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文章选择小叶片50%叶高处的弦长不变,分别将其前缘前掠、后掠25°,连同原型共三个方案进行加密网格的高精度全粘定常数值模拟,并将对三个方案的设计工况的转子性能以及内部流动进行比较,试图找到小叶片掠形设计对压气机的影响规律。通过分析发现,对于文章选取的一类风扇转子来讲小叶片前缘掠形设计可以比常规方案效率提高0.3%,不良的掠形也可能比常规设计效率降低0.6%,使用掠形设计后,总压比将略有提高,通流能力基本不变,不利的掠形还会降低通流能力达4%。对于设计工况,小叶片前缘掠形在转子流道顶部主要是通过影响激波结构来改善流动,通过控制激波的位置以及强度可以降低流道中激波损失这一主要损失来源;而在流道底部,小叶片主要靠前缘膨胀波束建立壁面良好的压力曲线,来抑制大叶片附面层的发展,重点降低叶型损失,同时可以增加小叶片的负荷分配,这样既增加了小叶片以及整个转子的加功量,又可以改善流道中的横向压力梯度。
In this paper, the chord length of 50% of the leaflet height at the leaf height is selected, and the leading edge of the leaflet is swept forward and swept by 25 ° respectively. A total of three schemes are combined with the prototyping to simulate the high-precision full- The three schemes are compared with the rotor performance and internal flow in the design condition to try to find out the influence rules of small blade swept design on the compressor. The analysis shows that for a fan rotor selected in this paper, the leading edge swept design of the small blade can be increased by 0.3% compared with the conventional scheme, and the poor swept shape may also be 0.6% less than the conventional design efficiency. After swept design, The total pressure ratio will be slightly increased, the basic flow capacity unchanged, adverse swept will also reduce the flow capacity of 4%. For the design conditions, the swept-out of the leading edge of the small vane at the top of the rotor flow channel mainly improves the flow through influencing the shock structure. By controlling the position and intensity of the shock wave, the main source of the loss of shock in the flow channel can be reduced. At the bottom of the flow channel, the small vane mainly builds a good pressure curve on the wall by expanding the beam on the leading edge to restrain the development of the large vane laminating layer, with emphasis on reducing the leaf type loss and at the same time increasing the load distribution of the small vane so as to increase the small vane As well as the entire rotor plus the amount of work, but also can improve the flow path of the lateral pressure gradient.