Abstract: Disclosed herein are modified human interleukin-2 (hIL-2) proteins, human antibody molecules, or antigen-binding fragments thereof, that immunospecifically bind to human programmed cell death protein-1 (hPD-1), and immunoconjugates comprising the same.

Abstract: A gas turbine engine airfoil includes an airfoil outer wall having widthwise spaced apart pressure and suction sidewall sections extending chordally between leading and trailing edges of the airfoil and extending longitudinally from a base to a tip. Inside the airfoil is at least one internal cooling circuit having a plurality of longitudinally extending circuit channels between longitudinally extending internal ribs extending widthwise between the pressure and suction sidewall sections and a longitudinally extending first sidewall film cooling chamber positioned between one of the sidewall sections and a first inner wall bounding the cooling circuit. Sidewall film cooling holes extend through the pressure sidewall section from the first sidewall film cooling chamber.

Abstract: A double-wall airfoil for applications such as the blades and vanes of gas turbine engines. The double-wall comprises an outer airfoil skin and an inner support wall that are metallurgically bonded to one another. The double-wall contains integral channels for passage of cooling air adjacent to the airfoil skin. Airfoil skin may be a metal alloy skin or a microlaminate structure, including microlaminate composite structures. Microlaminate composites typically have a lower density than that of the material used for the airfoil support wall, and a simplified internal geometry which promote weight reductions in the airfoils and increases in engine operating efficiency.

Abstract: An airfoil for a gas turbine engine is constructed from a core body formed of a conventional nickel-based superalloy and leading and trailing edge components and squealer tip formed of a nickel aluminide alloy. The nickel aluminide components exhibit a high degree of thermal conductivity and efficiently transfer heat into the core body by direct conduction.

Abstract: Sheet Metal thermal control dampers are disposed in the cavities between turbine blades to bear against the undersides of opposed blade platforms portions of angularly adjacent blades under centrifugal loading to dampen blade vibrations and to seal the gaps between platforms against the radial flow of working fluid into the interblade cavities. The dampers are configured to cooperate with forward and aft seals to also block the axial flow of working fluid through the interblade cavities. Holes are provided in the dampers through which cooling air introduced into the interblade cavities can flow into contact with the platform undersides and cool the platforms, thereby controlling temperature rise in the blade attachment structure.

Abstract: Thermally actuated flow diverters for gas turbine engines are provided which include an arrangement of vanes in spaced overlapping array, which direct, e.g. coolant air flow to rotating engine components, each vane having 3 foil components joined at 3 hinge points. That is, a leading foil positioned on the suction side of the vane, a trailing foil pivotably mounted to a rearward portion of such leading foil at a first pivot axis and a third foil positioned on the pressure side of the vane connecting a forward portion of such leading foil and such trailing foil at second and third pivot axes respectively. Either the third foil or the leading foil is fixedly mounted to engine walls of the same material, the other of these two foils defining an actuation link that is expandable and contractable relative to such walls; the third foil having a coefficient of thermal expansion greater than that of the leading foil.

Abstract: A metal detector search head which includes a transmitter wire coil and a receiver wire coil each having first and second coil sections. The first coil sections of the receiver and transmitter coils lie in substantially the same plane with the second coil sections thereof being parallel and displaced relative to the first coil sections with each second coil section lying in a plane generally perpendicularly oriented to the plane of location of the first coil sections of the transmitter and receiver coils.