在舰船综合电力系统中，武器上舰对原有提供动力的舰船燃气轮机运行性能提出更高要求。原有的轴流压气机导/静叶调节规律需要适应电力系统快速变化的复杂工况，以扩大燃气轮机高效运行范围。为此，基于原有最佳导/静叶调节规律，细化研究各级导/静叶角度变化对于压气机性能的影响规律。本文以NASA74A型轴流压气机为研究对象，针对原有最佳导/静叶调节规律，研究不同转速下导/静叶偏离最佳角度变化（0～±15°）对压气机特性和稳定工作范围影响规律。分析表明：在60%额定转速下，当进口导叶和前两级静叶偏离最佳角度±5°时，压气机最高效率点变化不明显，最高效率总压比偏差1%以内。但+5°偏转使得压气机稳定工作范围扩大，喘振裕度有所提升；在-5°偏转时，压气机稳定工作范围缩小，喘振裕度也下降约1.3%。此外，在60%～100%额定转速范围内，导/静叶分别偏转±5°时压气机特性曲线偏离最佳角度特性逐渐增大，尤其对于80%额定以上转速的特性，由于流道内激波的出现将使得压气机最高效率降低，相比于进口导叶角度偏转，前两级静叶角度偏转对压气机特性影响更大，且转速较高时应选择较小的导/静叶偏转角度。上述研究成果对舰船综合电力系统燃气轮机运行特性的优化具有指导意义。

In ship integrated power systems, weapon installation demands higher performance from ship gas turbines. The regulation of axial compressor guide/static vanes must adapt to complex, rapidly changing conditions to broaden the turbine’s efficient operation range. Based on optimal guide/static vane regulation, this study examines the impact of angle changes on NASA74A compressor performance. At 60% rated speed, ±5° deviations in inlet guide vanes and first two static vanes barely affect peak efficiency, with total pressure ratio deviation under 1%. A +5° deflection widens the stable range and boosts surge margin, while -5° narrows it and reduces surge margin by 1.3%. From 60% to 100% rated speed, ±5° deflections increasingly deviate from optimal characteristics, especially above 80% speed where shock waves reduce peak efficiency. First two static vane angle changes impact the compressor more than inlet guide vane changes, and smaller deflections are advised at higher speeds. These findings guide the optimization of ship gas turbine operation characteristics.

国家科技重大专项（No.J2019-I-0012-0012）资助