Turbomachine blade

摘要

The blade (1) for a turbo-engine is fixed in the flow passage of the engine by means of a fastening section (16) provided on its ends. The blade has at least one section of a chordal length increasing with increasing distance away from the fastening section. The profile (6) of the blade at least partially may have an increased curvature and may be at least partially curved backwards. The thickness of the blade profile can be reduced and blade mass distribution can be optimized. An independent claim is included for a steam turbine or gas turbine incorporating the aforesaid blade design.