基于压力场分布的大子午扩张涡轮非轴对称端壁造型方法

黄镜玮; 孟福生; 宋义康

doi:10.13224/j.cnki.jasp.2020.05.017

基于压力场分布的大子午扩张涡轮非轴对称端壁造型方法

doi: 10.13224/j.cnki.jasp.2020.05.017

基金项目: 国家自然科学基金(51779051,51979052); 航空动力基金(6141B09050392)

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出版历程
- 收稿日期: 2019-11-06
- 刊出日期: 2020-05-28

Non-axisymmetric endwall modeling for large meridional expansion turbines based on pressure field distribution

College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China

摘要

摘要: 为提高大子午扩张涡轮端区气动及传热性能，基于大子午扩张涡轮上端壁静压场分布细节，使用Bezier曲线与正弦三角函数曲线相结合的非轴对称端壁造型技术，对某1.5级大子午扩张涡轮第2级静叶上端壁进行8种非对称造型设计，并通过SST（shear stress transfer）湍流模型数值求解RANS（Reynolds-averaged Navier-Stokes equations）方程组对造型前后端壁进行了流动与传热特性的研究。结果表明：对大子午扩张涡轮上端壁进行非轴对称造型设计可有效改善其上端区叶片通道内横向压差分布情况；对其上端壁压力面进行通道内凸起造型可降低出口总压损失，当凸起幅值为S2叶高的5%时，出口总压损失最多可降低约1.1%；对其上端壁吸、压力面均进行通道内凹陷造型将减小机匣与叶片的热负荷，当凹陷幅值为S2叶高的5%时，机匣及叶片的热负荷最多可分别降低约3.1%与2.8%。
- 1.5级大子午扩张涡轮 /
- 非轴对称端壁 /
- 造型方法 /
- 端区流动 /
- 传热特性
Abstract: To improve large meridional expansion turbine side area of pneumatic and heat transfer performance, based on the large meridional expansion turbine upper wall static pressure distribution in detail, non-axisymmetric endwall modelling technology was employed for eight kinds of asymmetric design for a 1.5 magnitude large meridional expansion level 2 of a turbine upper wall, by combining the Bezier curve with a sine curve of trigonometric function; and the SST（shear stress transfer） turbulence model was used to solve the RANS（Reynolds-averaged Navier-Stokes equations） equations of end wall before and after the modelling of the flow and heat transfer characteristics research. Results showed that the non-axisymmetric design of the upper endwall of a large meridional expansion turbine can effectively improve the distribution of transverse pressure difference in the blade passage at the upper end of the turbine. The total pressure loss at the outlet can be reduced by bulking the upper endwall pressure surface in the channel. When the bulking amplitude is 5% of the S2 blade height, the total pressure loss at the outlet can be reduced by 1.1% at most. The heat load of the casing and blade can be reduced by hollow modeling on the suction and pressure surfaces of the upper end wall. When the sag amplitude is 5% of the blade height of S2, the thermal load of the casing and blade can be reduced by about 3.1% and 2.8% respectively at most.
- 1.5 stage large meridional expansion turbine /
- non-axisymmetric endwall /
- modelling methods /
- end zone flow /
- heat transfer characteristics

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