Abstract: A turbine blade that may include a tip shroud, one or more cooling cavities formed within the tip shroud, and at least one discrete structural element defined within at least one of the cooling cavities. The discrete structural element may include an element that structurally connects a floor of the cooling cavity to a ceiling of the cooling cavity that does not originate from, terminate in, or connect to an interior wall of the cooling cavity or an outer edge of the tip shroud.

Abstract: A row of stator blades in a compressor of a combustion turbine engine, the combustion turbine engine including a diffuser located downstream of the compressor, and the row of stator blades disposed in close proximity to the diffuser; the row of stator blades comprising: a plurality of stator blades that include at least one of an inboard forward notch and an outboard forward notch.

Abstract: An annular dual-flow check valve for controlling the flow through concentric channels that have a common outlet, comprising: an outer body and an inner body that define the concentric channels, which include an outer channel and an inner channel formed therein; a spring activated annular poppet that resides in the outer channel and has a range of motion in the axial direction; and an opening through the inner body that connects the outer channel to the inner channel; wherein: the axial movement of the annular poppet is regulated by the pressure of the flow upstream of the annular poppet in the outer channel; and the axial range of motion of the annular poppet includes at least two axial positions: a closed position where the annular poppet substantially covers the opening and a open position where at least a portion of the opening is not covered by the annular poppet.

Abstract: A method of distributing charge capacity to electric vehicles in a charging system that includes a solar charge capacity generated locally. The method may include: determining a requested charge for the plurality of electric vehicles, calculating a requested charge time, the solar charge capacity comprising the total charging capacity of the charging system via solar generated energy; calculating a charge time capacity, the charge time capacity comprising the available charge time of the charging system; comparing the requested charge to the solar charge capacity; comparing the requested charge time to the charge time capacity; and if it is determined that either the requested charge is greater than the solar charge capacity or the requested charge time is greater than the charge time capacity, auctioning the solar charge capacity to operators of the plurality of electric vehicles.

Abstract: A turbine engine that includes a vortex protrusion disposed upon a component that rotates during operation of the turbine engine; wherein the vortex protrusion includes an outer surface that is configured to induce a vortex flow pattern as the component rotates during operation.

Abstract: An assembly for delivering a supply of liquid fuel and a supply of purge air to a gas turbine engine, the assembly comprising: an annular dual-flow check valve for controlling the flow through concentric channels that have a common outlet, the annular dual-flow check valve comprising: an outer body and an inner body that define the concentric channels, which include an outer channel and an inner channel formed therein; a spring activated annular poppet that resides in the outer channel and has a range of motion in the axial direction; and an opening through the inner body that connects the outer channel to the inner channel; wherein the axial movement of the annular poppet is regulated by the pressure of the flow upstream of the annular poppet in the outer channel; and the axial range of motion of the annular poppet includes at least two axial positions.

Abstract: An assembly of airfoils in a turbine engine, the assembly comprising: at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row; wherein the first airfoil row and the third airfoil row each comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other; and wherein at least a majority of the mid-channel points of the airfoils in the third airfoil row are positioned circumferentially within +/?25% pitch of the third airfoil row with respect to the location at which a wake flow during a selected operating condition from the first airfoil row is determined to enter the third airfoil row.

Abstract: A seal formed between at least two blades in the turbine of a turbine engine, a first turbine blade and a second turbine blade, wherein one of the turbine blades comprises a turbine rotor blade and the other turbine blade comprises a turbine stator blade, and wherein a trench cavity and the seal is formed between the first turbine blade and the second turbine blade when first turbine blade is circumferentially aligned with the second turbine blade, the seal comprising: a cutter tooth and a honeycomb; wherein: the cutter tooth comprises an axially extending rigid tooth that is positioned on one of the first turbine blade and the second turbine blade and the honeycomb comprises an abradable material that is positioned on the other of the first turbine blade and the second turbine blade; and the cutter tooth and the honeycomb are positioned such that each opposes the other across the trench cavity when the first turbine blade is circumferentially aligned with the second turbine blade.

Abstract: The present application thus describes a solar-thermal power generation plant that includes one or more towers; a plurality of heliostats disposed around each of the one or more towers; a direct solar evaporator mounted at an elevated position on each of the one or more towers, the heliostats being configured to reflect solar radiation toward the direct solar evaporator such that concentrated solar radiation heats a receiving surface on the direct solar evaporator; and a heat engine mounted at an elevated position on each of the one or more towers, attached to the direct solar evaporator, and configured to use the heat from the receiving surface on the direct solar evaporator to generate electricity.

Abstract: A method of calculating the tip clearance during operation of a combustion turbine engine that includes the steps of: measuring a cold tip clearance and a cold shell-to-shell distance; while the combustion turbine engine is operating, measuring an operating parameter and measuring a shell-to-shell distance with a proximity sensor; calculating the tip clearance based on the cold tip clearance measurement and the operating parameter measurement; calculating the shell-to-shell distance based on the cold shell-to-shell distance measurement and the operating parameter measurement; comparing the shell-to-shell distance measurement of the proximity sensor with the shell-to-shell distance calculation; and calibrating the calculated tip clearance calculation based on the comparison.

