| Patent application number | Description | Published |
|---|
| 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 |
| 20100054911 | SYSTEM AND METHOD FOR ADJUSTING CLEARANCE IN A GAS TURBINE - A system for adjusting a clearance in a gas turbine including a turbine rotor and a plurality of buckets is disclosed. The system includes: a shroud assembly including at least one shroud segment, the at least one shroud segment being disposed in an interior of a turbine shell; and an elongated member extending from the turbine shell. The at least one shroud segment is attached to an end of the elongated member, the elongated member configured to move in response to a temperature change to move the shroud segment and change a clearance between the shroud segment and at least one of the plurality of buckets. | 03-04-2010 |
| 20100054912 | DEVICE, SYSTEM AND METHOD FOR THERMALLY ACTIVATED DISPLACEMENT - An actuating device includes: at least one first elongated member having a first coefficient of thermal expansion (CTE); and at least one second elongated member having a second CTE different from the first CTE, the second elongated member being nested within the first elongated member, the device being configured to displace a portion of the device a selected distance along a major axis of the device based on a relationship between the first CTE and the second CTE in response to a change in temperature. | 03-04-2010 |
| 20100068035 | APPARATUS AND METHOD FOR COOLING A TURBINE - A cooling system for a turbine includes a blower configured to generate a cooling gas flow to be passed through a rotor cavity of the turbine; piping configured to deliver the cooling gas flow to the turbine; and at least one valve configured to control the cooling gas flow. The piping is operatively connected to the rotor of the turbine. A method of cooling a turbine includes generating a cooling gas flow with a blower to be passed through a rotor cavity of the turbine; and delivering the cooling gas flow to the turbine. | 03-18-2010 |
| 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 |
| 20100247294 | METHOD AND APPARATUS FOR TURBINE INTERSTAGE SEAL RING - A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively. | 09-30-2010 |
| 20100254805 | GAS TURBINE INNER FLOWPATH COVERPIECE - A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body. | 10-07-2010 |
| 20100284799 | METHOD AND APPARATUS FOR TURBINE ENGINES - A method for sealing a gas turbine engine includes coupling a turbine bucket to a rotor wheel and forming an interface region therebetween. A cooling air passage is defined in a portion of the rotor wheel and a cooling air manifold is defined in a portion of the turbine bucket. The method also includes inserting a seal tube within at least a portion of the cooling air passage. The method further includes coupling the cooling air passage, the seal tube, and the cooling air manifold in flow communication to at least partially define a turbine bucket cooling system. The method also includes operating the gas turbine engine such that the rotor wheel and the turbine bucket are rotated, thereby inducing a pressure on the seal tube to substantially decrease air flow discharged from the turbine bucket cooling system through the interface region. | 11-11-2010 |
| 20100290904 | COUPLING FOR ROTARY COMPONENTS - A system is disclosed that includes a turbine engine having a first rotary component having a first annular coupling disposed about a rotational axis of the engine. The first annular coupling has an axially converging surface relative to the rotational axis. The system also includes a second rotary component having a second annular coupling disposed about the rotational axis of the turbine engine, wherein the second annular coupling comprises an axially diverging surface such that the axially converging surface of the first annular coupling mates with the axially diverging surface. | 11-18-2010 |
| 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 |
| 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 |
| 20110164982 | APPARATUS AND METHOD FOR A LOW DISTORTION WELD FOR ROTORS - A rotor includes a first rotor segment having a first outer surface and a second rotor segment having a second outer surface. A mechanical joint is between the first and second rotor segments, and a cavity is radially outward of the mechanical joint and beneath the first and second outer surfaces. A weld bead is between the first and second outer surfaces. A method for manufacturing a rotor includes machining a first rotor segment having a first concentric axis of rotation and machining a second rotor segment having a second concentric axis of rotation. The method further includes aligning the first rotor segment to the second rotor segment radially using a mechanical joint and applying a weld bead over a portion of the first and second rotor segments to connect the first rotor segment to the second rotor segment. | 07-07-2011 |
