To provide a high efficiency aerodynamic stator for the first phase of a low-pressure gas turbine.
The stator for the first phase of the low-pressure turbine has a series of blades 1 each defined by coordinates of a discrete combination of points, in a Cartesian reference system X, Y, Z, wherein the axis Z is a radial axis intersecting the central axis of the turbine. The profile of each blade 1 is identified by means of a series of closed intersection curves 20 between the profile itself and planes X, Y lying at distances Z from the central axis. Each blade 1 has an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat angle ranges from 57° to 60°.
| JPH05149104A | 1993-06-15 | |||
| JPH04269302A | 1992-09-25 | |||
| JPH05256102A | 1993-10-05 | |||
| JPH0610604A | 1994-01-18 |
Hirokazu Ogura
Nobukazu Ito
Toshihisa Kurokawa
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