Abstract: A method for maintaining a system consisting of a plurality of components, comprises the steps of collecting maintenance information for each component of the system for which maintenance information is available; providing a maintenance schedule for components of the system; operating the system; and maintaining the system wherein during scheduled maintenance of a component information about the status of that component is acquired, during a failure of a component information about the failure of that component is acquired, and modifying the maintenance schedule according to the acquired information.

Abstract: A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section includes at least one first opening and at least one second opening. The compressor assembly is located in the compressor section to define with the compressor section a compressor apparatus to compress air. The at least one combustor assembly is coupled to the combustor section to define with the combustor section a combustor apparatus. The turbine assembly is located in the turbine section to define with the turbine section a turbine apparatus.

Abstract: A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane.

Abstract: This document discusses, among other things, systems, devices, and methods of disabling an automatic generator starting (AGS) actuator, such as used with a fuel-powered AC power generator providing AC electrical power to a recreational vehicle (RV) or other vehicle. The AGS actuator is disabled in response to a fault condition, such as may be indicative of a risk of hazardous gas, such as carbon monoxide (CO) accumulating near the vehicle, potentially in an enclosed area. After such disabling is performed, the vehicle driver would then have to consciously re-engage the AGS actuator. Factors useful for determining whether the fault condition exist include, among other things, transmission position, wheel rotation, vehicle engine operation status, ignition status, and/or an exhaust gas sensor.

Abstract: A multi-stage selective catalytic reduction (SCR) unit (32) provides efficient reduction of NOx and other pollutants from about 50-550° C. in a power plant (19). Hydrogen (24) and ammonia (29) are variably supplied to the SCR unit depending on temperature. An upstream portion (34) of the SCR unit catalyzes NOx+NH3 reactions above about 200° C. A downstream portion (36) catalyzes NOx+H2 reactions below about 260° C., and catalyzes oxidation of NH3, CO, and VOCs with oxygen in the exhaust above about 200° C., efficiently removing NOx and other pollutants over a range of conditions with low slippage of NH3. An ammonia synthesis unit (28) may be connected to the SCR unit to provide NH3 as needed, avoiding transport and storage of ammonia or urea at the site. A carbonaceous gasification plant (18) on site may supply hydrogen and nitrogen to the ammonia synthesis unit, and hydrogen to the SCR unit.

Abstract: A cooling system for a turbine blade of a turbine engine having multiple serpentine trailing edge cooling channels in parallel. The serpentine cooling channels are positioned proximate to a trailing edge of the turbine blade and facilitate increased heat removal with less cooling fluid flow, thereby resulting in increased cooling system efficiency.

Abstract: Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restart or spin cool, it may be desirable to heat the vane carrier to enlarge or at least prevent a decrease in compressor clearances. In such cases, a heated thermal fluid can be provided by reclaiming residual exhaust energy from a heat recovery steam generator. At any condition where improved performance is desired, such as at base load operation, the vane carrier can be cooled to minimize compressor clearances. A cooled thermal fluid can be bleed air from an upstream portion of the compressor, water-cooled high pressure bleed air from a downstream portion of the compressor, or feed water from the bottoming cycle in a combined cycle engine.

Abstract: A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that may be produced from internal or external pressurization of the airfoil without incurring any substantial thermal stress. The stiffener is disposed on a CMC wall and generally extends along a chord length of the airfoil.

Abstract: A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.

Abstract: A method of repairing a generator blower hub assembly (12) and rotor blade (10) removed from the generator blower hub assembly (12) where the rotor blade (10) has fatigued material in threads of a threaded blade root (14). The method may include removing (32) at least a portion of the fatigued material to form the blade root (14) to a first or new diameter. Threads may be formed (36) on the diameter of the blade root (14) using a roll forming process. A collar (20) may be secured within a threaded hole (16) formed in the generator blower hub assembly (12) where the collar (20) includes internal threads (35) for receiving the threads formed on the diameter of the blade root (14), which may be threaded into the collar (20). Collar (20) may be fabricated of steel alloy and include relief groove (40) for improving the fatigue resistance of the threaded blade root (14) when reassembled into the generator blower hub assembly (12).

Abstract: A combustion turbine power plant (10) incorporating a desiccating scrubber (140) for simultaneously removing water and sulfur from a flue gas (20) of the power plant (10). The desiccating scrubber (140) may include an inlet nozzle (145) for spraying an aqueous solution (142) containing a desiccant and a base into flue gas (20) so the aqueous solution (142) makes direct contact with flue gas (20). A filter (162) may be provided to collect sulfur compounds downstream of the desiccating scrubber (140) and a regenerator (164) may be provided for recovering water. A controller (148) may control a base supply (170) and a desiccant supply (172) to regulate the respective amounts of each introduced into the aqueous solution (142). Controller (148) may be responsive to sensors (142) measuring the water and sulfur content of flue gas (20) exhausted to atmosphere (144). The desiccating scrubber (140) may include a demister (160) to entrain carryover droplets from a sprayed aqueous solution (142).

