| SIEMENS ENERGY, INC. Patent applications |
| Patent application number | Title | Published |
|---|
| 20120128266 | Reconstruction of Phased Array Data - An image reconstruction method includes receiving volume data comprising a plurality of sampling points, determining a first conditioning of the sampling points suppressing low amplitudes and conserving maximum amplitudes, determining a second conditioning of the sampling points wherein an influence of a sampling point depends on its distance to a grid point in a sampling grid, determining a kernel comprising a plurality of weighting functions for the first conditioning and the second conditioning to determine an energy spread of each of the plurality of sampling points without determining a shape or size of the kernel, and outputting a reconstructed volume according to the energy spread of each of the plurality of sampling points. | 05-24-2012 |
| 20110109627 | Method and Apparatus for Three-Dimensional Visualization and Analysis for Automatic Non-Destructive Examination of a Solid Rotor using Ultrasonic Phased Array - A method and apparatus for three-dimensional visualization and analysis for automatic non-destructive examination of a solid Rotor using ultrasonic phased array is disclosed. Data is acquired by scanning a solid rotor with a phased array ultrasound transducer producing a plurality of two dimensional ultrasound scans. Each of a plurality of sample points of a plurality of two dimensional ultrasound scans are associated with a corresponding 3D image point of a regular grid. A kernel function for each of the plurality of sample points defining a size and shape of a kernel located at the corresponding image point is determined. A weight is assigned to each kernel which, in one embodiment, is based on the sample point value. A value for each image point of the regular 3D grid is determined based on kernels overlapping each image point. A three-dimensional volume representing the solid rotor is then visualized. | 05-12-2011 |
| 20100284822 | Turbine Airfoil with a Compliant Outer Wall - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation in the outer layer is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a support structure. The outer layer may be a compliant layer configured such that the outer layer may thermally expand and thereby reduce the stress within the outer layer. The outer layer may be formed from a nonplanar surface configured to thermally expand. In another embodiment, the outer layer may be planar and include a plurality of slots enabling unrestricted thermal expansion in a direction aligned with the outer layer. | 11-11-2010 |
| 20100284798 | Turbine Airfoil With Dual Wall Formed from Inner and Outer Layers Separated by a Compliant Structure - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a compliant structure. The compliant structure may be configured such that the outer layer may thermally expand without limitation by the inner layer. The compliant structure may be formed from a plurality of pedestals positioned generally parallel with each other. The pedestals may include a first foot attached to a first end of the pedestal and extending in a first direction aligned with the outer layer, and may include a second foot attached to a second end of the pedestal and extending in a second direction aligned with the inner layer. | 11-11-2010 |
| 20100279072 | Gussets for Strengthening CMC Fillet Radii - A ceramic matrix composite (CMC) structure ( | 11-04-2010 |
| 20100257860 | Air Vent in Main Steam Duct of Steam Turbine - A power plant including a steam turbine, and a steam turbine exhaust duct configured to deliver uncontaminated fluid from the steam turbine to downstream components of the power plant. The steam turbine exhaust duct includes a steam turbine exhaust duct isolation valve selectively configured to prevent fluid communication between the steam turbine exhaust duct and the downstream components of the power plant, and a steam turbine exhaust duct vent with a steam turbine exhaust duct vent valve. The steam turbine exhaust duct vent is configured to deliver contaminated fluid from the steam turbine exhaust duct to a fluid sink upon opening of the exhaust duct vent valve. | 10-14-2010 |
| 20100239432 | Turbine Vane for a Gas Turbine Engine Having Serpentine Cooling Channels Within the Inner Endwall - A turbine vane for a gas turbine engine having an internal cooling system in fluid communication with cooling channels positioned in the inner endwall is disclosed. The cooling system in the inner endwall may include cooling channels extending outwardly from the leading edge, trailing edge, pressure side and suction side toward the edges of the inner endwall. The cooling channels may be serpentine cooling channels and may be two or more serpentine cooling channels coupled together in series. The cooling channels may exhaust cooling fluids from the inner endwall through a plurality of orifices on an outer surface facing the opposing endwall and on the sides surfaces of the endwall. The pressure side and suction side midchord modulus serpentine flow circuits may receive cooling fluids from one pass of an internal midchord cooling channel and may exhaust those cooling fluids into another pass of the midchord cooling channel. | 09-23-2010 |
