Rotor blade for a first phase of a gas turbine

Details Rotor blade for a first phase of a gas turbine Rotor blade for a first phase of a gas turbine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/14 (2006.01)

Patent

CA 2518558

Blade (1) of a rotor for a first phase of a gas turbine having a profile 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 closed curve (20) has a first rounded end (21) and a second rounded end (22), which connect the trace of the first surface (3) with the trace of the second surface (5) in depression, the first end (21) first meets a gas flow of the turbine, each closed curve (20) has an axial chord (40) defined as the maximum distance of the first end (21) from the second end (22) along the axis (X), each closed curve (20) has a thickness (30) of the first end (21) defined as the maximum diameter of the circle inscribed in the first end (21); said dimensionless thickness (30), i.e. divided by the axial chord (40), has a quadric distribution according to a curve of the fourth order along the axis (Z).

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