Abstract: Aspects of the invention relate to a system for assessing the condition of a thermal barrier coating on a turbine vane during engine operation. According to embodiments of the invention, one or more wires can be passed along the airfoil portion of the vane. The wires can extend over, within, or beneath the thermal coating. An electrical current can be passed along the wires, and electrical resistance can be measured across the wires. Thus, if a portion of the thermal coating becomes damaged, then the wires located in that area may break. A disconnect in the wires can lead to an increase in resistance across the wires, which can alert an operator to a problem. Some assessment systems can provide a general indication of the magnitude of damage and whether the damage is spreading.

Abstract: A seal usable to seal a transition in a can-annular combustion system of a turbine engine to a turbine vane assembly to direct exhaust gases through the turbine vane assembly. The seal may be formed from an elongated body extending along an outer edge of the transition and having first and second edges. The first edge of the seal may be attached to the transition, and the elongated body may extend away from the transition edge and contact a portion of the turbine vane assembly. The elongated body may flex during use without yielding or otherwise deforming.

Abstract: A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperating interlock features (30, 32) formed on the lamella and on the support structure respectively. Mating load-transferring surfaces (34, 36) of the interlock features are disposed in a plane (44) oblique to local axes of thermal growth (38, 40) in order to accommodate differential thermal expansion there between with delta alpha zero expansion (DAZE). Reinforcing fibers (62) within the CMC material may be oriented in a direction optimized to resist forces being transferred through the interlock features. Individual lamellae may all have the same structure or different interlock feature shapes and/or locations may be used in different groups of the lamellae. Applications for this invention include an airfoil assembly (10) and a ring segment assembly (82).

Abstract: A dynamoelectric machine 30 includes a rotor 32 and a stator 34 surrounding the rotor. The dynamoelectric machine 30 further includes a generator housing 36 surrounding both the rotor 32 and the stator 34. Additionally, the dynamoelectric machine 30 includes at least one blower 39a, 39b for generating a cooling gas flow 38 within the generator housing 36 to cool the stator 34 and the rotor 32. The dynamoelectric machine 30 includes at least one arcuate heat exchanger 40a, 40b, 80a, 80b within the generator housing 36 for extracting heat from the cooling gas flow 38.

Abstract: A stacked ceramic matrix composite lamellate assembly (10) including shear force bearing structures (48) for resisting relative sliding movement between adjacent lamellae. The shear force bearing structures may take the form of a cross-lamellar stitch (50), a shear pin (62), a warp (90) in the lamellae, a tongue (104) and groove (98) structure, or an inter-lamellar sealing member (112), in various embodiments. Each shear force bearing structure secures a subset of the lamellae, with at least one lamella being common between adjacent subsets in order to secure the entire assembly.

Abstract: A generator includes a shaft and rotor body defining poles and a winding positioned around the shaft on the rotor body. A rotor pole crossover is aligned to the shaft and connects ends of the winding between adjacent poles. The rotor pole crossover includes a body member having a curved medial section and opposing legs extending outwardly from the curved medial section that connect to the ends of the winding. The curved medial section has at least one slot formed therein to add flexibility to the rotor pole crossover.

Abstract: A heating system for a turbine engine air intake region for preventing the formation of ice on the air intake region, which may be formed from the bell-mouth, one or more vanes, such as inlet guide vanes, a turbine blade assembly formed from one or more blades, such as the first row of rotating blades, and related components. A heat source may be attached to the inlet manifold and positioned to emit thermal radiation toward the air intake region to prevent the formation of ice thereon.

Abstract: A method of operating a combustor (10), to provide intimately mixed hot combusted gas (44) for a gas turbine (46), includes feeding gaseous oxidant (12) and gaseous fuel (16) into the combustor (10) near a combustion flame (28) which has a tip end (39) and a root end (29), where corona discharge occurs through adjustment of an electric field (34), and where the corona discharge causes ionized particles (36) to form and also causes intimate turbulent mixing of the gases.

Abstract: An electrical power generating apparatus (20) may include a housing (22), an electrical generator (24) within the housing, and a step-up transformer (30) within the housing and connected to the electrical generator. A turbine (26) may be provided exterior the housing (22) to drive the electrical generator (24). A barrier wall (38) may be provided within the housing and (22) between the electrical generator (24) and the step-up transformer (30), and a fire extinguishing system (40) may be installed within the housing (22). The step-up transformer (30) may be connected to the electrical generator (24) without use of an isolated phase bus.

Abstract: The claimed invention is a method for determining a relationship between a metal temperature of a turbine component and an operating condition of a turbine housing the component. The claimed invention is also a method for determining consumed operating life for a turbine component. The invention further comprises a system for determining an amount of remaining useful life in a turbine component. The invention further comprises a method for determining a relationship between a stress state of a turbine component and an operating condition of a turbine housing the component.

Abstract: The present invention provides for thin sheet wedges that comprise a mica matrix impregnated with a conductive resin. The mica matrix is composed of mica flakes. The thin sheet wedge has a semi-conductive property of 500–500,000 ohms per square. In one embodiment the thin sheet wedge further comprises at least one glass fiber layer. In a particular embodiment the glass fiber layer is a backing for the mica matrix. In another particular embodiment the glass fiber is interwoven with the mica matrix. The glass fiber layer may itself be impregnated with a conductive resin.