| 20100239431 | Turbine Airfoil Cooling System with Dual Serpentine Cooling Chambers - A cooling system for a turbine airfoil of a turbine engine having dual serpentine cooling channels, an inward serpentine cooling channel and an outward serpentine cooling channel, positioned within the airfoil. The inward serpentine cooling channel may receive cooling fluids from a cooling supply system through the root and exhaust cooling fluids to the outward serpentine cooling channel at the leading edge. The outward serpentine cooling channel may pass the cooling fluids through the outward portion of the serpentine cooling channel and exhaust the cooling fluids through the trailing edge of the airfoil. Such configuration yields a better creep capability for the blade. | 09-23-2010 |
| 20100226790 | TURBINE BLADE LEADING EDGE TIP COOLING SYSTEM - A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one leading edge cooling chamber for cooling the leading edge and for exhausting cooling fluids through a tip exhaust outlet. The leading edge cooling channel may include a second section that extends radially inward from the tip exhaust outlet and a first section that extends radially inward from the second section along the leading edge. The second section may be narrower than the first section and may direct cooling fluids to be exhausted from tip exhaust outlet skewed angle towards the suction side of the blade. As such, the leading edge cooling channel and tip exhaust outlet cooperate to exhaust the cooling fluids without forming a separation zone at the upstream side of the intersection between the leading edge cooling channel and the tip exhaust outlet. | 09-09-2010 |
| 20100226789 | TURBINE BLADE DUAL CHANNEL COOLING SYSTEM - A turbine blade having an internal cooling system with dual serpentine cooling channels in communication with tip cooling channels is disclosed. In at least one embodiment, the cooling system may include first and second tip cooling channels in communication with the first and second serpentine cooling channels, respectively. The first tip cooling channel may extend from the leading edge to the trailing edge and be formed from a first suction side tip cooling channel and a first pressure side tip cooling channel. The second tip cooling channel may extend from a midchord region toward the trailing edge and may be positioned between the pressure and suction sides such that the second tip cooling channel is positioned generally between the first suction side and pressure side tip cooling channels. The first and second tip cooling channels may exhaust cooling fluids through the trailing edge. | 09-09-2010 |
| 20100226788 | TURBINE BLADE WITH INCREMENTAL SERPENTINE COOLING CHANNELS BENEATH A THERMAL SKIN - A turbine blade having an internal cooling system with incremental serpentine cooling channels in near walls forming an outer surface of the turbine blade is disclosed. The turbine blade may be formed from an internal structural spar that is covered with a thermal skin. The incremental serpentine cooling channels may be cut into the outer surface of the spar to which the thermal skin may be attached. The incremental serpentine cooling channels may be formed from two or more serpentine cooling channels aligned along an axis that extends generally spanwise throughout the turbine blade. A row of incremental serpentine cooling channels may extend from a root to a tip of the blade, but a single incremental cooling channel does not. | 09-09-2010 |
| 20100226761 | Turbine Airfoil with an Internal Cooling System Having Enhanced Vortex Forming Turbulators - A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The cooling channel may also include a plurality of vortex enhancers protruding from an inner surface forming the cooling channel and positioned nonparallel to the turbulators. In one embodiment, the vortex enhancers may be positioned generally orthogonal to the turbulators. The configuration of turbulators and vortex enhancers creates a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demand and better turbine performance. | 09-09-2010 |
| 20100226755 | Turbine Vane for a Gas Turbine Engine Having Serpentine Cooling Channels Within the Outer Wall - A turbine vane for a gas turbine engine having an outer wall containing a plurality of serpentine cooling channels. The serpentine cooling channels may be configured to receive cooling fluids from internal cooling fluids supply channels. The serpentine cooling channels may be positioned in the pressure side and suction side outer walls and configured such that a first pass is positioned radially outward from an internal chamber a greater distance than a second pass. As such, cooling fluids are first passed proximate to an outer surface where the fluids are heated and then passed proximate to an inner surface, thereby establishing a smaller thermal gradient than typically found in conventional turbine blade outer walls. | 09-09-2010 |
