Patent application number | Description | Published |
20090324422 | Cascade tip baffle airfoil - A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle. | 12-31-2009 |
20100158696 | CURVED PLATFORM TURBINE BLADE - A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform. | 06-24-2010 |
20100221122 | Flared tip turbine blade - A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side. | 09-02-2010 |
20130224027 | SCALLOPED SURFACE TURBINE STAGE WITH PURGE TROUGH - A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow. | 08-29-2013 |
20130251520 | SCALLOPED SURFACE TURBINE STAGE - A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil. | 09-26-2013 |
20140086739 | TRANSITION DUCT FOR USE IN A TURBINE ENGINE AND METHOD OF ASSEMBLY - A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end. | 03-27-2014 |
Patent application number | Description | Published |
20080286106 | TURBINE ROTOR BLADE ASSEMBLY AND METHOD OF FABRICATING THE SAME - A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein. | 11-20-2008 |
20080286109 | TURBINE ROTOR BLADE AND METHOD OF FABRICATING THE SAME - A rotor blade assembly includes a shank, an airfoil that is formed integrally with the shank, and a removable platform coupled between said shank and said airfoil via a friction fit. A method of assembling a gas turbine engine rotor blade assembly that includes a removable platform, and a gas turbine engine rotor assembly including the removable platform are also described herein. | 11-20-2008 |
20090202337 | METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES - A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger. | 08-13-2009 |