Abstract: Aspects of the invention relate to a cooling system for a blade platform that can provide cooling to and reduce stress on the platform. Aspects of the invention relate to including one or more channels in the blade platform such that the channels extend from the trailing edge face of the platform toward, but terminate prior to, the leading edge face of the platform. The channels can be generally oval or oblong in conformation. Extending between the hollow shank and the channels can be a plurality of cooling holes. During engine operation, coolant is supplied to the shank of the blade assembly. Because the pressure at the shank is greater than the pressure at the trailing edge of the platform, coolant flow is induced through the cooling holes and into the channels. After flowing through the channels, the coolant can be dumped at the trailing edge.

Abstract: A process to desulfurize a fuel gas, such as natural gas, for use as a feed fuel for a fuel cell is characterized by providing a feed stream (10) of sulfur containing gas, passing part of that as a stream (12) to a compressor (14), passing the compressed stream to a sulfur selective membrane (16) to provide a sulfur rich stream (18) which is returned to the feed stream (10), and a sulfur lean stream (20) which can be passed to an optional gas meter (26) and then to a sulfur sorbent medium (28) before reforming the essentially sulfur free stream (34) in the reformer (40) of a fuel cell unit (36) also containing a fuel cell (38).

Abstract: An electrical generator (80) utilizes supplemental blowers or fans (140) to move additional cooling fluid through coolant flow paths (116, 124) in the generator, thus reducing the internal temperature of the generator. The supplemental blower comprises a blower (160) for supplementing cooling fluid flow through a discharge coolant flow path (155) and/or a supplemental blower (176, 178) for supplementing cooling fluid flow through an inlet coolant flow path (156). Either supplemental blower has the effect of lowering the peak internal generator temperature (134).

Abstract: A detection system for identifying airfoils having a cooling systems with orifices that are plugged with contaminants or with showerheads having a portion burned off. The detection system measures pressures at different locations and calculates or measures a differential pressure. The differential pressure may be compared with a known benchmark value to determine whether the differential pressure has changed. Changes in the differential pressure may indicate that one or more of the orifices in a cooling system of an airfoil are plugged or that portions of, or all of, a showerhead has burned off.

Abstract: An improved generator rotor (30) and a method of repairing an existing generator rotor (12) are disclosed. Methods consistent with the present invention provide techniques for repairing existing stress-damaged rotors (12) to remove stress-induced cracks (29), without requiring new retaining rings (16), to significantly extend the useful life of a generator without the cost and complexity of conventional repair techniques. Improved generator rotors (30) consistent with the present invention provide a tooth-top design that is more resistant to stress-induced cracking than conventional designs, resulting in new generators with longer useful lives.

Abstract: A gas-cooled turbine generator includes a rotor having baffles arranged in rings and defining a plurality of gas cooling zones. A stator core has stator slots in a bore in which the rotor is received. A plurality of air gap baffle assemblies are arranged in segmented baffle rings in the stator slots and cooperate with the zone rings on the rotor. Each of the air gap baffle assemblies includes at least one baffle segment and an individual locking cam cooperating with a respective wedge of the baffle segment to lock the baffle segment relative to a stator slot at which the baffle segment is positioned such that prior baffle “trains” are no longer required.

Abstract: A corona suppression apparatus for a dynamoelectric machine having a stator coil (12) covered with a corona suppression covering (16), the apparatus including a member (10) conducting to ground (20) abutting a top layer (28) of the corona suppression covering proximate an overlap region (18) of the corona suppression covering. The member may be positioned in a gap (30) between the stator coil corona suppression covering and a stator core clamping finger (24) extending from the stator core proximate the stator coil. The member may also be configured to exert a compressive force on the overlap region by being compression biased between the corona suppression covering and the stator core clamping finger.

