Patent application number | Description | Published |
20090031802 | ROTOR ALIGNMENT SYSTEM AND METHOD - Disclosed herein is a rotor to stator alignment method. The alignment method includes, positioning a plurality of eccentric rings between the rotor and a stator, and rotating at least one of the plurality of eccentric rings relative to the stator thereby reducing eccentricity of the rotor with the stator. | 02-05-2009 |
20090053042 | METHOD AND APPARATUS FOR CLEARANCE CONTROL OF TURBINE BLADE TIP - A gas turbine including a casing and a shroud ring, the gas turbine including an attachment device rigidly attached to the casing and at least one of the shroud ring and a duct attached to the shroud ring, wherein the device allows the shroud ring to expand and contract independent of the casing and provides limited net axial growth of the shroud ring. | 02-26-2009 |
20090053046 | METHOD, SYSTEM AND APPARATUS FOR TURBINE DIFFUSER SEALING - A turbine diffuser is disclosed. The turbine diffuser includes a diffuser segment having a forward end and an aft end with a flange disposed at the aft end of the diffuser segment. The diffuser segment is joinable to an adjacent diffuser segment via the flange, which includes a seal retainer that is securedly connectable in a radial direction with a seal. | 02-26-2009 |
20090097968 | APPARATUS AND METHOD FOR CLEARANCE CONTROL OF TURBINE BLADE TIP - An inner shell for a rotating machine including at least one segment; and at least one complementary segment in operable communication with the at least one segment, the segments forming a support structure for a shroud ring; wherein the at least one segment and the at least one complementary segment are individually moved to change a set of dimensions defined by the at least one segment and the at least one complementary segment. A method for controlling a dimension of the shroud ring in a rotating machine is also disclosed. | 04-16-2009 |
20100189551 | Systems and Methods of Reducing Heat Loss from a Gas Turbine During Shutdown - A method operates a gas turbine that includes a compressor section, a turbine section and an extraction cooling system. The method includes monitoring an operation of the gas turbine, directing a cooling air flow through the extraction cooling system from the compressor section to the turbine section in response to normal operation of the gas turbine, and directing a warming air flow through the extraction cooling system to the compressor section and the turbine section in response to shutdown of the gas turbine. | 07-29-2010 |
20100272558 | Turbine rotor support apparatus and system - An apparatus to support a rotor of a turbine engine disposed upon a support surface is disclosed. The apparatus includes a housing, a rotor support bearing disposed within the housing, and a support leg in operable communication with the housing and in direct structural connection with the support surface. | 10-28-2010 |
20100296936 | LOW STRESS CIRCUMFERENTIAL DOVETAIL ATTACHMENT FOR ROTOR BLADES - A retaining system is provided for circumferential entry rotor dovetails inserted into dovetail slot in a rotor. A plurality of rotor blade dovetails are circumferentially slidable into and along the dovetail slot, with each rotor blade dovetail having a neck and a pair of oppositely oriented lobes. A plurality of rail segments are circumferentially slid into channels in the dovetail slot between the dovetail lobes and the respective disk hoops. The rail segments define a first pressure face that engages against an outward pressure face of the dovetail lobes, and a second pressure face that engages against an inward pressure face of the respective disk hoop component. | 11-25-2010 |
20100303606 | TURBOMACHINE COMPRESSOR WHEEL MEMBER - A turbomachine includes a rotor assembly including a wheel member. The wheel member includes a first portion that extends to a second portion through an intermediate portion. The intermediate portion partially defines a first wheel space and a second wheel space. The wheel member further includes a rotor inertia belt member arranged at the second portion. The rotor inertia belt member includes an extraction air cavity. The extraction air cavity includes an inlet, a first plurality of extraction air passages each including an inlet section and an outlet section, the outlet section leading into the first wheel space, and a second plurality of extraction air passages each including an inlet portion and an outlet portion, the outlet portion leading into the second wheel space. | 12-02-2010 |
