SUPERSONIC TURBINE BUCKET AND AXIAL FLOW TURBINE

• Main Author: SENOO SHIGEKI
• Format: Patent
• Language: English; Japanese
• Published: 15.09.2016
• Subjects: BLASTING; ENGINE PLANTS IN GENERAL; HEATING; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

PROBLEM TO BE SOLVED: To provide a supersonic turbine bucket capable of reducing the shock wave loss that generated in a blade inflow part and so forth by increasing the blade length and the average diameter so as to increase the bucket peripheral velocity.SOLUTION: A supersonic turbine bucket combines at least one of structures: a structure in that the curvature R1 of a blade pressure surface is non-negative ranging from a front edge end to a rear edge end; a structure in that the curvature of a blade suction surface is positive on the upstream R2 and negative on the downstream R3; a structure in that the curvature of a dimensionless blade pressure surface, which is a value of the pitch between blades divided by the curvature radius, is greater than 0.0 and smaller than 0.1 ranging from the 30% position to the 60% position of the entire length; a structure in that the blade front edge part is formed of the curvature consecutive curve, and the distance between a position where is half of the blade maximum thickness and the blade front edge end 1LE is larger than the half of the blade maximum thickness; a structure in that the blade exit angle is larger than the theory discharge angle; and a structure in that the blade maximum thickness position is disposed close to the blade rear edge than the blade front edge, and the channel between blades forms an enlargement flow channel having a throat as an entrance.SELECTED DRAWING: Figure 9 【課題】翼長や平均直径を大きくすることで動翼周速が大きくなることにより動翼流入部などで生じる衝撃波損失を小さくすることが可能な超音速タービン動翼を提供する。【解決手段】翼圧力面の曲率R1が前縁端から後縁端まで非負となる構造、翼負圧面の曲率が上流側R2では正で、下流側R3では負となる構造、翼間ピッチを曲率半径で割った無次元翼圧力面曲率が、翼圧力面に沿った距離で、全長の３０％位置から６０％間で、0.0より大きく0.1より小さくなる構造、翼前縁部が曲率連続の曲線で形成されており、翼の最大厚みの2分の1となる位置と翼前縁端1LEとの距離が、翼の最大厚みの2分の1より大きくなる構造、翼出口角を理論流出角より大きくした構造、翼の最大厚み位置を、翼前縁より翼後縁に近く配置し、翼間流路がスロートを入り口とする拡大流路を形成するようにした構造の少なくとも一つを組み合わせる。【選択図】図9