Solar Turbines Inc.

Jeremiah Wesley Key

Paul F Norton

Olivier Jacques Louis Lamicq

Fernando Manuel Ibarra Esparragoza

A compressor blade for a gas turbine engine includes a root configured to engage a hub of the gas turbine engine, and an airfoil radially extending a distance from the root to a tip. The airfoil includes a suction side, a pressure side, a leading edge connecting the suction and pressure sides, and a trailing edge connecting the suction and pressure sides opposite the leading edge. The distance that the airfoil extends from the root to the tip may be divided into a plurality of radially adjacent regions. At least one, but not all, of the plurality of radially adjacent regions may have a substantially constant thickness.

Compressor blade for gas turbine engine

A rotor blade for a gas turbine engine has an airfoil, a base integrally joined to the airfoil, and a root integrally joined to the base and mountable in a slot in a rotor hub of the gas turbine engine. The root has a dovetail including at least one contact face that, when mounted, contacts a surface of the slot to retain the rotor blade in the hub. The root includes a neck between the base and the dovetail, and a groove in the neck for redirecting stress in the rotor blade. In certain embodiments, the groove is at a distance from the at least one contact face, has a length less than a length of the dovetail, and/or has an initial non-zero depth at the side of a trailing edge of the airfoil and tapers to a zero depth in the direction of the leading edge of the airfoil.

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San Marcos, CA, United States of America

Jeremiah Wesley Key