Rtx Corporation

Raytheon Technologies Corporation

Carlos Calixtro

Yanhu Guo

Emma J Place

Alex D Wong

Jeffrey Michael Jacques

John E Paul

Mohamed Hassan

Charles Thistle

Vladimir Skidelsky

Matthew B DeGostin

Stephen D Doll

Nelson D Gonzalez

An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.

Internally cooled turbine blade

A turbine blade for use in a gas turbine engine includes localized thickening of a neck pocket of the turbine blade to meet strength requirements while minimizing the weight of the turbine blade. More specifically, a convex spline is positioned within a suction side neck pocket of the turbine blade adjacent a leading edge of the neck pocket to increase the strength of the blade.

Turbine blade neck pocket

A turbine blade for a gas turbine engine includes a plurality of cooling holes positioned adjacent a tip of the turbine blade. The plurality of cooling holes are oriented at specific angles to produce film-cooling of the turbine blade tip to improve durability and performance of the turbine blade. Further, the plurality of cooling holes are positioned at specific locations to improve film-cooling of the turbine blade while reducing negative impacts on performance of the turbine blade.

Turbine blade tip cooling hole arrangement

A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.

Angled tip rods

A damper seal for a turbine blade of a gas turbine engine, the damper seal having: an upper portion; a first downwardly curved portion; and a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is curved along the entire width as it extends along the length.

Growing community of inventors

Atlanta, GA, United States of America

Carlos Calixtro