| 摘要 |
PROBLEM TO BE SOLVED: To provide a high efficiency aerodynamic rotor for the first stage of a low-pressure gas turbine. SOLUTION: The rotor for the first stage 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 54.9°to 57.9°. COPYRIGHT: (C)2006,JPO&NCIPI
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