| 20100199672 | Condenser System - A method of substantially preventing contaminants from entering a condenser adapted for use within a steam generating system. A condenser is provided. Steam or a combination of water and steam is passed into the condenser, the condenser operating in a normal mode a pressure in a control area is equal to or greater than a predefined pressure and in a non-normal mode if the pressure in the control area is less than the predefined pressure. An inert gas is injected into the condenser if a pressure in the control area is less than a holding pressure, the holding pressure being equal to or greater than the predefined pressure. | 08-12-2010 |
| 20100199671 | Deaerator Apparatus in a Superatmospheric Condenser System - A power generating system comprises a condenser and a deaerator apparatus. The condenser condenses a working fluid into a condensate and operates at an internal pressure above ambient pressure during a normal operating mode. The deaerator apparatus uses steam to remove contaminants from the condensate to bring the condensate to a desirable purity. The deaerator apparatus is deactivated during a typical operating state of the power generating system such that the condensate bypasses the deaerator apparatus. The deaerator apparatus is activated during a non-typical operating state of the power generating system such that the condensate passes into the deaerator apparatus wherein contaminants can be removed from the condensate. The typical operating state of the power generating system occurs when the condensate comprises a desirable purity and the non-typical operating state of the power generating system occurs when the condensate comprises an undesirable purity. | 08-12-2010 |
| 20100199670 | Power Generation Plant Having Inert Gas Deaerator and Associated Methods - A power generation plant includes a steam turbine and an electrical generator driven thereby. A condenser is downstream from the steam turbine. Moreover, the power generation plant includes a steam source and an inert gas source. A deaerator downstream from the condenser and is operable to perform deaeration using the inert gas source and is also selectively operable to perform deaeration using the steam source. | 08-12-2010 |
| 20100180605 | Structural Attachment System for Transition Duct Outlet - A structural attachment system for the outlet of a transition duct includes a structural attachment member that has a step over portion with an outer flange at one end thereof and an inner flange at the other end thereof. The step over portion can project away from the inner and outer flanges and can define an open area. The step over portion can have a cross-section that is generally u-shaped, v-shaped, c-shaped, semi-circular, semi-oval, parabolic, or bowed. A portion of the outlet of a transition duct is received within the step over portion of the structural attachment member. Because of such arrangement, the structural attachment member is not constrained circumferentially to fitting in between two neighboring transition ducts. The structural attachment member can manage the thermal displacements that can occur between the transitions, rotor shaft cover and first row of blades during transient engine operation. | 07-22-2010 |
| 20100110451 | Coating Evaluation Process - System and method for evaluating coating thickness variations along a turbine blade contour. In one embodiment, applied to a first region extending 360 degrees about the blade and to a second region including an exposed reference surface, the first region includes a first surface over which the coating is formed and a second surface formed by the coating. The system provides a source of structured light positionable to cast patterns suitable for determination of coordinate position information along the surfaces. One or more imaging cameras are positionable to acquire image data based on the light patterns. A computer system processes image information to (1) characterize the first and second surfaces with respect to a coordinate along the reference surface; (2) compare coordinate data corresponding to the first surface with coordinate data corresponding to the second surface; and (3) determine thickness of the coating as a function of position. | 05-06-2010 |
| 20100078202 | Printed Circuit Board for Harsh Environments - A printed circuit board (PCB | 04-01-2010 |
| 20100077760 | Flex-Fuel Injector for Gas Turbines - A fuel injector ( | 04-01-2010 |
