An abradable seal comprises an organic matrix composite comprising an additive and an organic component, the additive is configured to prevent adhesion of the organic component onto an abrasive blade tip.

A rotor assembly for a gas turbine engine is disclosed. The assembly includes: a composite fan blade, the fan blade including a root; a metallic rotor including a slot for receiving the root; the root being at least partially coated with a metal to form a metal-coated portion; the metal-coated portion of the root being at least partially covered with an intermediate material; and the root, metal-coated portion and intermediate material being received in the slot and bonded to the rotor.

There is disclosed a fan track liner assembly 53 for a containment arrangement 50 of a gas turbine engine, the assembly 53 comprising a cellular reactive impact structure 60, wherein cells of the reactive impact structure 60 contain a reactive material having shear-thickening or shear-stiffening properties; whereby the reactive impact structure 60 is compliant during assembly to accommodate geometrical non-compliance in the fan track liner assembly.

Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines. The method includes providing the first and second structures and plating or otherwise coating a portion of the first structure with a metal to provide a metal-coated portion. The method includes applying at least one intermediate material onto the metal-coated portion of the first structure. The method further includes bonding the metal-coated portion of the first structure and the intermediate material to the second structure. The bonding is carried out using a relatively low-temperature process, such as liquid phase bonding, including TLP and PTLP bonding. Brazing is also a suitable technique, depending on the materials chosen for the first and second structures.

A grounding clip for an organic matrix composite guide vane with a metallic sheath comprises the organic matrix composite guide vane includes a body having a leading edge and a trailing edge opposite the leading edge and a root end extending between the leading end edge and the trailing edge. The metallic sheath is attached proximate the leading edge and extends to the root end. A metallic attachment fitting has a receiver configured to receive the root end of the organic matrix composite guide vane for coupling the organic matrix composite guide vane to the metallic attachment fitting. The grounding clip is coupled to the sheath proximate the root end; wherein the grounding clip is electrically connected to the metallic attachment fitting and the metallic sheath.

A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.

An air seal in a gas turbine engine includes a substrate. A bond coating layer is adhered to the substrate. An abradable layer is adhered to the bond coating layer. The abradable layer comprises a metal matrix discontinuously filled with a lubricious oxide solid lubricant filler.

An airfoil for a gas turbine engine is disclosed. The airfoil may include a first portion including a first slot, a second portion including a second slot, and a biscuit disposed within the first slot and the second slot. The first portion and the second portion may be joined by the biscuit. A method for constructing an airfoil is also disclosed. The method may include making a first slot on a sheath, the first slot sized to fit a first part of a biscuit; making a second slot on a body, the second slot sized to fit a second part of the biscuit; and joining the sheath and the body together through a biscuit joint, the biscuit disposed within the first slot and the second slot.

An abradable seal comprises an organic matrix composite comprising an additive and an organic component, the additive is configured to prevent adhesion of the organic component onto an abrasive blade tip.

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique frame for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine frames. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.