高负荷涡轮进口导向叶片叶型设计及验证
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Design and validation of high-lift turbine nozzle guide vane profile
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    摘要:

    针对涡轮进口导向叶片进口马赫数低、前部负荷小的特点,采用前缘截断思路构建了高负荷涡轮叶型,并采用Pritchard 11参数法进行重构设计。采用数值计算和平面叶栅试验开展了研究和分析。结果表明:高负荷叶型吸力面前缘马赫数显著提升,增加了叶片前部负荷。喉部峰值马赫数基本不变,但位置前移,负荷分布均匀性提高。叶型的马赫数特性和攻角特性表明,高负荷叶型在不同攻角和马赫数下,均能获得较低的总压损失,其中在设计马赫数,叶型负荷提升1倍的情况下,总压损失系数降低259%。

    Abstract:

    A method for high-lift turbine blade design based on Pritchard 11 parameters method was introduced for turbine nozzle guide vane working under low entrance Mach number and typically low lift at front part of the blade. A series of high lift nozzle guide vane profile were designed and investigated using numerical calculation, and validated by linear cascade test. Results showed that the blade loading of high-lift profile was more uniform due to increase of Mach number at front part of the suction side, and the throat suction moved forward. The Mach number characteristic and attack angle characteristic showed that the highly-loaded blades generated lower total pressure loss. The pressure loss coefficient of high-lift profile was 259% lower under design condition than that of the datum profile.

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张绍文,石建成,李维.高负荷涡轮进口导向叶片叶型设计及验证[J].航空动力学报,2021,36(1):185~192. ZHANG Shaowen, SHI Jiancheng, LI Wei. Design and validation of high-lift turbine nozzle guide vane profile[J]. Journal Of Aerospace Power,2021,36(1):185-192.

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  • 收稿日期:2020-08-12
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  • 在线发布日期: 2021-02-04
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