| 20100077719 | Modular Transvane Assembly - An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each flow-directing structure includes a straight path and an annular chamber end, wherein the annular chamber ends together define an annular chamber for delivering the gas flow to the turbine first stage section, wherein gasses flow from respective combustors, through respective straight paths, and into the annular chamber as respective straight gas flows, and wherein the annular chamber is configured to unite the respective straight gas flows along respective shear planes to form a singular annular gas flow, and wherein the annular chamber is configured to impart circumferential motion to the singular annular gas flow before the singular annular gas flow exits the annular chamber to the first row of blades. | 04-01-2010 |
| 20100076703 | Method and Apparatus for Monitoring Blade Vibration With A Fiber Optic Ribbon Probe - A method and apparatus for monitoring blade vibrations in a turbine engine having blade tip target portions associated with blades. An illumination conduit including a plurality of optical fibers conveys light from a light source to a transmission end of the optical fibers where the light is focused to define an axially elongated projected image. The blade tip target portions pass through the projected image and reflect light to receptor ends of a plurality of optical fibers defining a detection conduit for conveying the reflected light to a processor. The transmission ends and receptor ends of the optical fibers are configured as a narrow rectangle to define a probe end for receiving reflected light at different axial locations along the probe end, and to detect blade passing events defined by passage of either or both a blade leading edge and a blade trailing edge. | 03-25-2010 |
| 20100075111 | Structure and Method for Forming Detailed Channels for Thin Walled Components Using Thermal Spraying - A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel. | 03-25-2010 |
| 20100074763 | Trailing Edge Cooling Slot Configuration for a Turbine Airfoil - A gas turbine engine hollow turbine airfoil having pressure and suction sidewalls extending chordwise between leading and the trailing edges. The trailing edge includes a pressure sidewall lip and a suction sidewall lip, and a breakout distance between the pressure sidewall lip and the suction sidewall lip. A cooling fluid channel extends spanwise through the airfoil for supplying a cooling fluid to the airfoil. Flow channels are provided extending chordwise between the cooling fluid channel and the suction sidewall lip and include a metering section, an internal diffusion section and a breakout slot. The interior diffusion section includes a spanwise dimension and a widthwise dimension perpendicular to the spanwise dimension, wherein the spanwise dimension continuously increases extending in the chordwise direction, and the widthwise dimension continuously decreases extending in the chordwise direction. | 03-25-2010 |
| 20100074762 | Trailing Edge Cooling for Turbine Blade Airfoil - A gas turbine engine hollow turbine airfoil having chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between the leading edge and the trailing edge. A trailing edge rib extends from the trailing edge toward the leading edge, and forms a solid member between the pressure and suction sidewalls. A cooling fluid channel extends in the spanwise direction through the airfoil adjacent to the trailing edge rib. A plurality of fluid chambers are formed in the trailing edge rib. Film cooling holes extend from the fluid chambers to the pressure and suction sidewalls, and trailing edge discharge holes extend from the fluid chambers to the trailing edge. A metering hole is associated with each of the fluid chambers to define a flow restriction connecting the cooling fluid channel to a respective fluid chamber. | 03-25-2010 |
| 20100074735 | Thermal Shield at Casing Joint - A thermal shield for reducing thermal stress induced proximate to a first joint formed between adjacent engine casing components in a gas turbine engine. The thermal shield includes a cover structure for covering a radially inner portion of at least one of the engine casing components. The cover structure is disposed proximate to the first joint and attached to the respective engine casing component so as to limit exposure of a covered inner portion of the engine casing component to hot gases in an interior volume defined by the engine casing components. A thermally insulating layer is disposed between the cover structure and the engine casing component for effecting a reduced amount of heat transfer to the covered inner portion of the engine casing component from the hot gases in the interior volume defined by the engine casing components. | 03-25-2010 |
