Fastening of the blades of a compression machine
AssigneeALSTOM Technology Ltd
InventorsEduard Gotzfried, Helmut Wendler, Heinz May
Life of this patent
Estimating the term…
Abstract
The blades (1, 11, 12, 13, 1n) of a turbine or compressor are fastened into a groove (8) on the rotor (6) or stator of the turbine or compressor by means of the blade roots (4), there being no play or a prestress prevailing between the root plate (3) and/or the blade root (4), and adjacent blades (1, 11, 12, 13, 1n) thereby being supported relative to one another with respect to torsional moments (12) and not or only slightly on the rotor (6) or stator. This is possible, for example, by means of a bevel (9).
Claims6
A fastening of blades (11, 12, 13, 1n) of a turbomachine to a rotor (6) or stator, the blades (11, 12, 13, 1n) being fastened to the rotor (6) or stator by means of blade roots (4), and the blades (11, 12, 13, 1n) having a root plate (3), a cover plate (2) or supporting wing above the blade root (4) and a blade (5), and a torsional moment (13) acting on the cover plate (2) or on the supporting wing, characterized in that, after the installation of all the blades (11, 12, 13, 1n) , the blades (11, 12, 13, 1n) are contiguous to one another on the rotor (6) or stator at the root plate (3) and/or at the blade root (4) completely or partially without play or with a prestress and are therefore supported relative to one another with respect to torsional moments (12), the torsional moments (12) which act at the root plates (3) and/or at the blade roots (4) being opposite to the torsional moments (13) which act at the cover plate (2) or at the supporting wing.
Dependencies are inferred from the claim text.