| LI Xiao,JIA Chao,JIANG Tongtong,WU Zhenlong.Calculation and Experimental Verification of the Influence of Straight 2-D Nozzle Deformation on the Performance of Turbofan Engine[J].航空发动机,2026,52(1):96-102 |
| Calculation and Experimental Verification of the Influence of Straight 2-D Nozzle Deformation on the Performance of Turbofan Engine |
| DOI：10.12482/ISSN.1672-3147.20240702002 |
| Key Words:straight 2-D nozzle deformation law small deviation analysis performance matching turbofan engine |
| Author Name | Affiliation | | LI Xiao | College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China；
AECC Guiyang Engine Research Design Institute,Guiyang 550081,China | | JIA Chao | AECC Guiyang Engine Research Design Institute,Guiyang 550081,China | | JIANG Tongtong | AECC Guiyang Engine Research Design Institute,Guiyang 550081,China | | WU Zhenlong | College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China |
|
| Hits: 1629 |
| Download times: 461 |
| Abstract: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. |
| View Full Text View/Add Comment Download reader |
|
|
|
