Abstract: A fuel system for a turbine engine for reducing CO emissions caused during fuel staging processes while the turbine engine operates at reduced loads. The fuel system may include a first premix injector assembly and a second premix injector assembly, each formed from one or more injectors. In at least one embodiment, the first premix injector includes four injectors assembled into two pairs, and the second premix injector includes four injectors assembled into two pairs. The two pairs of the second premix injector assembly may be positioned between the two pairs forming the first premix injector assembly, thereby reducing the interface between fueled and unfueled areas, which reduces CO emissions.

Abstract: The present invention provides a flange-mounted condition monitor (30) that can be mounted to an access flange (21) on an access opening (20) on the housing (13) of a generator (10). The condition monitor (30) forms an integral part of the generator (10) and eliminates the need for complex systems of pipes and valves for transferring hydrogen samples from the generator (10) to the condition monitor (30). The flange-mounted condition monitor (30) provides greater sensitivity to overheat conditions, significantly reducing the risk of dangerous hydrogen leaks and eliminating costs associated with installing and maintaining a remote condition monitor and also reducing or eliminating the false alarms associated with water that collects in the piping of a remote condition monitor.

Abstract: A system (10) for imaging a combustion turbine engine airfoil includes a camera (12) and a positioner (24). The positioner may be controlled to dispose the camera within an inner turbine casing of the engine at a first position for acquiring a first image. The camera may then be moved to a second position for acquiring a second image. A storage device (30) stores the first and second images, and a processor (32) accesses the storage device to generate a composite image from the first and second images. For use when the airfoil is rotating, the system may also include a sensor (40) for generating a position signal (41) responsive to a detected angular position of an airfoil. The system may further include a trigger device (42), responsive to the position signal, for triggering the camera to acquire an image when the airfoil is proximate the camera.

Abstract: The present invention comprises a polymeric epoxy patching resin containing metal intercalated AlSiO structures. The AlSiO structures are typically nanoclays, and the preferred metals are Cr, Sn and Zn, and mixtures thereof. The patching resin is applied to damaged mica tapes, where the metal intercalated nanoclays penetrate the damaged area, leaving a homogenous patch. The present invention may also be used to thicken an area of insulating tape.

Abstract: A baffle system for routing cooling fluids through a dynamoelectric machine. The baffle system may include a locking cam mechanism for releaseably attaching a baffle to a stator assembly to substantially eliminate an annular air gap between a rotor assembly and a stator assembly. The baffle system may include a locking strip attached to a stator slot wedge to seal the locking cam mechanism and baffle to the stator assembly. In other embodiments, the baffle system may include a friction pad for sealing the locking cam mechanism and baffle to the stator assembly. The baffle system may also include a locking tool for simultaneously, or individually, moving the locking cam mechanism from an unlocked position to a locked position, or vice versa.

Abstract: A turbine vane assembly includes a turbine vane having first and second shrouds with an elongated airfoil extending between. Each end of the airfoil transitions into a shroud at a respective junction. Each of the shrouds has a plurality of cooling passages, and the airfoil has a plurality of cooling passages extending between the first and second shrouds. A substantially flat inner plate and an outer plate are coupled to each of the first and second shrouds so as to form inner and outer plenums. Each inner plenum is defined between at least the junction and the substantially flat inner plate; each outer plenum is defined between at least the substantially flat inner plate and the outer plate. Each inner plenum is in fluid communication with a respective outer plenum through at least one of the cooling passages in the respective shroud.

Abstract: A plasma sprayed ceria-containing interlayer is provided. The interlayer has particular application in connection with a solid oxide fuel cell used within a power generation system. The fuel cell advantageously comprises an air electrode, a plasma sprayed interlayer disposed on at least a portion of the air electrode, a plasma sprayed electrolyte disposed on at least a portion of the interlayer, and a fuel electrode applied on at least a portion of the electrolyte.

Abstract: A composite structure (62) having a bond enhancement member (76) extending across a bond joint (86) between a ceramic matrix composite (CMC) material (80) and a ceramic insulation material (82), and a method of fabricating such a structure. The bond enhancement member may extend completely through the CMC material to be partially embedded in a core material (84) bonded to the CMC material on an opposed side from the insulation material. A mold (26) formed of a fugitive material having particles (18) of a bond enhancement material may be used to form the CMC material. A two-piece mold (38, 46) may be used to drive a bond enhancement member partially into the CMC material. A compressible material (56) containing the bond enhancement member may be compressed between a hard tool (60) and the CMC material to drive a bond enhancement member partially into the CMC material.

