Abstract: A turbine vane with an airfoil extending between an inner diameter endwall and an outer diameter endwall, where thin slots are formed between the airfoil and the endwall in the trailing edge section in which cooling air is supplied to produce impingement cooling and purge air to prevent hot gas flow across the slots. The thin slot functions to thermally de-couple the thin airfoil trailing edge section from the thick endwall to prevent cracks.

Abstract: A turbine rotor blade with a dual triple pass serpentine flow cooling circuit in which a first triple pass serpentine circuit flows along the pressure side wall and the second triple pass serpentine circuit flows along the suction side wall to provide near wall cooling to the two walls. The legs of the serpentine flow cooling circuits have slanted ribs that form diamond shaped mixing chambers such that a criss-cross flow path for the cooling air is formed. In one embodiment, the last leg of the first serpentine circuit provides cooling to the leading edge region with showerhead film holes while the last leg of the second serpentine provides cooling to the trailing edge region with a row of exit holes. In other embodiments, the two serpentine circuits flow in a forward or a rearward direction with two trailing edge cooling channels arranged in the trailing edge and with a separate leading edge cooling supply channel to provide cooling air form the leading edge region.

Abstract: A turbine stator vane with endwall cooling that includes a row of submerged cooling air channels or slots that include a metering hole at an inlet end, a diffusion chamber downstream from the metering hole, and an open slot that channels and discharges the cooling air from the slots as film cooling air for the endwalls. Each submerged cooling air slot can be customized for pressure and flow to control metal temperature and cooling capability.

Abstract: A turbine rotor blade with a 5-pass serpentine aft flowing cooling circuit having first and second tip turns under the blade tip floor, and a core print-out hole having two inlets and one common outlet that discharges cooling air from the two tip turns out from the blade tip. A first inlet of the core print-out hole opens into the first tip turn, and a second inlet of the core print-out hole opens into the second tip turn. The core print-out hole is formed by a T-shaped ceramic core connector that also positions the core or cores used to cast the serpentine flow cooling circuit within the blade.

Abstract: A turbine rotor blade formed from three pieces with a pressure wall side piece and a suction wall side piece bonded to an intermediate piece so that a pressure side cooling circuit can be formed as a separate cooling circuit from a suction side cooling circuit. The intermediate piece has film cooling holes and blade tip cooling holes and trailing edge exit slots formed in it that are enclosed when the outer two pieces are boded to it.

Abstract: A turbine rotor blade with a showerhead arrangement of film cooling holes arranged in three zones with a lower span zone and a middle spa zone and an upper span zone. The film cooling holes in the lower zone have a greater ejection angle than the film holes in the middle span zone, and the middle span zone film holes have a greater ejection angle than the film holes in the upper span zone.

Abstract: A turbine stator vane with a low volume cooling circuit, the vane includes inner and outer endwall impingement cavities that feed cooling air to upward and downward flowing near wall cooling passages formed within the walls of the airfoil. The cooling passages then discharge into a collection cavity where the cooling air then flows out through trailing edge exit holes to cool the trailing edge region. The cooling passages are staggered from upward flowing to downward flowing.

Abstract: A turbine rotor blade with a platform cooling circuit that includes three zones with one zone occupying the entire pressure side of the platform and two zones occupying the entire suction side of the platform. Each zone is formed with a series of impingement ribs that form separated impingement chambers with impingement holes formed in the ribs to form a series of impingement holes with impingement chambers along the entire platform. Each zone is supplied with cooling air from one or more cooling air supply holes located in the forward most impingement chamber. The three zones discharge cooling air out through exit holes located along the two mate-faces and the aft side of the platform so that the cooling air discharged does not overlap.

Abstract: A method and a system to measure and monitor post-sales conditions within a network-based trading platform including a post-sales management module automatically to monitor post-sales parameters pertaining to an inventory of sold items and an alert module automatically to generate an alert when at least one post-sales parameter transgresses a threshold.

Abstract: A turbine vane for a gas turbine engine with an internal cooling system formed from a serpentine cooling channel with one or more flow blocking ribs is disclosed. The serpentine cooling channels may be configured to receive cooling fluids from internal cooling fluids supply channels. The serpentine cooling channels may include flow blocking ribs to form concurrent flow channels to reduce the cross-sectional area within the midchord region of the airfoil to maintain the internal through flow channel Mach number. The flow blocking ribs may include slots therein and may have any appropriate configuration. In at least one embodiment, the flow blocking ribs may be have a nonuniform taper or a uniformed taper.

