United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Bradley L Paquin

John D Riehl

Xiaomei Fang

George Alan Salisbury

Nicholas D Stilin

Sushruth G Kamath

Kevin M Bell

Connor C Perry

Jun Cao

Jacob Yochimowitz

A gas turbine engine component includes a structural component having a surface, the structural component having an organic matrix composite material; and a cured thermal barrier layer on the surface, wherein the cured thermal barrier layer is a pre-ceramic layer including inorganic matrix containing silicon oxides reinforced with glass or quartz fibers.

Pre-ceramic thermal barrier for gas turbine engine components

A composite airfoil is disclosed. The composite airfoil includes a first ply having a first plurality of strips of fiber oriented at a first angle with respect to a longitudinal axis and a second plurality of strips of fiber oriented at a second angle with respect to the longitudinal axis at least a first subset of the first plurality of strips of fibers have fibers intersecting and oriented at an angle to the fibers in at least a second subset of the second plurality of strips of fibers within a ply boundary.

Single ply having plurality of fiber angles

A fiber composite material comprises a polymer matrix, carbon fibers, and non-carbon fibers, wherein the non-carbon fibers have a strain to failure value greater than the strain to failure value of the carbon fibers. Also discussed is a preform comprising the fiber composite material combined in a three dimensionally woven structure. Also discussed is a fan blade for a jet engine.

Fiber composite material and preform and fan blade made therefrom

Growing community of inventors

Cheshire, CT, United States of America

Bradley L Paquin