20110000222 | GAS TURBINE ROTOR-STATOR SUPPORT SYSTEM - A system to support a rotor and a stator of a rotating machine disposed upon a support base, the system including at least one support leg in operable communication with a bearing of the rotor and with the support base; and at least one strut in operable communication with the at least one support leg and with the stator. | 01-06-2011 |
20120009058 | COMPRESSIBLE SUPPORTS FOR TURBINE ENGINES - A system is provided that includes a first turbine alignment component for a turbine engine; and a shim comprises a metal foam. The shim mounts between a first surface of the first turbine alignment component and a second surface of a second turbine alignment component. | 01-12-2012 |
20120093639 | APPARATUS AND METHOD FOR ALIGNING A TURBINE CASING - A casing includes an inner shell and an outer shell that surrounds the inner shell and comprises a plurality of inflection points. An annular flange is between the inner shell and the outer shell, and a plurality of joints attach the inner shell to the annular flange. A connector is between the annular flange and the outer shell at each of the plurality of inflection points. A method for assembling a casing includes joining a plurality of curved sections to one another to generally define an arcuate inner shell and surrounding the arcuate inner shell with an outer shell. The method further includes attaching the arcuate inner shell to an annular flange at first attachment points and connecting the annular flange to the outer shell at second attachment points spaced approximately equidistantly from the first attachment points. | 04-19-2012 |
20130058779 | TURBINE CASING ASSEMBLY MOUNTING PIN - In certain embodiments of the present disclosure a turbine casing assembly is described. The turbine casing assembly includes an inner casing and an outer casing surrounding the inner casing. The outer casing includes a first outer casing section and a second outer casing section that join together along a flange. Two bolts extend through the flange and join together the first outer casing section and the second outer casing section. A pin having a first segment having a first diameter and a second segment having a second diameter extends through the inner casing and the outer casing and supports the inner casing relative to the outer casing. The pin has a first diameter that is greater than the second diameter and is located between the two bolts along the axis of the flange. | 03-07-2013 |
20130058780 | TURBINE CASING ASSEMBLY MOUNTING PIN - In certain embodiments of the present disclosure, a turbine casing assembly is described. The turbine casing assembly includes an inner casing and an outer casing surrounding the inner casing. The outer casing has a first outer casing section and a second outer casing section that join together along a flange. A bolt extends through the flange and joins together the first outer casing section and the second outer casing section. The turbine casing assembly further includes a pin. The pin has a segment defining an opening therethrough. The pin extends through the inner casing and the outer casing and supports the inner casing relative to the outer casing. The bolt passes through the opening defined by the pin. | 03-07-2013 |
20130064649 | PIPING ASSEMBLY AND METHOD FOR CONNECTING INNER AND OUTER SHELL IN TURBINE SYSTEM - A piping assembly and a method for connecting an inner shell and an outer shell in a turbine system are disclosed. The piping assembly includes an inner fitting for connection to the inner shell and an outer fitting for connection to the outer shell. The piping assembly further includes an attenuation member extending between the inner fitting and the outer fitting and comprising an attenuation curve. The attenuation curve permits movement of the attenuation member in at least one of a longitudinal direction, a radial direction, or a tangential direction. | 03-14-2013 |
20130294883 | GAS TURBOMACHINE INCLUDING A COUNTER-FLOW COOLING SYSTEM AND METHOD - A gas turbomachine includes a casing assembly surrounding a portion of the gas turbomachine and a counter-flow cooling system arranged within the casing. The counter-flow cooling system is configured and disposed to guide cooling fluid through the casing assembly in a first axial direction and return cooling fluid through the casing assembly in a second axial direction that is opposite the first axial direction. | 11-07-2013 |
