Rtx Corporation

Peter Hansen Wilkins

Alex J Schneider

Paul M Lutjen

Howard J Liles

James T Roach

Jonas S Banhos

Russell Kim

Winston Smiddy

An endwall assembly for an airfoil of a gas turbine engine includes a first fiber layer, a second fiber layer forming a gas path surface, and a contoured insert disposed between the first and second fiber layers, wherein the second fiber layer conforms to a contoured surface of the contoured insert such that the contoured surface defines a geometry of the gas path surface.

Insertion of ceramic members for gas path endwall contouring

The disclosure describes methods and devices for directing/controlling cooling air flow for cooling CMC components. A cover plate is positioned within a cooling cavity in the CMC component wherein the cover plate is angled to vary the depth of the cooling cavity between the cover plate and a bottom wall of the cavity. The angled cooling plate can be used to vary the flux of cooling air within the cooling cavity and thereby achieve a desired cooling performance within the cooling cavity.

CMC component with cover plate

An airfoil includes a platform and an airfoil section that are formed of a ceramic matrix composite that includes core fiber plies, skin fiber plies, platform fiber plies, and a cooling passage that extends through selected ones of the plies to provide a cooling circuit through the airfoil section and into the platform.

CMC airfoil with cooling passage formed in fiber plies

Growing community of inventors

Manchester, CT, United States of America

Peter Hansen Wilkins