Abstract: A seal for sealing a seal groove in a shroud of a turbine vane. The seal may include a cooling system configured to pass cooling fluids through a cooling fluid supply port in a shroud, through a cooling system in which the cooling fluids contact the shroud and the seal, and exhaust the fluids through a gap between adjacent turbine vanes. The seal may include an elongated cooling channel for channeling cooling fluids from a supply to an exhaust channel at a first end. The cooling system may remove heat from the turbine vane shroud, the seal, and other related components, thereby reducing the likelihood of premature failure.

Abstract: A platform cooling system usable in a turbine engine together with an airfoil for preheating cooling fluids before the cooling fluids enter a cooling system in the airfoil in a turbine engine. The platform cooling system includes cooling channels in either the ID or OD platforms, or both, of the airfoil. The channels transfer heat to the cooling fluids flowing through the platform cooling system and thereby heat the cooling fluids. The preheated cooling fluids are particularly useful with cooling composite ceramic airfoils, which are susceptible to damage from large temperature gradients developed between combustion gases outside the airfoil and cooling fluids inside the airfoil. The platform cooling system may be combined with an airfoil cooling system to create a serial cooling system in which cooling fluids may enter the platform and flow through the platform and airfoil without being supplemented with additional cooling fluids along the flow path.

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one cooling channel. The cooling channel may be a serpentine cooling channel with a flow guide extending from a first turn to a second turn of the cooling channel and formed from a first turn section, a second turn section, and a body coupling the first and second turn sections together. The flow guide substantially eliminates separation of cooling fluid flow in the tip region of the cooling channel, thereby increasing heat transfer. In at least one embodiment, the flow guide extends from a first turn in the cooling channel proximate to the blade tip to a second turn proximate to a root of the blade.

Abstract: Apparatus for applying torsional vibration to a rotating machine is provided. In one exemplary embodiment the apparatus includes a permanent magnet machine (12) connected to the rotating machine (22) and configured to generate a three-phase AC output voltage. A converter (36) may be coupled to receive the three-phase AC output voltage from the permanent magnet machine to supply a DC load current. An electrical load (44) (or exciter) may be coupled to the converter to receive the load current. An oscillator (42) is connected to the converter to provide an oscillation signal for modulating the load current from the converter. Modulated load current causes variable loading of the permanent magnet machine thereby creating an oscillatory torque in the permanent magnet machine (12). The oscillatory torque causes torsional vibration in the rotating machine. Various components of the apparatus for applying torsional vibration may be part of a field-deployed power generating system.

Abstract: Aspects of the invention related to a system for providing advance notice of impending contact between a stationary component and a rotating component in a turbine engine. For example, the system can be used to warn of potential contact between a seal holder and a rotor disk in the compressor section of the engine. In one embodiment, a pad or other component can be provided on the stationary seal holder. If the seal holder and the rotor disk approach each other during operation, the pad can contact the rotor disk prior to actual contact between the seal holder and the rotor disk. An optical and/or an acoustic signal can be generated by such contact. The signals can be detected remotely from the point of contact by a signal detection device, thereby avoiding the need to pass wires through the compressor section.

Abstract: The present invention facilitates the placement of laminations 10 onto keybars 6 of stator generators frames 2. Laminations need to be tightly fit onto keybars 6, however, the same need for tightness makes stacking laminations onto keybars particularly onerous. This is magnified when donuts, which are preassembled groups of laminations, are attempted to be stacked onto the keybars 6. The present invention provides for enlarged grooves 12 that more easily accept the keybars. This makes stacking laminations, both individually and in donuts, much easier. The laminations are then held in position by the insertion of a wedge 16. The wedge may be placed to disperse forces 20 transferred to the laminations in a circumferential manner 22.

