Abstract: A clamping assembly includes a shaft, a first plurality of clamps, and a second plurality of clamps. Each of the first and the second pluralities of clamps includes a first wall, a second wall extending outwardly from the first wall in a first direction, and a third wall extending outwardly from the first wall in a second direction. Each of the first plurality of clamps is longitudinally spaced apart by one of the second plurality of clamps. The second walls of the first plurality of clamps are transversely spaced apart from the second walls of the second plurality of clamps. The first and the second walls of the first and the second pluralities of clamps collectively define a first slot that receives the shaft. The first and the third walls of the first and the second pluralities of clamps collectively define a second slot for receiving adjacent components.

Abstract: A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.

Abstract: A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.

Abstract: A clamping assembly includes a shaft, a first plurality of clamps, and a second plurality of clamps. Each of the first and the second pluralities of clamps includes a first wall, a second wall extending outwardly from the first wall in a first direction, and a third wall extending outwardly from the first wall in a second direction. Each of the first plurality of clamps is longitudinally spaced apart by one of the second plurality of clamps. The second walls of the first plurality of clamps are transversely spaced apart from the second walls of the second plurality of clamps. The first and the second walls of the first and the second pluralities of clamps collectively define a first slot that receives the shaft. The first and the third walls of the first and the second pluralities of clamps collectively define a second slot for receiving adjacent components.

Abstract: An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.

Abstract: Composite containment casings including a body having an interior and a fragment catcher integrally joined to the interior of the body of the containment casing.

Abstract: Methods for repairing composite containment casings involving providing a composite containment casing having an integrated abradable system, the abradable system having at least one damaged portion, and including a sandwich structure, and at least one abradable layer, removing the damaged portion of the abradable system to leave a hole, shaping a sandwich structure segment to produce a shaped sandwich structure, placing the shaped sandwich structure into the hole in the abradable system, infusing a resin into the shaped sandwich structure, and curing the containment casing having the shaped sandwich structure, and applying at least one abradable layer to the shaped sandwich structure to produce the containment casing having a repaired integrated abradable system.

Abstract: Composite containment casing including a body having an interior, an abradable system integrally joined to the interior of the body of the containment casing wherein the abradable system comprises, a sandwich structure including a first facesheet and a second facesheet position about at least one core layer, and at least one abradable layer applied to the sandwich structure wherein the at least one core layer comprises any of a cell configuration, a columnar configuration, or a truss configuration and wherein the sandwich structure is strong radially and weak circumferentially.

Abstract: Method for making a composite containment casing having an integrated abradable system involving providing a mandrel having a pocket, positioning a sandwich structure into the pocket, applying at least one ply of a material about the mandrel having the pocket containing the sandwich structure therein to produce a containment casing preform, infusing a resin into the containment casing preform, curing the containment casing preform to produce a containment casing, and applying at least one abradable layer to the sandwich structure of the containment casing to produce the containment casing having the integrated abradable system.

Abstract: Methods of making an article having at least one toughened region and at least one untoughened region involving providing a material, applying a toughening agent to a portion of the material, shaping the material to produce a preform, applying an untoughened resin to the preform, and curing the preform having the applied untoughened resin to produce the at least one toughened region and the at least one untoughened region wherein the toughened region comprises a toughened resin having a fracture toughness of at least about 1.0 MPa-m1/2.

Abstract: Methods for making components having improved erosion resistance including providing a component having a surface, applying at least one layer of an erosion system to at least a portion of the surface of the component, each layer of the erosion system containing a support, and a toughened resin applied to the support, and co-molding the component having the applied erosion system to produce a coated component having from about a 50% increase to about a 400% increase in erosion resistance per layer of the erosion system.

Abstract: An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.

Abstract: Articles having a body including a composite material having at least one toughened region and at least one untoughened region, the toughened region containing a toughening agent selected from the group consisting of polymers, nano fibers, nano particles, and combinations thereof where the toughened region includes a toughened resin having a fracture toughness of at least about 1.0 MPa-m1/2.

Abstract: Methods allowing for visual inspection of a coated component for erosion damage involving providing a component, and applying a plurality of layers of an erosion system to at least a portion of the component to produce the coated component where each layer of the erosion system comprises a different color that becomes visible as the layer is eroded.

Abstract: An erosion system including a toughened resin for improving erosion resistance, the toughened resin including a resin and a toughening agent, and a support for retaining the toughened resin where at least one layer of the erosion system is applied to a component to provide from about a 50% increase to about a 400% increase in erosion resistance to the component per layer of the erosion system.

Abstract: Methods of making an article having at least one toughened region and at least one untoughened region involving providing a material, applying a toughening agent to a portion of the material, shaping the material to produce a preform, applying an untoughened resin to the preform, and curing the preform having the applied untoughened resin to produce the at least one toughened region and the at least one untoughened region wherein the toughened region comprises a toughened resin having a fracture toughness of at least about 1.0 MPa-m1/2.

Abstract: Articles having a body including a composite material having at least one toughened region and at least one untoughened region, the toughened region containing a toughening agent selected from the group consisting of polymers, nano fibers, nano particles, and combinations thereof where the toughened region includes a toughened resin having a fracture toughness of at least about 1.0 MPa-m1/2.

Abstract: A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of variable fan guide vanes which are variable fan outlet guide vanes downstream of the forward fan rotor blades. An exemplary embodiment of the engine includes an afterburner downstream of the fan bypass duct between the core engine and an exhaust nozzle. The variable fan outlet guide vanes are operable to pivot from a nominal OGV position at take-off to an open OGV position at a high flight Mach Number which may be in a range of between about 2.5-4+. Struts extend radially across a radially inwardly curved portion of a flowpath of the engine between the forward fan section and the core engine.

Abstract: An erosion system including a toughened resin for improving erosion resistance, the toughened resin including a resin and a toughening agent, and a support for retaining the toughened resin where at least one layer of the erosion system is applied to a component to provide from about a 50% increase to about a 400% increase in erosion resistance to the component per layer of the erosion system.

Abstract: Methods for making components having improved erosion resistance including providing a component having a surface, applying at least one layer of an erosion system to at least a portion of the surface of the component, each layer of the erosion system containing a support, and a toughened resin applied to the support, and co-molding the component having the applied erosion system to produce a coated component having from about a 50% increase to about a 400% increase in erosion resistance per layer of the erosion system.