Abstract: A heat exchanger is provided for a gas turbine engine. This heat exchanger includes a pair of heat exchanger manifolds and a stack of flow channel modules arranged and fluidly coupled between the heat exchanger manifolds. The flow channel modules include a first flow channel module that includes a first heat exchanger section and a second heat exchanger section. The first heat exchanger section includes a base plate, a plurality of flow channel walls and a plurality of heat transfer augmentors. The flow channel walls project out from the base plate to the second heat exchanger section thereby forming a plurality of flow channels between the first heat exchanger section and the second heat exchanger section. The heat transfer augmentors project partially into at least one of the flow channels. A first of the heat transfer augmentors is formed from a different material than the base plate.

Abstract: An alloy composition includes, by weight: 20% to 23% of Cr; 8% to 10% of Mo; 3.15% to 4.15% of Nb+Ta; 0.25% to 1.5% of B; 0.35% to 1.75% of N; and a balance of Ni.

Abstract: An alloy composition includes, by weight: 20% to 23% of Cr; 8% to 10% of Mo; 3.15% to 4.15% of Nb+Ta; 0.25% to 1.5% of B; 0.35% to 1.75% of N; and a balance of Ni.

Abstract: A method is provided for manufacturing at least a portion of a heat exchanger. During this method, a first heat exchanger section is formed that includes a base and a plurality of protrusions. The forming of the first heat exchanger section includes building up at least one protrusion material on the base to form the protrusions. The first heat exchanger section is attached to a second heat exchanger section. A plurality of flow channels are defined between the first heat exchanger section and the second heat exchanger section.

Abstract: A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.

Abstract: A method is provided for manufacturing at least a portion of a heat exchanger. During this method, a first heat exchanger section is formed that includes a base and a plurality of protrusions. The forming of the first heat exchanger section includes building up at least one protrusion material on the base to form the protrusions. The first heat exchanger section is attached to a second heat exchanger section. A plurality of flow channels are defined between the first heat exchanger section and the second heat exchanger section.

Abstract: Aspects are directed to a tribological and creep resistant system configured to operate at temperature in excess of 750° C., comprising: a piston seal that includes a nickel base alloy, where the nickel base alloy includes a Ni3(Al,X) type precipitated phase in an amount greater than 40% by volume. Aspects are directed to a system comprising: a piston seal that includes a cobalt-based alloy. Aspects are directed to a method comprising: heat treating an ingot of a nickel base alloy that includes coarsening a precipitated phase to facilitate forging or wrought forming the ingot, machining the ingot to include a substantially flat surface, and processing the ingot to generate a piston seal.

Abstract: Aspects of the disclosure are directed to a method of repairing a non-line of sight feature on a surface, the method comprising machining a worn irregular non-line of sight surface to provide a substantially planar repair surface, depositing a nickel plate base layer having a base layer thickness on the substantially planar repair surface, and depositing a protective layer having a protective layer thickness on the nickel plate base layer.

Abstract: An airfoil may include an airfoil body, a cover, and a stud. The cover may be disposed on at least one of a suction side and a pressure side of the airfoil body and the stud may extend through the cover and into the airfoil body and the stud may be is joined to the airfoil body and the cover by a friction weld.

Abstract: Aspects are directed to removing a portion of a component that includes wear to generate a void in the component, where a material of the component has a first microstructure, depositing a filler material in the void, subjecting the filler material to a cold working technique to compress the filler material, and applying a heat treatment to cause the filler material to have a second microstructure that is matched to the first microstructure. Aspects are directed to a case of an engine, including: a first portion with a first material that has a first microstructure, and a second portion with a second material that has a second microstructure, where the second microstructure is matched to the first microstructure, where the second material includes a plurality of layers, and where at least one layer of the plurality of layers includes a compressive residual stress.

Abstract: A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.

Abstract: Aspects are directed to a tribological and creep resistant system configured to operate at temperature in excess of 750° C., comprising: a piston seal that includes a nickel base alloy, where the nickel base alloy includes a Ni3(Al,X) type precipitated phase in an amount greater than 40% by volume. Aspects are directed to a system comprising: a piston seal that includes a cobalt-based alloy. Aspects are directed to a method comprising: heat treating an ingot of a nickel base alloy that includes coarsening a precipitated phase to facilitate forging or wrought forming the ingot, machining the ingot to include a substantially flat surface, and processing the ingot to generate a piston seal.

Abstract: Attaching a fastener to a ceramic matrix composite or ceramic body by inserting a portion of the fastener into a compartment of the body, the compartment having a first portion and a second portion, the second portion outboard of and narrower than the first portion; and delivering a fluid into the fastener to expand a portion of the fastener within the blind compartment first portion.

Abstract: A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.

Abstract: A method is provided for manufacturing at least a portion of a heat exchanger. During this method, a first heat exchanger section is formed that includes a base and a plurality of protrusions. The forming of the first heat exchanger section includes building up at least one protrusion material on the base to form the protrusions. The first heat exchanger section is attached to a second heat exchanger section. A plurality of flow channels are defined between the first heat exchanger section and the second heat exchanger section.

Abstract: An airfoil may include an airfoil body, a cover, and a stud. The cover may be disposed on at least one of a suction side and a pressure side of the airfoil body and the stud may extend through the cover and into the airfoil body and the stud may be is joined to the airfoil body and the cover by a friction weld.

Abstract: A method of estimating an unknown solvus for a phase of a given alloy includes providing empirical data of a plurality of alloys from an alloy class, the empirical data at least including chemical compositions, heating rates, cooling rates and alloy solvus temperatures of the plurality of alloys, providing an alloy chemical composition, a selected heating rate and a selected cooling rate of another alloy from the alloy class that has an unknown solvus temperature, estimating the unknown solvus temperature based upon the empirical data to provide an estimated solvus temperature of the alloy, and establishing a solution heat treatment temperature corresponding to the estimated solvus temperature at which to treat a component that includes the alloy.

Abstract: A coating including a structural matrix having a porosity and a solid lubricant that at least partially fills the porosity.

Abstract: Attaching a fastener to a ceramic matrix composite or ceramic body by inserting a portion of the fastener into a compartment of the body, the compartment having a first portion and a second portion, the second portion outboard of and narrower than the first portion; and delivering a fluid into the fastener to expand a portion of the fastener within the blind compartment first portion.

Abstract: A coating including a structural matrix having a porosity and a solid lubricant that at least partially fills the porosity.