Abstract: A method for making a material system includes the steps of: providing a chamber, placing hollow geometric shapes in the chamber, closing the chamber, evacuating air from the chamber, feeding a binder for the shapes into the evacuated chamber to impregnate the geometric shapes, drying the binder permeated geometric shapes, and heating the hollow shapes and binder to provide a unitary, sintered material system.

Abstract: Aspects of the invention relate to a turbine engine configuration and method for overcoming a turbine blade tip clearance problem that can arise when the turbine inlet temperature is maintained at a high level during part load operation of the turbine. Aspects of the invention relate to reducing rotor cooling air to a temperature below the design temperature level by using, for example, additional heat extraction devices or by reconfiguring or resizing existing heat exchanger devices. Upon exposure to the cooled air, the discs and blades of the turbine will shrink so as to provide a clearance between the blade tips and surrounding stationary support structure. The design rotor cooling air temperature can be from about 350 degrees Fahrenheit to about 480 degrees Fahrenheit. Aspects of the present invention can be used to decrease the rotor cooling air to about 150 degrees Fahrenheit at about 70 percent load.

Abstract: Aspects of the invention relate to a compressor system for a turbine engine that not only allows for larger compressor blade tip clearances as the engine passes through non-standard operating conditions, but also minimizes clearances during normal engine operation, thereby increasing efficiency of the compressor. The blade assembly can include an airfoil having a movable tip insert recessed within a pocket in the radially distal end of the airfoil. The tip insert can move radially outward from a predetermined recessed position to a predetermined extended position. An abutment surface can be provided within the pocket for engaging the tip insert and/or other associated components so as to limit the extension of the tip insert to the predetermined extended position such that the tip insert does not impinge on the stationary compressor structure and such that a spring operatively associated with the tip insert does not overextend its operational limits.

Abstract: A gas turbine engine combustor (26) including a primary combustion chamber (28), a mixer element (34), a mixing chamber (46) and a secondary combustion chamber (48). The primary combustion chamber receives a fuel oxidizer mixture flow (22) and discharges a partially oxidized mixture flow (32). The mixer element includes a plurality of flow channels (36, 38) for separating the partially oxidized mixture from a flow of an oxidizer (24) and producing a plurality of partially oxidized mixture flows interspersed with a plurality of oxidizer fluid flows. The mixer element may include a plurality of tubes (62) retained by an upstream tubesheet (70) and a downstream tubesheet (76). The mixer element may function as a heat exchanger to heat the oxidizer fluid flow and to cool the partially oxidized mixture flow upstream of the post-mixing chamber.

Abstract: A drop-in nozzle block (40) formed in two 180° segments (52) that can be simply lowered into position within the nozzle chamber casing of a steam turbine (42). An entire 180° segment can be lowered into position because an inner arcuate portion (58) of the nozzle block fits over and captures mating portions of the casing rather than having the casing capture the nozzle block as in the prior art. Elimination of a hook portion of the casing eliminates the necessity for the prior art procedure of rotating 90° segments into position through an arcuate-shaped slot. The drop-in installation allows closer tolerances to be maintained between the nozzle block and the casing, thereby eliminating the need for the expansion pins used in the prior art. The use of two 180° segments rather than the prior art 90° segments also eliminates the need for a dogleg joint between segments for turbines having eight steam inlet segments.

Abstract: A power plant (10) including a boiler unit portion (12) and a gas turbine unit portion (14) operable in multiple modes, including operation of the boiler unit portion independent of the gas turbine unit portion. Exhaust gas from the gas turbine is cooled in a heat recovery steam generator (HRSG) (52, 54) where steam is produced. The exhaust gas may also be provided to support combustion in a separately fueled boiler (16). The exhaust gas may be extracted from any location within or downstream of the HRSG. Steam produced in the HRSG and/or in the boiler may be supplied to a steam turbine unit (42, 44, 46). Dampers (60, 62, 74) are provided to selectively direct the gas turbine exhaust to the boiler or to bypass the boiler. An existing boiler fired steam power plant may be reconfigured to have the described arrangement.