20130326875 | METHOD AND APPARATUS FOR ROLL-IN AND ALIGNMENT OF A CASING SHELL OF A GAS TURBINE - A method and apparatus for rolling and aligning a casing of a gas turbine is disclosed. At least one jack having a roller at one end is positioned at a location to couple the roller to the casing. The casing is rolled within the turbine by rolling over the roller of the at least one jack. The roller is moved relative to the at least one jack to align the casing within the turbine. | 12-12-2013 |
20130330187 | METHOD AND APPARATUS FOR MITIGATING OUT OF ROUNDNESS EFFECTS AT A TURBINE - A turbine and a method of mitigating out-of-roundness effects at a turbine is disclosed. An inner turbine shell and an outer turbine shell of the turbine is provided. The inner turbine shell is coupled to the outer turbine shell using a ring insert. The ring insert is segmented into a plurality of ring insert segments that reduce a transfer of load from the outer turbine shell to the inner turbine shell to mitigate out-of-roundness of the inner turbine shell. | 12-12-2013 |
20140010646 | TURBINE ASSEMBLY AND METHOD FOR ASSEMBLING A TURBINE - According to one aspect of the invention, a turbine assembly includes a frame coupled to a ground surface, a bearing housing supporting a rotor bearing and a sleeve assembly attached to the frame and the bearing housing. The sleeve assembly includes an outer sleeve with a first flange on a first end that is positioned in an opening in the bearing housing and a second end that abuts the shim, an inner sleeve positioned within a portion of the outer sleeve and a bolt positioned within the inner sleeve and threadably coupled to the frame, wherein the bolt compressively loads the inner sleeve thereby loading a portion of the outer sleeve at the second end between the inner sleeve and the frame and wherein a first gap dimension is substantially maintained between the first flange and bearing housing as the bolt is preloaded and coupled to the frame. | 01-09-2014 |
20140017076 | Turbine Shell Support Arm - The present application and the resultant patent provide an example of a turbine casing. The turbine casing may include an outer shell, an inner shell, and a support arm supporting the inner shell within the outer shell. The inner shell and the support arm may include a scallop therein for reduced stress. | 01-16-2014 |
20140026414 | METHOD AND SYSTEM FOR ASSEMBLING AND DISASSEMBLING TURBOMACHINES - A method and system adapted for removing one or more shells from an assembly of multiple annular shells, for example, turbine shells of a gas turbine engine. The method includes removing an upper shell positioned in an upper position relative to a lower shell of the assembly of multiple annular shells, and then positioning and securing a counterweight in the upper position and securing the counterweight to the lower shell as a replacement for the upper shell in the upper position. The counterweight and the lower shell are then rotated in unison until the lower shell is in the upper position and the counterweight is in a lower position previously occupied by the lower shell. Thereafter, the lower shell can be removed from the assembly. | 01-30-2014 |
20140102290 | MECHANICAL STOP ADJUSTMENT FOR JACK - A first adjustable stop on a jack member selectively adjusts an incline stop gap while a second adjustable stop on a support element selectively adjusts a decline stop gap. Stop surfaces on the first adjustable stop and the support element may define the incline stop gap, while stop surfaces on the second adjustable stop and the first adjustable stop may define the decline stop gap. A number of turns of a stop needed to effect a desired of adjustment may be determined using a pitch, lead, and/or number of starts of threads used to mount the stops. | 04-17-2014 |
20140109590 | GAS TURBINE THERMAL CONTROL AND RELATED METHOD - Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine. | 04-24-2014 |
20140109594 | Deformable Mounting Assembly - A deformable fastener assembly for use with a gas turbine engine. The deformable fastener may be used to fasten a component of the gas turbine that is subjected to high temperatures and thermal deformation, such as an impingement sleeve assembly, to a rigid portion, such as the inner turbine shell of the gas turbine engine. The deformable fastener assemblies may permit components to be fastened to a rigid portion of the gas turbine with a consistent load input to permit frictional transient sliding of the component relative to the rigid portion of the gas turbine engine. | 04-24-2014 |
20140112759 | GAS TURBINE CASING THERMAL CONTROL DEVICE - A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed. | 04-24-2014 |
