Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Andrew Pope

Gregory E Reinhardt

John C DiTomasso

Carl Brian Klinetob

Arun K Theertham

David R Lyders

Thomas B Hyatt

Peter V Tomeo

Thomas D Kasprow

Myron Klein

William Richard Ganoe

Jason Leroux

John P Lucashu

Douglas J Morgan

Steven L Conner

Daniel A Rodrigues

Christopher Avery

Stephen J Lindahl

David J Yudichak

Myron L Klein

Jr William Richard Ganoe

A multi-material vane is provided for a gas turbine engine. This vane includes an airfoil extending along a chamber line between a leading edge and a trailing edge. The airfoil extends along a span line between an inner end and an outer end. The airfoil extends laterally between a first side and a second side. The airfoil includes a base section, a first side section and a second side section. The base section defines at least a portion of the trailing edge of the airfoil. The base section is laterally between and connected to the first side section and the second side section. The first side section defines at least a portion of the first side of the airfoil. The second side section defines at least a portion of the second side of the airfoil.

Multi-material vane for a gas turbine engine

A multi-material vane includes an airfoil extending longitudinally between a leading edge and a trailing edge. The airfoil extends spanwise between an inner end and an outer end. The airfoil extends laterally between a first side and a second side. The airfoil includes a base section, a first side section, a second side section and a sheath. The base section extends along the span line between the inner end and the outer end. The base section is laterally between the first side section and the second side section. The first side section is connected to the base section and partially forms the first side of the airfoil. The second side section is connected to the base section and partially forms the second side of the airfoil. The sheath at least partially forming an edge of the airfoil. The edge is the leading edge or the trailing edge of the airfoil.

An inspection feature for an adhesive bond portion between parts of a component comprising the inspection feature extending from a surface of the part of the component a predetermined bond line thickness, the inspection feature having a density configured to imitate a defect of the adhesive bond portion responsive to a non-destructive inspection scan.

Comolded non-destructive inspection standard functioning as a bond bump

A structural guide vane including a vane body contact surface and a vane edge, wherein at least one of the vane body contact surface or the vane edge comprises a fiber metal laminate.

Structural guide vane

The present disclosure provides methods and systems for an airfoil of a gas turbine engine. An airfoil of a gas turbine engine may comprise an airfoil body having a body contact surface, and an airfoil edge coupled to the body contact surface, wherein at least one of the airfoil body or airfoil edge comprises a fiber metal laminate.

Airfoil

A fan blade assembly for a gas turbine engine is provided. The fan blade assembly having: a non-linear composite airfoil; and a metal root removably attached to the non-linear composite airfoil.

Multi-piece non-linear airfoil

A guide vane includes an airfoil with a first end and a second end. A platform is disposed at a first end of the airfoil, and a K-gusset is disposed on the platform opposite the airfoil. The K-gusset includes four bosses and ribs extending between the bosses in a 'K' configuration.

Structural guide vane outer diameter K gussets

A stationary guide vane includes a top platform, a bottom platform, and a vane body located between the top platform and the bottom platform. The vane body includes one or more cavities formed on a side wall of the vane body. One or more of the cavities are filled with vibration damping material and a vane cover is bonded to the vane body over the one or more containers.

Vibration damping for structural guide vanes

A vane having a cambered airfoil body is frequency-tuned via a number of cavities formed in a surface of the vane. At least some of the cavities are filled with a nonmetallic filler material, and the remainder of the cavities are left unfilled. A cover is affixed to the vane so as to cover at least the unfilled cavities. In an embodiment, the filling and covering of cavities is performed in a manner that excludes the frequency modes of the guide vane from a precluded band, e.g., an engine excitation band.

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Glendale, NY, United States of America

Andrew Pope