| 20100074734 | Turbine Seal Assembly - A seal assembly that limits gas leakage from a hot gas path to one or more disc cavities in a turbine engine. The seal assembly includes a seal apparatus that limits gas leakage from the hot gas path to a respective one of the disc cavities. The seal apparatus comprises a plurality of blade members rotatable with a blade structure. The blade members are associated with the blade structure and extend toward adjacent stationary components. Each blade member includes a leading edge and a trailing edge, the leading edge of each blade member being located circumferentially in front of the blade member's corresponding trailing edge in a direction of rotation of the turbine rotor. The blade members are arranged such that a space having a component in a circumferential direction is defined between adjacent circumferentially spaced blade members. | 03-25-2010 |
| 20100074733 | Ingestion Resistant Seal Assembly - A seal assembly limits gas leakage from a hot gas path to one or more disc cavities in a gas turbine engine. The seal assembly includes a seal apparatus associated with a blade structure including a row of airfoils. The seal apparatus includes an annular inner shroud associated with adjacent stationary components, a wing member, and a first wing flange. The wing member extends axially from the blade structure toward the annular inner shroud. The first wing flange extends radially outwardly from the wing member toward the annular inner shroud. A plurality of regions including one or more recirculation zones are defined between the blade structure and the annular inner shroud that recirculate working gas therein back toward the hot gas path. | 03-25-2010 |
| 20100074729 | Compressible Ceramic Seal - A stack of substantially parallel ceramic plates ( | 03-25-2010 |
| 20100074727 | Method and Apparatus for Monitoring Blade Vibration With An Imaging Fiber Optic Ribbon Probe - A method and apparatus for monitoring blade vibrations in a turbine engine having blade tip target portions associated with blades. An illumination conduit including a plurality of optical fibers conveys light from a light source to a transmission end of the optical fibers where the light is focused to define an axially elongated projected image. The blade tip target portions pass through the projected image and reflect light to a receptor array defined by receptor ends of a plurality of optical fibers forming an imaging conduit for conveying the reflected light to a sensor array. An imaging end of the imaging conduit radiates an image onto the sensor array that is identical to the reflected light image received at the receptor array to track tangential and axial movement of a predetermined point on the target portion. | 03-25-2010 |
| 20100073008 | Partial Discharge Coupler for Application on High Voltage Generator Bus Works - A partial discharge coupler for detecting partial discharges in a conductor includes a frequency dependent network, a differential amplifier and a frequency selective coupling component. The frequency dependent network includes a first filter component, a fuse component and a load component, typically coupled together in series with reference to a first ground. The first filter component filters the high voltage, low frequency alternating current signal carried by the conductor from the load component and passes high frequency partial discharge pulse signals to the load component. The frequency selective coupling component couples in series between the differential amplifier and the load component. The output of the differential amplifier is configured to provide an output that is isolated from the ground connection for communicating detected partial discharge signals to partial discharge test equipment. | 03-25-2010 |
| 20100071382 | Gas Turbine Transition Duct - A transition member between a combustion section and a turbine section in a gas turbine engine. The transition member includes a casing inner wall and a plurality of spanning members. The spanning members extend radially outwardly from a radially outer surface of the casing inner wall. Each of the spanning members included a slot formed therein. Each slot is in communication with a first aperture formed in the radially inner surface of the casing inner wall and a plurality of second apertures formed in an aft side of the spanning member for effecting a passage of the cooling fluid from a first cooling fluid channel to an inner volume defined within the radially inner surface of the casing inner wall. The slots include a component in the radial direction and a component in the axial direction such that the first aperture is not radially aligned with the second apertures. | 03-25-2010 |
| 20100071376 | Combustor Assembly in a Gas Turbine Engine - A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct. | 03-25-2010 |
