Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: A nosecone assembly having an axially extending centerline is provided. The assembly includes a nosecone body and at least one access panel. The nosecone body has at least one wall that defines an interior cavity. The wall has an interior surface contiguous with the interior cavity, and at least one window aperture extending through the wall. The access panel has first and second face surfaces. The access panel is attached to the wall interior surface within an attachment region that includes first and second attachment region portions partially contiguous with one another. The first and second attachment region portions define an interior unattached region, and the interior unattached region is aligned with the window aperture.

Abstract: A nosecone assembly having an axially extending centerline is provided. The assembly includes a nosecone body and at least one access panel. The nosecone body has at least one wall that defines an interior cavity. The wall has an interior surface contiguous with the interior cavity, and at least one window aperture extending through the wall. The access panel has first and second face surfaces. The access panel is attached to the wall interior surface within an attachment region that includes first and second attachment region portions partially contiguous with one another. The first and second attachment region portions define an interior unattached region, and the interior unattached region is aligned with the window aperture.

Abstract: A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.

Abstract: A spinner for a gas turbine engine may include a substantially-flat inner surface having frustoconical geometry. A flange having semi-toroidal geometry may extend from the spinner with an inner curved surface of the flange being tangential to the inner surface. A mating portion may extend substantially tangentially from the inner curved surface of the flange and configured for fastening to a fan hub.

Abstract: A recirculation seal for use within a gas turbine engine. The recirculation seal includes a first seal base, including a first seal base axis. The recirculation seal further includes a second seal base, including a second seal base axis The recirculation seal further includes a resilient bulb member coupled to the first seal base. The resilient bulb member includes an exterior bulb wall and an interior bulb wall, wherein the interior bulb wall defines an interior space.

Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.

Abstract: A spinner for a gas turbine engine may include a substantially-flat inner surface having frustoconical geometry. A flange having semi-torroidal geometry may extend from the spinner with an inner curved surface of the flange being tangential to the inner surface. A mating portion may extend substantially tangentially from the inner curved surface of the flange and configured for fastening to a fan hub.

Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.

Abstract: A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.

Abstract: A recirculation seal for use within a gas turbine engine. The recirculation seal includes a first seal base, including a first seal base axis. The recirculation seal further includes a second seal base, including a second seal base axis The recirculation seal further includes a resilient bulb member coupled to the first seal base. The resilient bulb member includes an exterior bulb wall and an interior bulb wall, wherein the interior bulb wall defines an interior space.

Abstract: A gas turbine engine is provided having a nose cone, wherein the nose cone is symmetrically disposed about an axis. The nose cone includes a leading edge and a base. A forward section is disposed between the leading edge and the base and has a radius at any axial location defined by a first equation. A transition section is disposed between the forward section and the base and has a radius at any axial location defined by a second equation. The first equation is different than the second equation.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: An assembly for a turbine engine including a nosecone that extends along an axis between a tip end and a second end. The nosecone includes a base region and a deformation region configured integral with the base region. The base region is arranged axially between the deformation region and the second end. The deformation region is adapted to deform relative to the base region upon impact of an object, and includes a stress concentrator.