A method of manufacturing a net shaped seal comprising depositing a first layer of powder material on a substrate; the powder material comprising an abradable feedstock material comprising matrix alloy clad filler particles, wherein the matrix alloy cladding includes Al, Cu, Ni, Co, Cr, Fe, Si and Y; guiding a heat source over the powder material layer; laser sintering the powder material, the matrix alloy clad filler particles sinter in the absence of the filler particles melting; depositing a second layer of powder material over the first layer; laser sintering the second layer of powder material with a second laser pass at predetermined locations; wherein at least one of the matrix alloy clad filler particles sinter, and in the absence of the filler particles melting; and repeating the depositing step and laser sintering step to form subsequent layers to form an abradable seal on the substrate.

A method of forming a blade or vane for a gas turbine engine comprising: attaching a first outer layer to a first two-dimensional array of attachment areas on a first surface of an intermediate layer; attaching a second outer layer to a second two-dimensional array of attachment areas on a second surface of the intermediate layer opposite the first surface; and increasing a separation between at least a portion of the first and second outer layer to thereby deform the intermediate layer into a corrugated structure having corrugations in first and second directions.

A seal is formed of a matrix and includes hard particles. The matrix has a shear strength of greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine is also disclosed.

The invention relates to a sealing material, to a gas seal made of this sealing material, and to a method for the production of such a gas seal made of this sealing material. The sealing material contains a bromobutyl elastomer in an amount of 100 parts by weight, a filler material in an amount between 10 and 100 parts by weight for setting the volume of the sealing material, a curing agent in an amount between 0.5 and 3.0 parts by weight for curing the sealing material, and a cross-linking component in an amount between 0.1 and 2.0 parts by weight for bringing about a peroxidic cross-linking of the sealing material. This sealing material permits a particularly high vacuum-tightness (that is to say, a low leakage rate) in comparison to sealing materials according to the state of the art, and accounts for resistance, on the one hand, to aggressive gases and, on the other hand, to pump oils such as, for instance, perfluoropolyethene oil or silicon oil.

A fan blade for an aircraft engine, including a leading edge, a trailing edge, a suction side, a pressure side and a blade tip, is provided. The fan blade has a large-area elastomer layer which takes up at least 20% of the surface of the suction side of the fan blade.

An article according to an exemplary embodiment of this disclosure includes a substrate and a bond coat disposed on the substrate. The bond coat includes a matrix. The matrix includes regions of ?-cristobalite. The article also includes a plurality of gettering particles disposed in the matrix, a plurality of diffusive particles disposed in the matrix, and an additive operable to stabilize the regions of ?-cristobalite at ambient temperatures dispersed in the matrix. An article and a method of coating an article are also disclosed.

A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust. The bypass duct includes a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap therebetween. A sealing strip is positioned in the gap between the first component and the second component distal to the gas washed surfaces of the first and second components. A sealant is positioned between the first and second component proximal to the gas washed surfaces of the first and second components, so as to seal the gap between the first component and the second component from airflow through the bypass duct.

An air seal for use in a gas turbine engine. The seal includes a thermally sprayed abradable seal layer. The abradable material is composed of aluminum powder forming a metal matrix, and co-deposited methyl methacrylate particles and/or hexagonal boron nitride particles embedded as filler in the metal matrix.

An airfoil for a gas turbine engine includes first pressure and suction side layers forming a cavity and terminating in ends near a trailing edge. The first and second suction side layers are constructed from a composite material. A bridge is wrapped about the ends.

An air seal for use in a gas turbine engine. The seal includes a thermally sprayed abradable seal layer. The abradable material is composed of aluminum powder forming a metal matrix, and co-deposited methyl methacrylate particles and/or hexagonal boron nitride particles embedded as filler in the metal matrix.