Abstract: A gas turbine system (100) includes a compressor (110) for receiving air and producing compressor discharge air, a combustor (120) for combusting an oxygen comprising gas flow including the discharge air and a fuel into a hot gas flow, and a turbine expander (130) generating output power from the hot gas flow and providing a hot exhaust gas flow. An extractor (135) is provided for splitting the discharge air into a direct flow portion (121) which directly reaches the combustor (120) and an indirect flow portion (122). A mixing device (140) receives the indirect flow portion (122) and mixes it with a water flow (145), either in the form of water or steam, to produce a water enhanced indirect flow portion (150). A recuperative heat exchanger (155) heats the water enhanced indirect flow portion (150) using heat from at least a portion of the hot exhaust gas flow. The heated water enhanced indirect flow portion (158) is then reintroduced into the oxygen comprising gas flow.

Abstract: An automatic recovery pilot nozzle support system for supporting a pilot nozzle in a fuel injection system of a turbine engine. The support system includes a sleeve extending from an orifice in a support housing, wherein the sleeve has a hollow opening for containing a pilot nozzle. The sleeve may increase the natural frequency of the pilot nozzle above an excitation zone, thereby limiting destructive vibrations. The sleeve may be attached to the support housing with an interference fit. The automatic recovery aspect of the support system enables the sleeve to maintain an interference fit with the support housing such that anytime the sleeve looses contact with the support housing, an insulative film of air forms between the sleeve and the support housing. The insulative film of air causes the temperature of the sleeve to increase, and the sleeve to expand and reform the interference fit with the support housing.

Abstract: Embodiments of the invention relate to a turbine vane having a fail safe cooling system. According to embodiments of the invention, the vane can have multiple concentric layers of radial cooling holes extending about the vane; each layer being fluidly connected to the adjacent layer or layers. Such fluid communication can occur through one or more plenums in the vane or in the shrouds bounding the radial ends of the vane. Coolant can initially be supplied to the innermost layer of cooling holes. From there, the coolant can sequentially progress through successive outer layers. Between two adjacent layers, the coolant can flow in opposite directions. Not only does such a system provide needed cooling to the vane, but the multilayer redundant cooling system can avoid or delay catastrophic failures that can occur if the vane surface is damaged, such as by impact.

Abstract: Aspects of the invention relate to a fixture and a method to assist in the alignment of the inlet end of a transition duct and a combustor component in a turbine engine. Among other things, the fixture can include a flange adapted for mounting to a combustor component, an elongated mandrel, and a plurality of radially extendable jaws. After mounting the fixture to a combustor component, the jaws can engage an inner peripheral surface of a transition so as to properly align the transition with a target axis of alignment. The fixture can be configured to measure the size of any shims needed at the base of the flexible support bracket. Further, the fixture can also include various gauges to validate the alignment of the inlet end of the transition.

Abstract: Ceramic tile (32) insulation for protecting a substrate material (34) in a high temperature environment. A plurality of ceramic tiles (78) may be used in combination with a monolithic layer of ceramic insulation (80) to protect a fillet region (76) and an airfoil section (80), respectively, of a gas turbine vane (72). Individual ceramic tiles (84) may be applied to repair a damaged area of the monolithic insulating layer. Ceramic tile insulation may be applied in two layers (56, 58) with the material properties of the two layers being different, and with the gaps (38) of the two layers being misaligned.

Abstract: A resonator for damping pressure waves or instabilities in a system supported by acoustic energy wherein the resonator adopts the use of counter-bored openings on the downstream side of the resonator within the flow path of the system. The resonator includes a first member and a second member where the second member includes a plurality of openings therethrough with each hole having a counter-bore on its upstream side. The first member has a size substantially smaller than the diameter of said flow path and a first plurality of openings therethrough. The openings are in fluid communication with the flow path. The second member has a size generally equal to the first member and a second plurality of openings therethrough, which openings are in fluid communication with the flow path.

Abstract: The exhaust gas of a turbine engine can include water vapor. Aspects of the invention relate to various systems for recovering water from the exhaust gas of a gas turbine engine. In one system, a portion of the exhaust gas can be routed to an absorption chiller. In another system, a portion of the exhaust gas can be routed to a direct contact heat exchanger. In a third system, a portion of the exhaust gas can be routed to a fin-fan cooler. In each of these systems, the portion of gas can be cooled below its dew point temperature to release a portion of its humidity as liquid water. Aspects of the invention can be used with the turbine exhaust of simple and combined cycle power plants. A water recovery system according to aspects of the invention can minimize or eliminate a power plant's dependence on local water sources.