20140130342 | SYSTEM FOR ASSEMBLING AND DISASSEMBLING A TURBINE SECTION OF A GAS TURBINE - A counter weight for installing and removing a lower portion of an inner casing of a turbine section generally includes a semi-annular main body having a first radially extending mating surface and a second radially extending mating surface. A radial gear rack extends radially outward from the main body. The radial gear rack includes a primary segment that extends a first angular distance between the first radially extending mating surface and the second radially extending mating surface of the main body. A secondary segment of the radial gear rack extends a second angular distance from the second radially extending mating surface of the main body. The secondary segment defines an at least partially linear inner surface and an outer arcuate surface. | 05-15-2014 |
20140271111 | METHOD AND APPARATUS TO IMPROVE HEAT TRANSFER IN TURBINE SECTIONS OF GAS TURBINES - A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide. | 09-18-2014 |
20140334925 | SYSTEM FOR SUPPORTING A TURBINE NOZZLE - A system for supporting a turbine nozzle includes an inner barrel having a forward end, an aft end and an outer surface that extends between the forward end and the aft end. A first fitting that extends through the outer surface is defined within the inner barrel. The system further includes a nozzle support ring that defines a second fitting that is complementary to the first fitting defined within the inner barrel. | 11-13-2014 |
20140352313 | DIFFUSER STRUT FAIRING - A diffuser strut fairing includes a top portion, a bottom portion, a pressure side portion, a suction side portion, an inner surface and an outer surface. The pressure side portion and the suction side portion extend between the top portion and the bottom portion. The exhaust diffuser strut faring further includes a flow manifold that is at least partially defined between the pressure side portion and the suction side portion. A plurality of openings is disposed along the suction side portion and are in fluid communication with the flow manifold. | 12-04-2014 |
20150037145 | SYSTEMS RELATING TO AXIAL POSITIONING TURBINE CASINGS AND BLADE TIP CLEARANCE IN GAS TURBINE ENGINES - A gas turbine engine that includes: a flowpath defined through one of a compressor and a turbine; an inner casing defining an axially tilted outboard boundary of the flowpath, which, relative to the axial tilt, defines a converging direction in which the flowpath converges and a diverging direction in which the flowpath diverges; a row of rotor blades having outer tips that oppose the outboard boundary across a gap clearance defined therebetween; an outer casing concentrically arranged about the inner casing so to form an annulus therebetween; and a connection assembly that slidably connects the inner casing to the outer casing and includes a biasing means for axially preloading the inner casing in the converging direction. | 02-05-2015 |
20150040581 | BORESCOPE ASSEMBLY AND METHOD OF INSTALLING BORESCOPE PLUGS - A borescope assembly includes a first borescope plug comprising a first perimeter geometry portion. Also included is a second borescope plug comprising a second perimeter geometry portion distinct from the first perimeter geometry portion. Further included is a first borescope hole comprising a first hole geometry portion corresponding to the first perimeter geometry portion of the first borescope plug. Yet further included is a second borescope hole comprising a second hole geometry portion corresponding to the second perimeter geometry portion of the second borescope plug. | 02-12-2015 |
20150047358 | INNER BARREL MEMBER WITH INTEGRATED DIFFUSER FOR A GAS TURBOMACHINE - An inner barrel member for a gas turbomachine includes a body having an outer surface, an inner surface and one or more radial flow splitters provided on the outer surface. The one or more radial flow splitters are configured and disposed to be arranged along a combustor centerline at a combustion flow outlet radially inwardly of a transition piece. | 02-19-2015 |
20150086330 | GAS TURBINE CASING LOAD SHARING MECHANISM - A turbine system is provided having a first turbine casing and a second turbine casing, the first and second turbine casings together defining an inner wall. The turbine system further includes a first attachment flange extending from a surface of the first turbine casing within the inner wall and a second attachment flange extending from a surface of the second turbine casing within the inner wall. The first attachment flange defines a first aperture and the second attachment flange defines a second aperture. A pin extends through the first aperture and into the second aperture. | 03-26-2015 |