Abstract: A mount is for installing a probe, such as for example, a search coil, in a variety of locations and orientations within an electrical generator, without requiring the rotor of the generator to be removed. The mount includes a block having a longitudinal hole and a plurality of transverse slots intersecting the hole. A plurality of wedges are disposed within the slots. A wedge pin inserted into the longitudinal hole engages the wedges forcing the wedges outward in order to secure the mount and search coil thereon in the desired position within the generator, such as for example, in the air gap between the rotor and stator. A fastening mechanism further secures the mount in place.

Abstract: Aspects of the invention relate to a system for attaching a ceramic liner to a non-ceramic combustor head-end component while accommodating different rates of thermal expansion of these components. One end of the liner can be received within a slot formed by the combustor head-end component. The liner can be held in place by a plurality of pins with each pin passing through a pair of aligned openings in the liner and the head-end component. The end of the liner can be spaced from each of the walls of the slot so as to form a series of gaps in fluid communication. The gaps and the pins can accommodate differential thermal expansion between the liner and combustor head-end component. If desired, at least some of the gaps can be tightly controlled so as to regulate air leakage around the end of the liner.

Abstract: Embodiments of the invention relate to a system and method for controlling the size of gaps in a turbine engine. In many instances, it is desirable to minimize the size of the gaps between neighboring rotating and stationary components in a turbine engine, such as between a disc cover plate and a proximate pre-swirler. According to embodiments of the invention, each component can be provided with a sealing surface. The sealing surfaces can be angled relative to the axis of rotation. The sealing surfaces are spaced from each other so as to form a gap therebetween. The sealing surfaces may or may not be substantially parallel. As a result of such configuration, the size of the gap can be controlled by axial and radial movement of the components. For example, the gap between the cover plate and the pre-swirler can be adjusted by axially movement of the rotor.

Abstract: An inspection system formed at least from a viewing tube for inspecting aspects of a turbine engine during operation of the turbine engine. An outer housing of the viewing tube may be positioned within a turbine engine using at least one bearing configured to fit into an indentation of a support housing to form a ball and socket joint enabling the viewing tube to move during operation as a result of vibrations and other movements. The viewing tube may also include one or more lenses positioned within the viewing tube for viewing the turbine components. The lenses may be kept free of contamination by maintaining a higher pressure in the viewing tube than a pressure outside of the viewing tube and enabling gases to pass through an aperture in a cap at a viewing end of the viewing tube.

Abstract: In some instances, ice can form on the surface of a compressor airfoil. If the ice dislodges, it can impact and damage other compressor components. Aspects of the invention relate to systems for detecting the presence of ice or water on a compressor vane during engine operation. A ceramic insulating coating can be deposited on a portion of the surface of the vane. A heater and a thermocouple can be provided near the outermost surface of the coating such that the thermocouple can sense heat from the heater. The heater and the thermocouple can be provided within the coating. The presence of water film and/or ice on the coating surface can be detected by taking a thermocouple measurement following a heater pulse. The presence of a water film or ice results in a delay in the temperature rise detected by the thermocouple.

Abstract: A method of operating a fuel cell including an anode, a cathode, a first passage, and a second passage, wherein the anode is disposed in the first passage and the cathode in the second passage including producing a non-explosive gaseous feed consisting of (i) at least one oxidizable component having a greater tendency to undergo oxidation relative to the anode, and (ii) a remainder which is the predominant component in the gaseous feed consisting essentially of water vapor; and introducing the non-explosive gaseous feed to the first passage to form a first gaseous feed stream flowing through the first passage when the anode realizes a temperature effective to facilitate deteriorative oxidation of the anode in the presence of an oxidizing agent. The non-explosive gaseous feed is provided to mitigate or prevent anode oxidation and the formation of potentially explosive gaseous mixtures.

Abstract: The present invention facilitates keeping the slot cells 8 of a generator rotor from migrating during operation of the rotor. The present invention utilizes a slot cell catch 10 that hold slot cells 8, both U-shaped and L-shaped, in position within a rotor body slot 6. The catch 10 limits movement to a pre-determined amount, usually only a fraction of an inch.

Abstract: A tooling system including a workstation assembly and a toolkit, is for performing an operation on a valve assembly. The workstation assembly includes a base platform; upright members extending generally vertically therefrom; an adjustable valve seat assembly coupled thereto for adjusting the height and alignment of the valve assembly being worked on; a stabilizing assembly for further aligning and securing the valve assembly; and a clamping assembly for engaging and securing the valve assembly once it is aligned, in order to permit the operation to be quickly and easily performed on the aligned, secured valve assembly. A method of use is also disclosed.

Abstract: The present invention provides for an insulating boot 20 for ends of through-bolts 12 in electric generators that comprises a shaped insulating boot. The boot has an inner surface and an outer surface and an opening, where the inner surface is substantially free of protrusions. The inner surface of the shaped boot 20 is within 0.01 to 0.5 inches (0.025–1.3 cm) larger than the shape of the end of a through-bolt 12 to which the shaped boot will be applied. The shaped insulating boot has a breakdown voltage of at least 10 kV, and more particularly at least 30 kV, and the shaped boot is placed over the end of a through-bolt of an electric generator.