High efficiency rotor for the first phase of a gas turbine

Details High efficiency rotor for the first phase of a gas turbine High efficiency rotor for the first phase of a gas turbine

2008-06-17

2008-06-17

Edgar, Richard (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

C416SDIG004

Reexamination Certificate

active

07387495

ABSTRACT:
A rotor for the first phase of a low-pressure turbine has a series of blades each defined by coordinates of a discreet 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 is identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. Each blade 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°.

REFERENCES:
patent: 5299909 (1994-04-01), Wulf

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