响计算。通过直二元喷管变形仿真分析、台架试车测量发动机全
转速范围内二元喷管出口变形量，验证仿真计算得出的超椭圆直二元喷管在使用包线内的变形特性规律的正确性，使用与直二元
喷管强相关的发动机涡轮后温度及环境压力拟合得出喷管出口变形规律，根据该变形规律开展小偏差的稳态性能仿真迭代，修正
了稳态性能模型，并进行全包线和地面台架试验验证。结果表明：最大状态高空校准推力计算值比试验值偏低0.9%，巡航高度最
大状态推力计算值比试验值最大偏低3.72%，巡航状态耗油率计算值比试验值最大偏低1.6%，模型计算值与试验结果吻合程度较
好，性能优化后的发动机性能一致性较好，均能满足设计要求，研究结果可为后续异型喷管构型的发动机整机性能匹配设计提供
参考。 |
| 英文摘要: |
| To investigate the deformation law of the straight 2-D nozzle with a superelliptic exit cross-section and the key aspects of
overall performance design matching between a low-bypass turbofan engine and such nozzle in engineering development, a computational
study on the influence of nozzle deformation on engine performance was conducted. Through deformation simulation analysis of the straight
2-D nozzle and measurement of its exit deformation across the full engine speed range during rig testing, the correctness of the deformation
characteristic law of the superelliptic straight 2-D nozzle within the operational envelope derived from simulation was validated. The
deformation law of the nozzle exit was obtained by fitting the turbine exit temperature and ambient pressure which were strongly correlated
with the straight 2-D nozzle. Based on this deformation law, steady-state performance simulation with small deviations was carried out, the
steady-state performance model was corrected, and full envelope and ground rig tests were conducted for verification. The results show that
the calculated maximum state high-altitude calibrated thrust is 0.9% lower than the experimental value, the calculated maximum state
thrust at cruising altitude is 3.72% lower than the experimental value, and the calculated fuel consumption rate at cruising state is 1.6%
lower than the experimental value. The computational model exhibits good agreement with the experimental results, and the optimized
engine demonstrates satisfactory performance consistency, meeting all design requirements. The findings of this study can provide a refer?
ence for the performance matching design of the engine with non axisymmetric nozzles in subsequent research. |
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