IMPROVED FIRST STAGE TURBINE BLADE

• Main Authors: XIAO ZHENHUA, YU RICHARD, SMITH WESLEY, ELLIS CHARLES A, PARKER DAVID G, MEDRANO DAVID, MARTLING VINCENT C
• Format: Patent
• Language: Chinese; English
• Published: 17.08.2021
• Subjects: AEROPLANES; AIRCRAFT; AVIATION; BLASTING; COSMONAUTICS; ENGINE PLANTS IN GENERAL; HEATING; HELICOPTERS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; PERFORMING OPERATIONS; STEAM ENGINES; TRANSPORTING; WEAPONS

A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form an airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant. 涡轮叶片具有基本根据表1所示的X、Y和Z的笛卡尔坐标值的翼型轮廓，其中，X和Y值以英寸为单位，Z值为从0到1的无量纲值，通过将Z值与以英寸为单位的翼型件的高度相乘其可被转换为以英寸为单位的Z距离。X和Y值为距离，当用平滑连续的弧线连接时，其在每个距离Z限定翼型件轮廓截面。将各Z距离处的轮廓截面平滑地彼此连接形成翼型形状。X和Y值还可以根据第一常数缩放，并且，Z值可以根据第二常数缩放。