To provide a turbine blade having a great lifting power load during transonic operation and attaining high efficiency.
The turbine blade system is equipped with a blade air-foil having an air-foil shape. The blade air-foil has a reference contour which materially conforms to normalized Cartesian coordinates values X, Y, and Z of Table 1 (not shown). These coordinate values are dimensionless values capable of being converted into corresponding absolute distance values which define a reference air-foil contour cross-section. When correctly combined with the cross section of an opposing reference air-foil contour, the cross-section of the reference air-foil contour forms a complete reference air-foil shape which is materially equal to the air-foil shape of the blade air-foil. This blade air-foil is supported by a ring platform having a supporting surface. This supporting surface of the ring platform has a shape of a supporting surface to be formed near a place which supports the blade air foil by a method similar to the above.
GACEK RICHARD E
STAUBACH JOSEPH B
| JPH10508671A | 1998-08-25 | |||
| JP2004353676A | 2004-12-16 | |||
| JPH09193295A | 1997-07-29 |
| WO2006033407A1 | 2006-03-30 |
Tomioka Kiyoshi