Abstract: A method of stress relief for stainless steel combustion turbine components includes vibrating the components during welding at a subharmonic frequency. The proper frequency is selected to be below a harmonic frequency, and to produce an amplitude in the range of ¼ to ½ the amplitude produced by a harmonic frequency. The component to be repaired is vibrated during and after welding at this frequency.

Abstract: A seal assembly is provided to prevent leakage of cooling fluid from a generator housing. A bracket 26 includes an inlet connectable to power plant piping for receiving a supply of sealing fluid. The inlet is in communication with a bracket passageway 32 for admitting the sealing fluid in a radially inner section of the bracket. A sealing cartridge 28 is mountable in an annulus defined by the bracket. The sealing cartridge includes at least one cartridge passageway 44 in communication with the bracket passageway for admitting the supply of sealing fluid and passing the supply of sealing fluid to establish a sealing boundary about the rotor shaft. At least one of the bracket or the sealing cartridge includes a first sealing fluid-distribution channel 30 extending along a radial direction for providing fluid communication between the bracket passageway and the at least one passageway in the sealing cartridge.

Abstract: An online method, system, and computer-readable code for remotely monitoring radiant energy emitted from a turbine blade (106), which may be undergoing an incipient degradation, such as a crack, in a relatively low-temperature, and saturated steam environment of the low pressure stage of a steam turbine. The method and system provide sufficient temporal and spatial resolution to obtain high quality infrared images of the blade areas of interest enabling the system to identify the crack at any of those areas of the blade prior to such a crack growing to a critical length.

Abstract: A phased array ultrasonic testing system is for examining turbine disc bores and blade attachments for discontinuities, such as stress corrosion cracking. The system is particularly suited to perform an accurate and efficient inspection of components despite their having a relatively complex geometry, such as axial entry blade attachments and bores of associated discs. The system includes a control system with a computer and a controller for programming, emitting, and steering an ultrasonic beam via at least one two-dimensional phased array probe, thereby precisely inspecting the area of interest while simultaneously accommodating the aforementioned complex geometry of the disc or blade attachment. Computer control of the beam permits the number of inspection locations and the number of different probe wedges to be reduced providing for an efficient, timely inspection. Methods of profiling and examining turbine components of known and unknown geometries, are also disclosed.

Abstract: High voltage coils (40) having an insulated coil surface that includes a composite tape (32) bonded to a secondary conductive layer (34) in a half lap manner. The composite layer comprising a glass conductive tape bonded to a layer of mica paper tape in an edge lap manner.

Abstract: An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may be shortened relative to conventional clips and may include a cooling channel proximate to a point of attachment to the combustor basket.

Abstract: A gas turbine combustor (23) includes a catalytic combustion stage (22) receiving a first portion (18) of a total oxidizer flow (16) and a first portion (30) of a total fuel flow (29) and discharging a partially oxidized fuel/oxidizer mixture (40) into a post catalytic combustion stage (24) defined by a combustion liner (58). The combustor further includes an injector scoop (54) having an injector scoop inlet (56) in fluid communication with an opening (56) in the combustion liner for receiving a second portion (20) of the oxidizer flow. A fuel outlet (e.g. 64) selectively supplies a second portion (42) of the total fuel flow into the second portion of the oxidizer flow.

Abstract: A method and system for directly measuring the compression of a ripple spring (23) in a dynamoelectric machine through a corresponding wedge (27). A compression-assessment tool (3) is provided that includes a carriage (32) for supporting a proximity sensor (34). The carriage (32) enables the proximity sensor (34) to be passed over the length of the ripple spring (23), which produces an output signal that is representative of the compression of the ripple spring (23).

Abstract: A braze material (10) including nano-sized filler material particles (14). The nano-sized particles will melt at a temperature significantly lower than the micron-sized particles used in prior art braze materials, thereby eliminating or reducing the need for the addition of temperature depressant materials such as boron or silicon. The resulting braze joint is substantially free of detrimental boride and suicides phases, thereby improving the material properties of the joint, eliminating the need for a separate post-braze diffusion heat treatment, and permitting a subsequent welding operation with reduced risk of cracking. The braze heat treatment may also function as a solution heat treatment, a pre-weld heat treatment or a post-weld heat treatment.