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: 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 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 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 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 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 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: 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 turbine nozzle includes a vane joined to opposite inner and outer bands. The inner band includes a pocket adjoining a flange which recesses in part the inner surface of the band. The pocket undercuts the flange to form a notch at the base thereof.

Abstract: A turbine nozzle includes a row of vanes in corresponding segmented outer and inner bands. The inner band of each segment includes a retention flange. A nozzle support includes forward and aft flanges defining a retention slot receiving the retention flange. The retention flange includes a radial lug trapped axially in the retention slot, and a tangential lug at an opposite circumferential end disposed on the forward flange. The aft flange includes an outer hinge, and the retention flange further includes an inner hinge for cradle mounting the retention flange in the nozzle support.

Abstract: A turbine nozzle includes a row of vanes in corresponding segmented outer and inner bands. The inner band of each segment includes a retention flange. A nozzle support includes forward and aft flanges defining a retention slot receiving the retention flange. The retention flange includes a radial lug trapped axially in the retention slot, and a tangential lug at an opposite circumferential end disposed on the forward flange. The aft flange includes an outer hinge, and the retention flange further includes an inner hinge for cradle mounting the retention flange in the nozzle support.