| 20100068068 | Turbine Airfoil Cooling System with Diffusion Film Cooling Hole Having Flow Restriction Rib - A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes first and second sections. The first section may function as a metering section, and the second section may function as a diffusion section. The second section may include flow restriction ribs that direct the flow of cooling fluids in disproportionately larger amounts proximate to the downstream side of the diffusion film cooling hole. | 03-18-2010 |
| 20100068067 | Turbine Airfoil Cooling System with Divergent Film Cooling Hole - A cooling system for a turbine airfoil of a turbine engine having at least one divergent film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The divergent film cooling hole includes a first section extending from an inner surface of the outer wall into the outer wall and a second section extending the first section and terminating at an outer surface of the outer wall. The divergent film cooling hole may provide a metering capability together with a divergent section that provides a larger film cooling hole breakout and footprint, which creates better film coverage and yields better cooling of the turbine airfoil. The divergent film cooling hole may provide a smooth transition, which allows the film cooling flow to diffuse better in the second section of the divergent film cooling hole. | 03-18-2010 |
| 20100068033 | Turbine Airfoil Cooling System with Curved Diffusion Film Cooling Hole - A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes a first sidewall having a first radius of curvature about an axis generally orthogonal to a centerline of cooling fluid flow through the diffusion film cooling hole and a second sidewall having a second radius of curvature about an axis generally orthogonal to the centerline of cooling fluid flow through the at least one diffusion film cooling hole. The radii of curvature of the first and second sidewalls are different such that the diffusion film cooling hole includes an ever increasing cross-sectional area moving from an inlet to an outlet, thereby diffusing and reducing the velocity of cooling fluids flowing there through. | 03-18-2010 |
| 20100068032 | Turbine Airfoil Cooling System with Diffusion Film Cooling Hole - A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes a first section extending from an inner surface of the outer wall into the outer wall, a second section extending the first section toward an outer wall, and a third section extending from the second section and terminating at an outer surface of the outer wall. The diffusion film cooling hole may provide a metering capability together with diffusion sections that provide a larger film cooling hole breakout and footprint, which create better film coverage and yield better cooling of the turbine airfoil. The diffusion film cooling hole may provide a smooth transition, which allows the film cooling flow to diffuse better in the second and third sections of the diffusion film cooling hole. | 03-18-2010 |
| 20100027584 | Thermocouple for Gas Turbine Environments - A thin-film thermocouple ( | 02-04-2010 |
| 20100021291 | Diffuser Apparatus in a Turbomachine - A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone. | 01-28-2010 |
| 20090266076 | Condensate Polisher Circuit - A power generating system including a working fluid circuit. The power generating system includes a condenser system in the working fluid circuit and a condensate polisher circuit. The condenser system receives a working fluid that includes steam or a combination of water and steam and condenses at least a portion of the working fluid into a condensate. The condensate has a temperature above a predetermined upper operating temperature. The condensate polisher circuit is branched off from the working fluid circuit and receives and treats said condensate from the working fluid circuit and returns treated condensate to the working fluid circuit. The condensate polisher circuit includes a heat exchanger that reduces the temperature of the condensate at least to the upper operating temperature and a condensate polisher that removes contaminants from the condensate to bring the condensate to a predetermined purity. | 10-29-2009 |
| 20090235516 | Method of Servicing a Power Generator - A method of servicing a stator frame of a power generator. The method includes removing a first stator core from a main housing of the stator frame, removing a plurality of first dove-tail shaped keybars that extend axially within and are coupled to a main support structure forming part of the main housing, and installing a plurality of second keybars in the main support structure. The second keybars are adapted to support a second stator core. Each of the second keybars has a generally rounded engagement surface and the second stator core includes recesses with shapes corresponding to the generally rounded engagement surfaces of the second keybars such that the second stator core can be securely supported in the main support structure by the second keybars. | 09-24-2009 |