Abstract: A turbine blade for a turbine engine having a leading edge cooling system formed from a suction side cooling channel and a pressure side cooling channel. Cooling fluids flow into the leading edge cooling channels through impingement orifices that meter cooling fluid flow. The cooling fluids may form vortices in the cooling channels before being released from the turbine blade through gill holes. The cooling fluids then form a boundary layer of film cooling fluids on an outer surface of the turbine blade.

Abstract: A turbine blade for a turbine engine having a cooling system formed from one or more cooling channels having a plurality of mini channels. The cooling system may include first ribs forming a first passageway of mini channels in which the cross-sectional area of the cooling channel is reduced, thereby increasing the velocity of the cooling fluids and the internal heat transfer coefficient. The cooling system may also include second ribs forming a second passageway downstream from the first passageway a distance sufficient to prevent the formation of a fully developed boundary layer and allow the cooling fluids to fully expand after exiting the first passageway. The cooling channel may also include a plurality of protrusions extending from surfaces forming the cooling channel to create turbulence and prevent formation of a fully developed boundary layer.

Abstract: A turbine blade for a turbine engine having a platform cooling system formed from one or more platform cooling channels extending from an inner cooling cavity in a root of a turbine blade to an outer surface of a platform on the turbine blade. The platform cooling channels may be positioned in ribs protruding from a bottom surface of the platform. The ribs act as fins during operation of a turbine engine in which the turbine blade is installed by increasing surface area of the platform and thereby increasing convection on the bottom surface.

Abstract: The present invention relates to monitoring the corrosive damage caused to items in a corrosive environment by using multiple monitored coupons 30 of varying thickness that, when corroded, transmit information to a monitor 40 allowing a user to estimate the corrosive damage valuable industrial components 20. The corrosion rate of the coupons 30 can be used to optimize the environmental conditions, so that items in the environment corrode at desired rates.

Abstract: A tool for sensor management and fault visualization in machine condition monitoring. The method and system are able to monitor a plurality of sensors at one time. The sensors may be used in a power plant system monitoring system. The method and system may display a fault status for each sensor in the plurality of sensors in a single display, wherein the fault status for each sensor is displayed over time. The method and system also provide a mechanism that permits a user to examine details of each sensor in the plurality of sensors at any given time. In addition, the method and system are capable of categorizing each fault in the fault status using one or more properties or categorizing criteria. The method and system also permit sensors to be tested such that different operating models may be examined by utilizing different sensors.

Abstract: A composite material (10) formed of a ceramic matrix composite (CMC) material (12) protected by a ceramic insulating material (14). The constituent parts of the insulating material are selected to avoid degradation of the CMC material when the two layers are co-processed. The CMC material is processed to a predetermined state of shrinkage before wet insulating material is applied against the CMC material. The two materials are then co-fired together, with the relative amount of shrinkage between the two materials during the firing step being affected by the amount of pre-shrinkage of the CMC material during the bisque firing step. The shrinkage of the two materials during the co-firing step may be matched to minimize shrinkage stresses, or a predetermined amount of prestress between the materials may be achieved. An aluminum hydroxyl chloride binder material (24) may be used in the insulating material in order to avoid degradation of the fabric (28) of the CMC material during the co-firing step.

Abstract: A replaceable section (25) of force-cooling tubing assembly (21, 22) for attachment to a transition piece (5) of a gas turbine is comprised of two ends (54, 70) fashioned for attachment by removable unions (52) to adjoining parts of a force-cooling tubing assembly. When assembled thereto to complete the assembly, the replaceable section 25 provides for fluid communication between a manifold (3) and the transition piece (5) for either the supply or return of cooling fluid. A transition piece (5) in combination with two such assemblies, one a supply assembly (21), the other a return assembly (22), comprises a field-installable transition piece assembly (10) that provides for rapid and easy installation.