Abstract: A method for controlling the injection of water into the combustor (16) of a gas turbine (18) may include determining a flow rate of water to be injected into the combustor (16) and controlling (86) a centrifugal pump (20) with a variable frequency drive (40) to control the flow rate of water. The flow rate of water may be further controlled by controlling (88) a throttle valve (32) to control water flow through a recirculation line (28) of a water circuit (24) that directs the flow rate of water to the combustor (16). A system (10) for controlling the injection of water into the combustor (16) may include a water delivery circuit (24) for directing water from a water supply (12) to the combustor (16), a centrifugal pump (20) for pumping water through the water delivery circuit (24) and a variable frequency drive (40) for controlling a motor (42) driving the centrifugal pump (20).

Abstract: A component (10) having a thermal barrier coating (14) exhibiting an improved resistance to thermal shock. A plurality of stress relieving cracks (22) are formed at the free surface (24) of the thermal barrier coating as a result of the expansion of an inclusion (20) having a higher coefficient of thermal expansion than that of the surrounding matrix material (16). The inclusions function as crack initiators during the fabrication process as well as crack arrestors preventing the propagation of the cracks farther into the matrix material. The inclusion material may be selected to have an evaporation temperature that is less than the peak matrix material processing temperature, wherein the inclusion material will evaporate to leave a plurality of voids (30). In one embodiment, a superalloy substrate (12) is coated with a ceramic thermal barrier coating material having a plurality of spherical polymer inclusions disposed below its free surface.

Abstract: A cooled fluid flow component for a combustion engine which directs cooling fluid through complementary guided-flow regions to ensure effective cooling of the component tip end, without producing overcooled regions. The component includes multiple channels fluidly linked by a first turning zone. A contoured boundary member divides the turning zone into two guided-flow regions which cooperatively ensure that the tip is cooled appropriately. According to one aspect of the invention, the first guided-flow region forms a vortex that cools a region adjacent a channel-dividing partition, while the second guided flow region ensures the region adjacent the component tip is cooled appropriately. A method of cooling a internally-cooled fluid guide component is also provided.

Abstract: A device (10) is made, having a ceramic thermal barrier coating layer (16) characterized by a microstructure having gaps (18) with a sintering inhibiting material (22) disposed on the columns (20) within the gaps (18). The sintering resistant material (22) is stable over the range of operating temperatures of the device (10), is not soluble with the underlying ceramic layer (16) and is applied by a process that is not an electron beam physical vapor deposition process. The sintering inhibiting material (22) has a morphology adapted to improve the functionality of the sintering inhibiting material (22), characterized as continuous, nodule, rivulet, grain, crack, flake and combinations thereof and being disposed within at least some of the vertical and horizontal gaps.

Abstract: A dynamoelectric machine combining the functions of an exciter, a turning motor, and a starting motor for a turbine. The machine operates in a first mode where the slip between a first stator winding and a first armature winding is positive and thus the magnetic fields interact and operate as a motor to turn the turbine. In a second mode the slip is negative as the turbine turns the shaft and the first stator winding and the first armature operate as an exciter for supplying excitation to the rotating field winding of a main generator.

Abstract: A gas turbine combustor (10) having a first grouping (64) of pre-mix burners (12, 12?, 12?) having mixing passages (36) that are geometrically different than the mixing passages (38) of a second grouping (66) of pre-mix burners (14, 14?, 14?). The aerodynamic differences created by these geometric differences provide a degree of control over combustion properties of the respective flames (44, 46) produced in a downstream combustion chamber (40) when the two groupings of burners are fueled by separate fuel stages (52, 54). The geometric difference between the fuel passages of the two groupings may be outlet diameter, slope of convergence of the passage diameter, or outlet contour. The fuel injection regions (16, 18) of all of the burners may be identical to reduce cost and inventory complexity. The burners may be arranged in a ring (60) with a center pre-mix burner (68) being identical to burners of either of the groupings.

