Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

Arun K Theertham

Peter Karkos

Andrew Pope

Matthew R Zsunkan

A fan blade platform assembly includes a pressure side platform half that includes a first attachment wall, a first gas path wall, and a first connecting wall attached to both the first attachment wall and the first gas path wall. A suction side platform half includes a second attachment wall, a second gas path wall, and a second connecting wall attached to both the second attachment wall and the second gas path wall. A seal engages the pressure side platform half and the suction side platform half.

Fan blade platform for gas turbine engine

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

An assembly for a gas turbine engine includes an airfoil that includes an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. A platform is dimensioned to receive a retention pin to mount the platform to a rotatable hub. The platform includes a plurality of composite layers that define an internal cavity. A filler includes a stacked composite structure in the internal cavity that extends between the plurality of composite layers.

Platform for an airfoil of 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.

Platforms for airfoils in gas turbine engines are provided. The platforms include an aero-structure defining a gaspath surface and a non-gaspath surface, a first securing element arranged to receive a locking pin and secure the aero-structure to a rotor disk, and a first securing element structure extending between the non-gaspath surface and the first securing element, wherein the first securing element structure comprises at least two legs defining a hollow space between the two legs and the non-gaspath surface.

A method of assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, positioning an array of airfoils about an outer periphery of a hub, the hub being rotatable about an engine longitudinal axis of a gas turbine engine, the hub including a plurality of flanges, and each one of the airfoils including an airfoil section extending from a root section. An array of platforms are positioned about the outer periphery of the hub, each of the platforms including one or more slots defined by a plurality of platform flanges, and including the one or more slots receiving a respective one of the flanges of the hub. A plurality of retention pins are moved relative to the array of airfoils such each one of the retention pins extends through the flanges of the hub and through the plurality of platform flanges of a respective one of the platforms to mechanically attach a respective one of the platforms and the root section of a respective one of the airfoils to the hub. At least one of the airfoils and the platforms includes a plurality of composite layers that define an internal cavity, and includes a lattice structure in the internal cavity that extends between the plurality of composite layers.

Composite gas turbine engine component with lattice

A fan platform includes a platform body that has gaspath and non-gaspath sides, leading and trailing ends, first and second circumferential sides that are contoured to follow profiles of adjacent fan blades, and lugs that project from the non-gaspath side and define fastener openings. The platform body includes a core and a fiber-reinforced polymer matrix composite skin attached on the core at least on portions of the gaspath and non-gaspath sides.

Fan platform with core and skin

A platform assembly for a fan of a gas turbine engine includes a lug, and a platform. The lug has a head, a base, and a leg that extends between the head and the base. The platform is at least partially disposed about the head. The platform has an outer surface and an inner surface. The head is arranged to engage the inner surface.

Gas turbine engine fan platform

A multi-piece fan spacer for a gas turbine engine includes at least one lug comprising a platform portion, a connection portion radially inward of the platform portion, and a support connecting the platform portion to the connection portion. The multi-piece fan spacer includes a plurality of platforms. Each of the platforms is connected to at least one axially adjacent platform portion.

Fan spacer for a gas turbine engine

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil that has an airfoil section extending from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. A platform is dimensioned to receive a retention pin to mount the platform to a rotatable hub. At least one of the airfoil and the platform includes a plurality of composite layers that define an internal cavity. A lattice structure in the internal cavity extends between the plurality of composite layers. The lattice structure has a plurality of branches that extend from a plurality of nodes.

Composite gas turbine engine component with lattice structure

Platforms for gas turbine engines are described. The platforms include a flow structure having a gaspath surface and a non-gaspath surface with a front end, a rear end, a first edge, and a second edge. A platform connector extends from the flow structure. A first layer forms a part of the gaspath surface and is a non-continuous layer terminating at the ends and the edges. A second layer forms a part of the platform connector and is a non-continuous layer terminating at the ends and the edges. The second layer contacts the first layer proximate the first and second edges. A third layer defines an internal void and is a continuous layer arranged between the first layer and the second layer and defines a part of the flow structure and a part of the platform connector.

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Rocky Hill, CT, United States of America

Arun K Theertham