Abstract: A turbine comprising a first turbine component being of a first material having a first coefficient of thermal expansion. A second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component. A space between said first and second turbine components. A seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.

Abstract: An airfoil includes a leading edge, a trailing edge, and a pair of sides extending from the leading edge to the trailing edge. The airfoil also includes an internal cooling flow passage defined between the sides, wherein the passage has a passage axis along which cooling air is to flow. The airfoil further includes a plurality of flow paths extending through at least one of the sides such that the flow paths are configured to discharge cooling air from the passage, wherein each of the flow paths has a broken flow path axis oriented to intersect the passage axis at an acute angle.

Abstract: A shroud for turbine engines. The shroud has an integrated anti-rotation device that prevents circumferential movement of the shroud during normal engine operation, and which allows for circumferential installation in split annular case designs. Since the anti-rotation device is an integral part of the shroud and/or annular split turbine case, no additional parts are necessary for assembly or disassembly. Moreover, existing annular split turbine cases can be reworked to accept the anti-rotation device and yet still be backwards compatible with original shroud designs.

Abstract: A turbine blade includes forward and aft serpentine cooling circuits terminating in corresponding forward and aft impingement channels. Each serpentine circuit has two metered inlets for distributing primary inlet flow to the first passes thereof and supplemental inlet flow to the last passes thereof.

Abstract: A shroud apparatus for a gas turbine engine includes: an annular shroud segment having an arcuate bottom wall defining an arcuate inner flowpath surface, spaced-apart forward and aft walls extending radially outward from the bottom wall, and spaced-apart side walls extending radially outward from the bottom wall and between the forward and aft walls, each side wall defining an end face which includes: an axial slot extending in a generally axial direction along the end face; a first radial slot extending in a generally radial direction along the end face, and intersecting the axial slot; an axial spline seal received in the axial slot; and a first radial spline seal having an L-shape with radial and axial legs, the radial leg being substantially longer than the axial leg, wherein the radial leg is received in the first radial slot, and the axial leg is received in the axial slot.

Abstract: An airfoil includes a leading edge, a trailing edge, and a pair of sides extending from the leading edge to the trailing edge. The airfoil also includes an internal cooling flow passage defined between the sides, wherein the passage has a passage axis along which cooling air is to flow. The airfoil further includes a plurality of flow paths extending through at least one of the sides such that the flow paths are configured to discharge cooling air from the passage, wherein each of the flow paths has a broken flow path axis oriented to intersect the passage axis at an acute angle.

Abstract: A component for a gas turbine engine is provided. The component includes a cooling aperture and a plug filling at least a portion of the cooling aperture to prevent airflow through the cooling aperture. The plug is configured to melt at a predetermined temperature during operation of the gas turbine engine to permit airflow through the cooling aperture.

Abstract: A method for repairing a turbine nozzle segment includes providing a turbine nozzle segment having an enclosure with an integral discourager, removing the enclosure and/or the discourager from the turbine nozzle segment and attaching a new enclosure ad/or discourager to the turbine nozzle segment.

Abstract: A turbine nozzle includes a row of vanes extending radially in span between inner and outer bands. The vanes include opposite pressure and suction sidewalls and opposite leading and trailing edges. Each vane includes an inner pattern of inner cooling holes and an outer pattern of outer cooling holes distributed along the leading edge. The inner and outer holes diverge toward the corresponding inner and outer bands to preferentially discharge cooling air.

Abstract: A turbine nozzle segment includes a band having a flowpath side and a non-flowpath side and an enclosure disposed on the non-flowpath side of the band. A plenum may be defined between the band and the enclosure and a discourager may extend from the enclosure.

Abstract: A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.

Abstract: A shroud for turbine engines. The shroud has an integrated anti-rotation device that prevents circumferential movement of the shroud during normal engine operation, and which allows for circumferential installation in split annular case designs. Since the anti-rotation device is an integral part of the shroud and/or annular split turbine case, no additional parts are necessary for assembly or disassembly. Moreover, existing annular split turbine cases can be reworked to accept the anti-rotation device and yet still be backwards compatible with original shroud designs.

Abstract: A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.

Abstract: A turbine blade with improved tip cooling includes an airfoil having a tip cap and a tip wall extending outwardly from the tip cap. A recessed portion of the tip wall forms a tip shelf. At least one tip shelf hole extends through the tip shelf in flow communication with an internal airfoil cooling circuit. At least one tip wall opening extends through the recessed portion of the tip wall radially outward of the tip shelf in flow communication with the internal cooling circuit. The recessed tip wall portion may be tapered from a wider base to a minimum thickness. In a cooling method, cooling air channeled through the tip wall openings joins and mixes with a stream of hot combustion gases downstream of where cooling air channeled through the tip shelf openings joins and mixes with the stream of hot gasses to enhance convection cooling of the blade tip.

Abstract: An MSW processing apparatus includes two or more semi-isolated reaction chambers separated from one another by isolation regions configured with two or more TIG elements, either or both of which may be independently purged. The TIG elements may be configured in a staircase-like fashion and include vertical and horizontal conductance spacings, sized so that, under different operational process temperatures of the MSW processing apparatus, a change in the horizontal conductance spacing is less than a change in the vertical conductance spacing.

Abstract: A turbine airfoil for a gas turbine engine includes: (a) spaced-apart pressure and suction sidewalls extending between a leading edge and a trailing edge; (b) a first cavity disposed between the pressure and suction sidewalls, the first cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates with an exterior surface of the airfoil; (c) a second cavity disposed between the pressure and suction sidewalls, the second cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates solely with the suction sidewall of the airfoil; and (d) a metering structure adapted to substantially restrict air flow into the second cavity.

Abstract: A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.

Abstract: A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component.

Abstract: A method for repairing a turbine nozzle segment includes providing a turbine nozzle segment having an enclosure with an integral discourager, removing the enclosure and/or the discourager from the turbine nozzle segment and attaching a new enclosure ad/or discourager to the turbine nozzle segment.

Abstract: A turbine nozzle segment includes a band having a flowpath side and a non-flowpath side and an enclosure disposed on the non-flowpath side of the band. A plenum may be defined between the band and the enclosure and a discourager may extend from the enclosure.