Abstract: Embodiments of the present disclosure include a gas turbine engine system. The system may include a rotor wheel having a number of blades mounted about a periphery of the rotor wheel. Further, the system may include a retention device. The retention device may include a number of projections extending from a radial surface of the rotor wheel to form a number of circumferential slots about the rotor wheel. The retention device may also include a number of elongated members positioned within the circumferential slots to impede axial movement of the blades.

Abstract: Systems, methods, and apparatus for linking machine stators are provided. A bracket may be utilized to link adjacent stators within a machine, for example, a turbine. The bracket may include a body portion, a first plurality of extensions, and a second plurality of extensions. The body portion may include a first edge operable to align with a base of a first stator and a second edge opposite the first edge and operable to align with a base of a second stator. The first plurality of extensions may extend from the first edge and may be operable to align with at least one corresponding groove on the base of the first stator. The second plurality of extensions may extend from the second edge and may be operable to align with at least one corresponding groove on the base of the second stator. When utilized to link the first stator and the second stator, the bracket may facilitate a reduction of vibrations in the first stator and the second stator.

Abstract: An axial retention system for restraining axial movement of a machine component having a dovetail within a complimentary-shaped dovetail slot includes: a first substantially T-shaped groove formed in a bottom surface of the dovetail slot; a second substantially T-shaped groove formed in a bottom surface of the dovetail, the first and second grooves in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery substantially T-shaped slot having a stem portion and a lateral cross portion at one end of the stem component, wherein the other end of the stem is open; and a compressible locking clip adapted for insertion within the substantially T-shaped slot, the locking clip having a pair of oppositely extending lugs receivable in opposite ends of the lateral cross portion.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: A rotating assembly. The rotating assembly may include a wheel, a slot positioned about the wheel with the slot having a staking recess positioned therein, a wheel attachment positioned within the slot, and a staking insert positioned within the staking recess. The staking recess axially retains the staking insert and the wheel attachment radially retains the staking insert.

Abstract: An axial retention system for restraining axial movement of a first machine component having a dovetail within a complimentary-shaped dovetail slot in a second machine component that includes a first curved groove formed in a bottom surface of the dovetail slot and a second curved groove formed in a bottom surface of the dovetail. The first and second grooves are in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery aperture. A curved locking clip is received within the closed periphery aperture. An optional cover plate may be placed over the ends of the locking clip, with ends of the locking clip deformed by, for example, swaging.

Abstract: An axial retention system for restraining axial movement of a first machine component having a dovetail within a complimentary-shaped dovetail slot in a second machine component that includes a first curved groove formed in a bottom surface of the dovetail slot and a second curved groove formed in a bottom surface of the dovetail. The first and second grooves are in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery aperture. A curved locking clip is received within the closed periphery aperture. An optional cover plate may be placed over the ends of the locking clip, with ends of the locking clip deformed by, for example, swaging.

Abstract: Systems, methods, and apparatus for linking machine stators are provided. A bracket may be utilized to link adjacent stators within a machine, for example, a turbine. The bracket may include a body portion, a first plurality of extensions, and a second plurality of extensions. The body portion may include a first edge operable to align with a base of a first stator and a second edge opposite the first edge and operable to align with a base of a second stator. The first plurality of extensions may extend from the first edge and may be operable to align with at least one corresponding groove on the base of the first stator. The second plurality of extensions may extend from the second edge and may be operable to align with at least one corresponding groove on the base of the second stator. When utilized to link the first stator and the second stator, the bracket may facilitate a reduction of vibrations in the first stator and the second stator.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: An axial retention system for restraining axial movement of a machine component having a dovetail within a complimentary-shaped dovetail slot includes: a first substantially T-shaped groove formed in a bottom surface of the dovetail slot; a second substantially T-shaped groove formed in a bottom surface of the dovetail, the first and second grooves in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery substantially T-shaped slot having a stem portion and a lateral cross portion at one end of the stem component, wherein the other end of the stem is open; and a compressible locking clip adapted for insertion within the substantially T-shaped slot, the locking clip having a pair of oppositely extending lugs receivable in opposite ends of the lateral cross portion.

Abstract: A method is provided for attaching a shim to at least one of a base of a stator vane unit and a ring segment of a ring segment assembly in a gas turbine compressor. The method includes providing a shim shaped to conform to an engaging face of the base of the stator vane unit or the segment ring of the segment ring assembly, with a predetermined thickness dimension; boring at least one hole, normal to the face of the shim and extending fully through the thickness dimension of the shim; positioning the shim on the engaging face of the at least one of the base of the stator vane unit and the segment ring of the segment ring assembly; and welding the shim to the engaging face of the at least one of the base of the stator vane unit and the ring segment of the stator ring assembly.

Abstract: Vibration induced compressor vane failure from tip leakage vortex bursting is eliminated or minimized. By securing the vane at opposite ends to inner and outer stationary casings, tip leakage is entirely avoided hence avoiding the mechanism for inducing vibration. By contouring the inner surface of the flow path to converge the flow in a downstream direction with a cantilevered compressor vane having a vane tip spaced from the inner casing surface, airflow lift off is precluded or minimized maintaining the flow attached to the flowpath surfaces with consequent avoidance of tip vortex induced vibration.

Abstract: A turbine component includes mounting structure for attaching the turbine component. A core is attached to the mounting structure. The core is made from a structural material. A plastic airfoil portion envelopes at least a portion of the core.

Abstract: A method of manufacturing a composite airfoil includes the step of providing a core made of a metal or ceramic material. A plastic airfoil portion is molded to envelope at least a portion of the core.

Abstract: A rotating assembly. The rotating assembly may include a wheel, a slot positioned about the wheel with the slot having a staking recess positioned therein, a wheel attachment positioned within the slot, and a staking insert positioned within the staking recess. The staking recess axially retains the staking insert and the wheel attachment radially retains the staking insert.

Abstract: A method is provided for attaching a shim to at least one of a base of a stator vane unit and a ring segment of a ring segment assembly in a gas turbine compressor. The method includes providing a shim shaped to conform to an engaging face of the base of the stator vane unit or the segment ring of the segment ring assembly, with a predetermined thickness dimension; boring at least one hole, normal to the face of the shim and extending fully through the thickness dimension of the shim; positioning the shim on the engaging face of the at least one of the base of the stator vane unit and the segment ring of the segment ring assembly; and welding the shim to the engaging face of the at least one of the base of the stator vane unit and the ring segment of the stator ring assembly.