Abstract: An improvement for a turbomachinery blade having an airfoil portion, a neck portion, and a root portion, the neck portion extending from the root portion, and the airfoil portion extending from the neck portion, and the root portion being tear-drop shaped, includes a jacket attached to the root portion and extending along a portion of the neck portion. Additionally, a process of forming a turbomachinery blade includes steps of providing a laminate of a material; providing a blade insert; wrapping the laminate around to insert to form a blade having a root portion, a neck portion extending from the root portion, and an airfoil portion extending from the neck portion; and providing for a jacket secured around the root portion and a portion of the neck portion extending from the root portion, the jacket having such shape as to prevent delamination of the laminates at a critical point due to centrifugal force acting on the blade.

Abstract: A gas turbine engine having a bypass flow in which the bypass flow includes a central bypass passage formed by a rotary shaft of the engine, and an outer bypass passage located between the casing and the combustor, where the hot gas stream from the turbine is located between the outer bypass flow and the central bypass flow. Also, a gas turbine engine having a central bypass passage with a single spool or twin spools, in which various ways are arranged to support the rotary members of the engine.

Abstract: An improvement for a turbomachinery blade having an airfoil portion, a neck portion, and a root portion, the neck portion extending from the root portion, and the airfoil portion extending from the neck portion, and the root portion being tear-drop shaped, includes a jacket attached to the root portion and extending along a portion of the neck portion. Additionally, a process of forming a turbomachinery blade includes steps of providing a laminate of a material; providing a blade insert; wrapping the laminate around to insert to form a blade having a root portion, a neck portion extending from the root portion, and an airfoil portion extending from the neck portion; and providing for a jacket secured around the root portion and a portion of the neck portion extending from the root portion, the jacket having such shape as to prevent delamination of the laminates at a critical point due to centrifugal force acting on the blade.