Abstract: A system for attaching liners to a carrier for forming inner surfaces of turbine combustor. The system may include one or more liners attached to a carrier using connectors engaged to the carrier on a cold side of the liner and may include one or more liners attached to the carrier using connectors engaged to a hot side of the liners. The carrier may include one or more access ports for accessing from the hot side connectors engaged to the carrier on the cold side. In at least one embodiment, the system may include attaching all liners, except for one liner, to a carrier using connectors coupled to the carrier on the cold side and may include attaching the one liner to the carrier using connectors coupled to the carrier on the hot side.

Abstract: A turbine blade for a turbine engine having one or more cavities in a trailing edge of the turbine blade for forming one or more vortices in inner aspects of the trailing edge. In at least one embodiment, the turbine blade may include one or more elongated cavities in the trailing edge of the blade formed by one or more ribs placed in a cooling chamber of the turbine blade. The elongated cavity in the trailing edge may have one or more orifices in the rib on the upstream side of the cavity. The orifice may be positioned relative to a vortex forming surface so that as a gas is passed through one or more orifices into the elongated cavity, one or more vortices are formed in the cavity. The gas may be expelled from the cavity and the blade through one or more orifices in an inner wall forming the pressure side of the turbine blade.

Abstract: An alumina comprising composition protective overlayer (20) for protecting a ceramic matrix composite material (12) from a high temperature, moisture-containing environment. Alumina may be used as a protective overlayer to protect an underlying mullite layer to temperatures in excess of 1,500° C. The coating may have porosity of greater than 15% for improved thermal shock protection. To prevent the ingress of oxygen to an underlying ceramic material, an oxide barrier layer may be optionally disposed between the alumina coating and the ceramic material. Such a protective overlayer may be used for an article having a ceramic oxide or non-oxide substrate.

Abstract: Aspects according to the invention relate to a locking spacer assembly for a slotted turbine engine component. In one embodiment, aspects of the invention can be used in connection with the assembly and disassembly of a disc hosting a row of airfoils as can be found in the compressor or turbine section of a turbine engine. The spacer according to the invention is a multi-part assembly. In one embodiment, the spacer includes at least three sub-components: first and second end supports and a filler. The inner and outer faces of each of these components can have various features to facilitate engagement of the assembly and distribution of centrifugal loads in operation. These parts can be held together by a retainer, which can be received in a cutout provided in the end supports and the filler.

Abstract: A thermal barrier coating material formed of a highly defective cubic matrix structure having a concentration of a stabilizer sufficiently high that the oxygen vacancies created by the stabilizer interact within the matrix to form multi-vacancies, thereby improving the sintering resistance of the material. The concentration of stabilizer within the cubic matrix structure is greater than that concentration of stabilizer necessary to give the matrix a peak ionic conductivity value. The concentration of stabilizer may be at least 30 wt. %. Embodiments include a cubic matrix of zirconia stabilized by at least 30-50 wt. % yttria, and a cubic matrix of hafnia stabilized by at least 30-50 wt. % gadolinia.

Abstract: The present invention increases the life of a pole crossover while minimizing the need for timely inspections and costly replacements. The present invention splits the pole crossover band 4 at one or more locations along its circumference and then joins the multiple arcs with a flexible member 10, such as an omega shaped bow. As deflection related stresses 8 increase, the circumference of the pole crossover band, the flexible member 10 allows for a natural expansion point in the otherwise rigid material. This relieves stresses that would otherwise be transferred to the connection point 6 between the pole crossover and the generator windings that can cause cracking and eventually generator failure.

Abstract: A sealing system for reducing a gap between a tip of a shrouded turbine blade and a stationary shroud of a turbine engine. The sealing system includes one or more seal lands extending from a shrouded turbine blade toward a stationary shroud of a turbine engine. During operation of the turbine engine, the seal lands straighten and extend towards the stationary shroud of the turbine engine, thereby reducing the leakage of air past the shrouded turbine blades and increasing the efficiency of the turbine engine. The sealing system may also include one or more protrusions extending from the stationary shroud towards the tips of the shrouded turbine blades.