高负荷跨音速模型涡轮的设计与试验研究

 采用大转角的跨音设计是提高涡轮级负荷的有效途径之一。将原控制环量设计的模型涡轮改设计成跨音级,进行了研究。气动设计采用了作功量沿叶高为抛物线型的分布规律。叶片造型采用了短弦长、低稠度设计,叶背型线曲率为“倒曲率”分布。平面叶栅试验表明其性能良好。级试验表明其性能良好,变工况特性变化平缓。沿叶高测量表明,气流参数与设计值基本吻合。本研究摸索了跨音设计的技术途径,并取得了良好的效果。

DESIGN AND EXPERIMENTAL INVESTIGATION OF A HIGH-LOADED TRANSONIC AXIAL MODEL TURBINE

Advanced aircraft engines require designing a transonic turbine stage with large deflection blades. In order to enhance its design aerodynamic load level and to research its design procedure, an existing single turbine stage which was designed as a test model for controlled vortex project has been reconstructed to be a transonic stage with loading coefficient of 2. 4. Aerodynamic design of the stage is characterized by improved parabolic spanwise distribution of work and exit blade angle. The transonic blade profile is a compromise of aerodynamic performance, strength, weight and cooling requirements according to an advanced low solidity design. Two-dimensional cascade testing verifies its favourable performance. Stage testing indicates that the stage efficiency reaches such a level as a turbine of the modernest K. O. Loss system achieves in similar conditions. Measurements of aerodynamic characteristics along the blade height have been shown in good agreement with design parameters.