Patent application number | Description | Published |
20100178160 | DEVICE AND SYSTEM FOR REDUCING SECONDARY AIR FLOW IN A GAS TURBINE - A device for reducing secondary airflow in a gas turbine is disclosed. The device includes an inter-stage sealing member located between a plurality of first turbine buckets attached to a first rotor disk, and a plurality of second turbine buckets attached to a second rotor disk. The first rotor disk and the second rotor disk are rotatable about a central axis. The inter-stage sealing member is configured to be attached in a fixed position relative to the first rotor disk and the second rotor disk, and to contact the plurality of first buckets and the plurality of second buckets in a sealing engagement. | 07-15-2010 |
20100196164 | Turbine Coverplate Systems - In one embodiment, a coverplate may be configured to axially overlay a plurality of blade retaining slots within a wheel post of a rotor wheel. The coverplate may include a tab for radially securing the coverplate within a complementary groove of the rotor wheel and an aperture configured to align with a corresponding aperture of the turbine wheel to receive a fastener for axially securing the coverplate to the rotor wheel. | 08-05-2010 |
20110070096 | CURVED ELECTRODE AND ELECTROCHEMICAL MACHINING METHOD AND ASSEMBLY EMPLOYING THE SAME - An electrode for an electrochemical machining process is provided. The electrode comprises a curved, electrically conductive member, and an insulating coating covering at least a portion of a side surface of the curved, electrically conductive member. An electrochemical machining assembly is also provided for machining curved holes in a workpiece. The assembly includes at least one curved electrode and a power supply operatively connected to provide a pulsed voltage to the at least one curved electrode and to the workpiece. The assembly further includes a rotational driver operatively connected to move the at least one curved electrode along a curved path within the workpiece. The assembly is configured to remove material from the workpiece upon application of the pulsed voltage to the at least one curved electrode and to the workpiece. An electrochemical machining method is also provided for forming one or more curved holes in an electrically conductive workpiece. | 03-24-2011 |
20110097199 | SYSTEM AND METHOD TO INSULATE TURBINES AND ASSOCIATED PIPING - An insulation system includes at least one turbine insulation compartment configured to enclose at least a portion of a turbine; an insulation storage compartment configured to store a supply of insulation; a plurality of first pipes that connect to the turbine insulation compartment and the insulation storage compartment; and a blower configured to generate a flow of air in at least one first pipe to pneumatically convey insulation between the insulation storage compartment and the at least one turbine insulation compartment. A method of insulating at least a portion of a turbine includes enclosing at least a portion of the turbine in a compartment; and conveying insulation into the compartment. | 04-28-2011 |
20110162384 | TEMPERATURE ACTIVATED VALVES FOR GAS TURBINES - A system for modulating the amount of air supplied through a pressure boundary in a gas turbine is disclosed that includes a passageway located on the pressure boundary. Additionally, a temperature activated valve is mounted within the passageway and is configured to activate at a predetermined temperature threshold. Specifically, the temperature activated valve activates from a closed position to an open position when the local temperature at the temperature activated valve reaches or exceeds the predetermined temperature threshold to allow air to flow through the passageway. | 07-07-2011 |
20110243746 | COMPOSITE TURBINE BUCKET ASSEMBLY - A composite turbine blade assembly includes a ceramic blade including an airfoil portion, a shank portion and an attachment portion; and a transition assembly adapted to attach the ceramic blade to a turbine disk or rotor, the transition assembly including first and second transition components clamped together, trapping said ceramic airfoil therebetween. Interior surfaces of the first and second transition portions are formed to mate with the shank portion and the attachment portion of the ceramic blade, and exterior surfaces of said first and second transition components are formed to include an attachment feature enabling the transition assembly to be attached to the turbine rotor or disk. | 10-06-2011 |
20120003079 | APPARATUS AND SYSTEM FOR SEALING A TURBINE ROTOR - An apparatus for restricting fluid flow in a turbo-machine is disclosed. The apparatus includes: a first inter-stage sealing member configured to be located between a first rotating airfoil stage and a second rotating airfoil stage attached to a rotor shaft, the first inter-stage sealing member including a segmented structure that includes a plurality of segments forming a circumferential surface, the first inter-stage sealing member including: a first base portion including a securing mechanism configured to at least substantially radially and tangentially secure the inter-stage sealing member to an inter-stage support structure; a first axial retention mechanism; and a first axially extending sealing portion configured to be outwardly radially loaded against at least one of the first rotating airfoil stage and the second rotating airfoil stage. | 01-05-2012 |
20120087799 | AXIAL RETENTION DEVICE FOR TURBINE SYSTEM - An axial retention device for a turbine is disclosed. The axial retention device includes a latch associated with a mating surface of one of a turbine component and a support structure. The latch has an outward bias and includes an axial load surface. The axial retention device further includes a pocket defined in a mating surface of the other of the turbine component and the support structure. The pocket is configured to accept the latch therein and includes a mating axial load surface. Engagement of the latch and the pocket allows the axial load surface and the mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in at least one direction. | 04-12-2012 |
20120093634 | BONDED TURBINE BUCKET TIP SHROUD AND RELATED METHOD - A turbine bucket includes an airfoil portion and a tip shroud at a radially outer end of the airfoil portion. The tip shroud includes a first radially inner tip shroud component formed integrally with the airfoil portion and composed of a first metal material, and a second radially outer structural tip shroud component composed of a second metal material bonded to the first radially inner tip shroud component. | 04-19-2012 |
20130168927 | MODIFICATION OF TURBINE ENGINE SEAL ABRADABILITY - In one aspect, the present subject matter discloses a seal including a substrate material. The substrate material has a first portion having a first abradability and a second portion having a second abradability, the first abradability being different from the second abradability. | 07-04-2013 |
20130236289 | TURBINE INTERSTAGE SEAL SYSTEM - A system includes a multi-stage turbine. The multi-stage turbine has an interstage seal extending axially between a first turbine stage and a second turbine stage. The interstage seal has an upper body that extends from an upstream seating arm to a downstream seating arm. The upstream and downstream seating arms are designed to constrain movement of the interstage seal along a radial direction of the multi-stage turbine. The interstage seal also has a lower body that extends from a seating end to a hook end. The seating end is designed to constrain movement of the interstage seal along the radial direction. The hook end has a protrusion that extends crosswise relative to a base of the lower body. The hook end is designed to constrain movement of the interstage seal along the radial direction and an axial direction of the multi-stage turbine. | 09-12-2013 |
20130330168 | THERMALLY ACTUATED ASSEMBLY FOR A GAS TURBINE SYSTEM AND METHOD OF CONTROLLING A COOLING AIRFLOW PATH - A thermally actuated assembly for a gas turbine assembly for a gas turbine system includes a heat transfer component having a first portion and a second portion, wherein the first portion is disposed within a first cavity having a first temperature and the second portion is disposed in a second cavity having a second temperature, wherein the heat transfer component extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element disposed within the second cavity and in operable communication with the heat transfer component. Further included is a flow manipulating device disposed within the second cavity and configured to displace in response to a temperature change in the first cavity. | 12-12-2013 |