Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Robert C Dolan

Daniel A Bales

Eric W Malmborg

Dmitri Novikov

Steven T Gordon

Michael A Weisse

Russell Albert Beers

Charles R Watson

Francis B Parisi

Thomas DeMichael

William R Graves

Xuedong Zhou

Kenneth A Frisk

John William Putnam

Randy P Salva

Phyllis L Kurz

Christopher Treese

Tri Nguyen

Russell A Beers

Eric W Malmberg

Bret B Bonarrigo

An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.

Hybridized airfoil for a gas turbine engine

A method of forming an airfoil includes the steps of (a) providing an airfoil body with a hollow having at least one rib extending to an outer surface, and forming the outer surface of the rib to have at least one groove connecting a hollow pocket within a boundary defined by the rib to a location outwardly of the rib, (b) placing a cover over the hollow, and (c) welding the cover to the airfoil body, and such that the rib is welded to the blade cover. An intermediate airfoil body is also disclosed.

Welding method for hollow airfoils and intermediate body

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub. The airfoil section includes an airfoil body extending between leading and trailing edges in a chordwise direction, extending between pressure and suction sides separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib bounding a respective pocket within a perimeter of the recessed region. A cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. A method of forming a gas turbine engine component is also disclosed.

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body defining a recessed region and including at least one rib dimensioned to loop about a respective pocket within a perimeter of the recessed region. At least one cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. The at least one cover skin is welded to the at least one rib along a respective weld path. The weld path defines a weld width, the at least one rib defines a rib width, and a ratio of the weld width to the rib width is equal to or greater than 3:1 for each position along the weld path. A method of forming a gas turbine engine component is also disclosed.

Airfoil with cover for gas turbine engine

A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to establish pressure and suction sides of an airfoil, positioning the airfoil between first and second dies of a deforming station, heating the airfoil body to a first predefined temperature threshold between the first and second dies, and moving the first die relative to the second die to hold the airfoil between the first and second dies subsequent to the heating step, and then deforming the airfoil between the first and second dies.

Method of forming gas turbine engine components

An airfoil surface includes a first titanium portion, a second titanium portion, an aluminum alloy braze disposed there between, and a titanium coating covering the aluminum alloy braze, at least part of the first titanium portion and at least part of the second titanium portion.

Hollow titanium airfoil with titanium coating

An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.

Power beam welded cavity-back titanium hollow fan blade

Growing community of inventors

Coventry, CT, United States of America

Robert C Dolan