Alstom Technology Limited

William David Day

Edward Len Miller

Alex Torkaman

Kevin Damian Carpenter

Jeffrey S Taylor

Hitesh Narendra Patel

A system and method for securing a blade within a disk so as to eliminate the need for permanently deforming materials associated with the blade disk is disclosed. A recess is formed generally within each slot used to secure a blade within the disk. A retaining insert is positioned within the recess and a wedge insert is positioned within a slot of the retaining insert, such that a pressure is applied to the retaining insert thereby deflecting the retaining insert into a pre-set radial position to prevent axial movement of the blade within the slot of the disk.

System and method for blade retention

A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.

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Jupiter, FL, United States of America

William David Day