Abstract: A turbine blade with a generally hollow airfoil having an outer wall that defines a chamber for receiving cooling air, the airfoil comprising a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, a concave pressure side, and an insert disposed within the chamber that is configured to initially receive at least a portion of the cooling air entering the chamber and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall, the insert further comprising a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto, wherein the chamber and insert narrow as they extend toward the trailing edge, the insert eventually terminating and the chamber eventually terminating at a pin array section, wherein a first distance exists that comprises the generally axial distance between the position of downstream termination point of the insert an

Abstract: A flow directing assembly for use in a turbine engine comprising: a plurality of circumferentially spaced blades, each of the blades including a radial projecting airfoil with a concave pressure side and a convex suction side that extend from a platform; and a plurality of flow passages, each flow passage defined by the airfoils of neighboring blades and an inner wall formed by abutting platforms of neighboring blades, the inner wall forming the inner radial boundary of the flow passage; wherein the inner wall of one or more of the flow passages comprises means for reducing frictional losses between the flow through the turbine engine and the inner wall. The means for reducing frictional losses may comprise a non-axisymmetrical trough positioned between neighboring airfoils that is configured to reduce frictional losses.

Abstract: A combustor for a combustion turbine engine, the combustor that includes: a chamber defined by an outer wall and forming a channel between windows defined through the outer wall toward a forward end of the chamber and at least one fuel injector positioned toward an aft end of the chamber; a screen; and a standoff comprising a raised area on an outer surface of the outer wall near the periphery of the windows; wherein the screen extends over the windows and is supported by the standoff in a raised position in relation to the outer surface of the outer wall and the windows.

Abstract: A cart and detachable hangers system for transporting copper coils that may include: 1) a cart with a substantially rectangular structure that includes at least two opposing side rails and at least two opposing end rails; 2) a plurality of pockets disposed along a top surface of each of the two opposing side rails; and 3) a plurality of hangers, each of the hangers including two projections that are sized such that each may detachably engage one of the pockets. The hanger and the cart are sized such that the distance between the projections correspond approximately to the distance between the pocket on one upper side rail and the opposing pocket on the other upper side rail.

Abstract: A hollow passage in a machine element for enhancing the heat exchanging properties between the machine element and a fluid flowing through the hollow passage; the hollow passage including a helicoidal groove. In some embodiments, the machine element comprises a heated machine element and the fluid comprises a coolant. In some embodiments, the machine element comprises a stator blade or a rotor blade of a gas turbine engine and the coolant comprises compressed air. In some embodiments, the helicoidal groove comprises a depression in an outer wall of the hollow passage that extends axially along the hollow passage to form a helicoidal or swirling path.

Abstract: A turbine blade with a generally hollow airfoil having an outer wall that defines at least one radially extending chamber for receiving the flow of a coolant, the airfoil including a leading edge that resides in an upstream or forward direction, a trailing edge that resides in a downstream or aft direction, a convex suction side, and a concave pressure side, the turbine blade comprising: a plurality of inserts disposed within the chamber that are configured to initially receive at least a portion of the coolant entering the chamber and direct a substantial portion of the coolant through a plurality of insert apertures toward the inner surface of the outer wall; wherein the inserts are configured to form at least one inward bleed channel and a central collector passage into which the inward bleed channel flows.

Abstract: A method of constructing an industrial machine such that, in operation, a supply of a fluid coolant through a hollow passageway is delivered at a reduced temperature, the method including the steps of: a) identifying at least a section of the hollow passageway that transports or is meant to transport the fluid coolant through a space that resides at a temperature that is significantly higher than a desired temperature of the fluid coolant; and b) through at least a majority of the identified section of the hollow passageway that transports the fluid coolant through the space that resides at the temperature that is significantly higher than the desired temperature of the fluid coolant, constructing the hollow passageway such that the outer surface of the hollow passageway has an emissivity coefficient less than about 0.1.

Abstract: An airfoil assembly for a turbine engine, that may comprise: an airfoil that includes at least one panel opening formed therein; and an aperture panel that includes at least one cooling aperture; wherein the panel opening and the aperture panel are configured such that, upon installation of the aperture panel within the panel opening, a substantially smooth outer surface of the airfoil is formed and at least one of the cooling apertures of the aperture panel forms an exit passageway from at least one hollow internal cavity within the airfoil.

Abstract: A system for detecting defects in a combustion duct of a combustion system of a combustion turbine engine while the combustion turbine engine operates, wherein the combustion duct comprises a hot side, which is exposed to combustion gases and, opposing the hot side, a cold side. In one embodiment, the system comprises: a photodetector aimed at the cold side of the combustion duct, the photodetector being configured to detect a visible change to the cold side of the combustion duct.

Abstract: A blade tip of a turbine rotor blade for a gas turbine engine, the turbine rotor blade including an airfoil and a root portion for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from the root portion to the blade tip, and a squealer tip cavity formed at the blade tip, the blade tip comprising: a trailing edge trench originating at the squealer tip cavity, wherein the trailing edge trench generally extends toward the trailing edge of the blade tip.