Abstract: Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

Abstract: Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

Abstract: Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

Abstract: Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

Abstract: Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

Abstract: Dual alloy bladed rotors are provided, as are methods for manufacturing dual alloy bladed rotors. In one embodiment, the method includes arranging bladed pieces in a ring formation such that contiguous bladed pieces contact along shank-to-shank bonding interfaces. The ring formation is positioned around a hub disk, which is contacted by the bladed pieces along a shank-to-hub bonding interface. A metallic sealing material is deposited between contiguous bladed pieces utilizing, for example, a laser welding process to produce an annular seal around the ring formation. A hermetic cavity is then formed, which is circumferentially bounded by the annular seal and which encloses the shank-to-shank and shank-to-hub bonding interface. Afterwards, a Hot Isostatic Pressing process is performed during which the ring formation and the hub disk are exposed to elevated pressures external to the hermetic cavity sufficient to diffusion bond the shank-to-shank and shank-to-hub bonding interface.

Abstract: Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel. The second clip has a bumper portion that extends into the spaced defined by the at least one notch, and the bumper portion is adapted to contact the shroud.

Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

Abstract: Dual alloy bladed rotors are provided, as are methods for manufacturing dual alloy bladed rotors. In one embodiment, the method includes arranging bladed pieces in a ring formation such that contiguous bladed pieces contact along shank-to-shank bonding interfaces. The ring formation is positioned around a hub disk, which is contacted by the bladed pieces along a shank-to-hub bonding interface. A metallic sealing material is deposited between contiguous bladed pieces utilizing, for example, a laser welding process to produce an annular seal around the ring formation. A hermetic cavity is then formed, which is circumferentially bounded by the annular seal and which encloses the shank-to-shank and shank-to-hub bonding interface. Afterwards, a Hot Isostatic Pressing process is performed during which the ring formation and the hub disk are exposed to elevated pressures external to the hermetic cavity sufficient to diffusion bond the shank-to-shank and shank-to-hub bonding interface.

Abstract: Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel.

Abstract: Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.