Abstract: A blown fuse proximity sensing device 40 is for use with a rectifying wheel 37 of a type including rectifying diodes 38 and associated fuses 42. Each fuse 42 may include a housing 51, a fuse element 52 carried by the housing, and a pop-out indicator 54 movable between a normal position and a popped-out position. In the popped-out position, the indicator 54 extends outwardly from the housing responsive to failure of the fuse element. At least one stationary proximity sensor 44 is mounted adjacent the rectifying wheel 37 for sensing positions of the pop-out indicators 54 without contact therewith during rotation of the rectifying wheel to thereby sense at least one blown fuse. The sensing device 40 may also include a local display 61, and a controller 68 connected to the stationary proximity sensor 44 for generating an indication of a blown fuse on the local display. The controller 68 may also generate at least one remote output, such as to be monitored by other plant control equipment.

Abstract: A turbine vane usable in a turbine engine and having at least one cooling system. The cooling system including an aft cooling circuit formed from at least one serpentine cooling path. The serpentine cooling path having at least one rib may include bypass orifices for allowing air to pass through the rib to shorten the distance of the serpentine cooling path through which at least some of the air passes. The bypass orifices allow a greater quantity of air to pass through the vane and be expelled into a disc to which the vane is movably coupled as compared to a similar shaped and sized serpentine cooling path not having the bypass orifices.

Abstract: A turbine blade for a turbine engine having a cooling system in at least an outer wall. The cooling system in at least the outer wall formed from at least a first plurality of parallel cavities intersected by a second plurality of parallel cavities positioned in a nonparallel position relative to the first plurality of parallel cavities. In at least one embodiment, the second plurality of parallel cavities may include an alternating configuration of cavities, such that a first cavity may be positioned proximate to an inner surface of the outer wall and a second cavity adjacent to the first cavity is positioned proximate to the outer surface of the outer wall. The first cavity may also be offset from the second cavity to form a spiral gas flow path. The cooling system in the outer wall of the turbine blade may form a spiral flow path.

Abstract: In one embodiment the present invention is an MLB assembly 6 that is made up of two circular terminal conductor ends 2, 4. Multiple fins 10 radially extend from each of the two circular terminal conductor ends 2, 4, and each fin on each of the two circular terminal conductor ends has a matching fin on the other of the two circular terminal ends. Multiple flexible connectors 8 are attached to the fins 10 that electrically connects the terminal conductors 2, 4. The flexible connectors 8 also allow for a difference of movement between the two circular terminal ends. Current flowing through the MBL assembly 16 is evenly distributed 18 through the plurality of flexible connectors.

Abstract: A system (90) for measuring the gap (16) between a rotating blade (14) and a stationary component (12) of a turbo-machine, including an eddy current coil (30) and an eddy current tester (91). The eddy current tester may excite the coil in a pulsed eddy current testing mode. The coil is positioned in a stationary portion (12) of a turbo-machine traversed by a rotating blade and the eddy current tester is coupled to the eddy current coil to provide an indication responsive to a distance between the blade and the stationary portion as the blade traverses the position. The coil may be mounted in a frangible ceramic pill (70) movably disposed in a housing (74). The coil is positioned near the turbine blade, the coil is excited with a voltage step function (120), and the response (122) of the coil to the step function is detected and processed to determine the proximity of the blade.

Abstract: An abradable thermal barrier coating material (10) formed of a highly defective fluorite ceramic matrix (16) having a desired degree of porosity (18) created in part by the addition of a fugitive material (19). The ceramic material has 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. Such a concentration of stabilizer results in a material that is softer than prior art materials having lower concentrations of stabilizer, and that will be more resistive to sintering than prior art materials. Embodiments include a fluorite matrix of zirconia stabilized by at least 30 wt. % yttria, or stabilized by at least 30 wt. % ytterbia, and with porosity of 10-40%. In one embodiment, a metallic gas turbine seal ring segment is coated with a bond coat layer, then with a layer of porous 8 wt. % YSZ material, and finally with a layer of 33 mole % YbSZ (61.3 wt.