United Technologies Corporation

Raytheon Technologies Corporation

Thomas H Rogers

Edward J Gallagher

Eric W Malmborg

James R Murdock

Randall Joyner

Michael A Morden

Andrew J Brinks

Randall W Joyner

A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, forming a plurality of internal channels in a main body between one or more internal ribs, and forming a weld pattern in an external surface of a cover skin. The weld pattern is based on at least a geometry of the one or more internal ribs. The method includes positioning the cover skin along the main body to enclose the plurality of internal channels, and welding the cover skin to the main body along the weld pattern subsequent to the positioning step.

Method of forming gas turbine engine components

A method of inspecting components between a pre-coated state and a post-coated state is provided. The method entails providing at least first and second datum points onto the component in the pre-coated state, where each of the at least first and second datum points have a substantially hemi-spherical shape and a center point. The center points of each of the at least first and second datum points are utilized for measurement of a selected portion on the component in the pre-coated state. Then, the component is coated. Next, the center points of each of the at least first and second datum points are utilized for measurement of the selected portion on the component in the post-coated state. The pre-coated state measurements and the post-coated state measurements are then correlated for inspection purposes.

Datum transfer apparatus and method for inspecting coated components

A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be driven at a at a design speed by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool. Rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extend from the hub. Each of the propulsor blades includes an airfoil body. The leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial span.

Subsonic swept fan blade

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East Hampton, CT, United States of America

Thomas H Rogers