Abstract: A turbine rotor blade with a platform includes platform cooling channels on the pressure side and the suction side of the platform. The cooling channels are formed from straight section that generally follows a contour of the airfoil in order to provide cooling to as much of the platform surfaces as possible. Pressure side cooling channels have a V-shape from inlet to outlet. Suction side channels branch off from a common channel located along a suction side edge of the platform.

Abstract: A turbine rotor blade with a hollow open cavity formed between the airfoil walls, and radial flow near wall cooling channels formed within the walls that open on the tip surface to discharge the cooling air for sealing of the tip. The radial channels have a converging flow area to increase the cooling air flow velocity, and the radial cooling channels on the pressure side wall are slanted toward the pressure side so that the discharged cooling air will produce a smaller vena contractor and further reduce tip leakage flow.

Abstract: A turbine rotor blade with a cooling air channel formed in a mid-chord region, the channel includes a number of rows of semi-circular shaped ribs that extend across the channel and open toward the blade tip. Adjacent ribs form metering and impingement passages that discharge a jet of cooling air against the rib above it. The open ends of the ribs form vortex generating passages in which the impingement cooling air flows into to form a vortex flow pattern in the cooling air.

Abstract: A turbine rotor blade with counter flowing near wall cooling channels that includes an outer spanwise flowing near wall cooling channel and an inner chordwise flowing near wall cooling channel connected in series and with an arrangement of pedestals to produce turbulent flow. Cooling air form the spanwise flow channels flows through a blade tip floor cooling channel and then into a collection cavity, and then through impingement cooling holes in the leading edge region and into the chordwise channels before discharging out exit holes on both sides of the blade. An arrangement of pedestals forms 90 degree flow paths through the near wall cooling channels.

Abstract: A turbine rotor blade with a thin thermal skin bonded to a spar to form a near-wall cooled blade, the blade having a near-wall cooling circuit formed by plurality of multiple pass serpentine flow cooling circuits that have cooling channels formed within the airfoil walls and the platform, and with a row of cooling air exit slots that connect to the last leg of the serpentine flow cooling channels and open onto an upstream side of the tip edge so that cooling air is discharged to form a blockage for the blade tip. The airfoil walls include radial extending cooling channels that form the airfoil legs of the serpentine cooling circuits.

Abstract: A trailing edge cooling circuit for a turbine rotor blade, which includes a radial flow cooling channel that supplies cooling air for the T/E region of the blade. Three radial flow cooling channels are located adjacent to one another and connected to the radial flow cooling supply channel, each discharging through an opening along the T/E just underneath the blade tip. The radial flow cooling channels in the T/E region are connected together by rows of metering holes in the middle spanwise height of the blade that produce mixing of the cooling air flowing upward toward the blade tip and improve the cooling effectiveness of the cooling air. A row of exit holes along the T/E discharge cooling air from the third radial flow cooling channel.

Abstract: A BOAS with a blade tip shroud having a row of teeth formed by rows of grooves on an underside surface, and where rows of teeth include cooling air passages to provide cooling for the blade tip shroud and to discharge cooling air into the blade tip gap to reduce an effective hot gas leakage area to reduce the blade tip leakage flow. The cooling passages include inlet convergent channels to increase the cooling air flow velocity, followed by flow metering sections and then cooling air exit slots that open onto the bottom surface of the teeth.

Abstract: A ring segment for a turbine in an industrial gas turbine engine, the ring segment having an inner side with a number of pedestals extending radially inward, each pedestal having an inlet metering hole connected to a diffusion chamber having an opening flush with a TBC covering the pedestals. The pedestals form a larger surface area to secure the TBC to the ring segment so that the TBC can be formed thicker than the prior art without spalling.

Abstract: A turbine blade with a squealer pocket formed by a tip rail extending along the pressure side and suction side of the tip. A row of diffusion trenches are spaced along the pressure side tip rail and the suction side tip rail, each trench formed by side walls and a bottom wall so that the front face and top face of the trench is open. Each trench includes side walls that increase in width in the direction of the tip crown, is connected by a metering hole to discharge cooling air into the trench, are separated from each other and are spaced from near the leading edge to near the trailing edge, and includes a curved inward surface toward the squealer pocket. Two rows of convective cooling holes are spaced adjacent to the pressure side tip rail and the suction side tip rail and open into the squealer pocket.

Abstract: Turbine stator vane with endwall cooling that includes a number of impingement chambers that extend around the airfoil perpendicular to a hot gas flow over the endwall, the impingement chambers are connected by rows of near wall cooling channels offset so that impingement cooling occurs within the chambers, some of the impingement chambers are connected by resupply cooling air holes and some of the impingement chambers are connected to film cooling holes.