United Technologies Corporation

Rtx Corporation

Kar D Chin

Edward F Pietraszkiewicz

Om Parkash Sharma

Richard N Allen

Jason D Himes

Bryan D Roseberry

James J Gander

Wilfred J De Jesus Vargas

Carlos Rendon Roman

Ryan P Humelsine

Amy M Sunnarborg

Argenis Roberto Cruz Mercado

Victor A Lammoglia Hoyos

Rachel Irujo

Sebastian Ruiz Espinel

An air seal is provided which extends axially between a first side and a second side. The air seal includes an axial flange, a radial flange, a seal element, a retainer neck and a retainer head. The axial flange extends axially to the second side. The radial flange is connected to the axial flange at the second side. The radial flange projects radially outward from the axial flange to a distal end. The seal element projects radially outward from the distal end of the radial flange. The retainer neck is connected to the radial flange at the distal end of the radial flange. The retainer neck projects axially out from the radial flange towards the first side and then projects radially outward to the retainer head. The retainer head projects axially towards the first side and away from the retainer neck to an axial end of the retainer head.

Air seal for a turbine engine

A turbine blade is cooled by cooling air that flows through a radial cooling channel. The turbine blade includes a root and an airfoil. The flow of cooling air into the cooling channel is limited by a pre-meter orifice to provide a reduced pressure within the cooling channel. The pressure drop results from the cross-sectional area of the pre-meter orifice being less than the cross-sectional area of the adjacent cooling channel. After flowing through the cooling channel, the cooling air exits the cooling channel through a film hole to form a film layer over the airfoil to cool and insulate the turbine blade.

Turbine blade with radial cooling channels

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Simsbury, CT, United States of America

Kar D Chin