| Patent application number | Description | Published |
|---|
| 20090096174 | BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE - An air seal assembly includes a featherseal engaged between adjacent turbine engine components to close a gap therebetween. The featherseal includes a first lateral tab and a second lateral tab which defines a tab space therebetween. The tab space locks the featherseal into the turbine engine component to prevent fore-aft movement thereof. | 04-16-2009 |
| 20090116953 | Turbine airfoil with platform cooling - Convective cooling of gas turbine engine airfoil platforms is enhanced by grooving the interface of the platforms with corresponding platform-to-platform seals, thereby accelerating cooling airflow over the platform surfaces. | 05-07-2009 |
| 20090208325 | LARGE FILLET AIRFOIL WITH FANNED COOLING HOLE ARRAY - A turbine airfoil has a fillet connecting the nominal portion of the airfoil into an end wall. Cooling holes are formed over a greater circumferential extent in the fillet than they are through the nominal portion of the airfoil. | 08-20-2009 |
| 20090269184 | Gas Turbine Engine Systems Involving Turbine Blade Platforms with Cooling Holes - Gas turbine engine systems involving turbine blade platforms with mateface cooling holes are provided. In this regard, a representative turbine blade for a gas turbine engine includes: an airfoil having a leading edge, a trailing edge, a pressure side and a suction side; and a blade platform on which the airfoil is disposed, the blade platform having a pressure side mateface located adjacent to the pressure side of the airfoil and a suction side mateface located adjacent to the suction side of the airfoil, the blade platform having a cooling hole operative to direct a flow of cooling air toward an adjacent blade platform. | 10-29-2009 |
| 20100232979 | BLADE TIP COOLING GROOVE - An example turbine blade includes a blade having an airfoil profile extending radially toward a blade tip. A shelf is established in the blade tip. A sealing portion of the blade tip extends radially past a floor of the shelf. The sealing portion extends from a blade tip leading edge to a blade tip trailing edge. A groove is established in the blade tip. The groove extends from adjacent the shelf to adjacent the blade tip trailing edge. The groove is configured to communicate a fluid from a position adjacent the shelf to a position adjacent the blade tip trailing edge. | 09-16-2010 |
| 20100310367 | Impingement cooling of a turbine airfoil with large platform to airfoil fillet radius - A method of impingement cooling a turbine airfoil with a large platform to airfoil fillet radius which includes coring the airfoil fillet such that the fillet wall is maintained at a minimum thickness. An impingement tube is used which follows the fillet contour as it transitions from airfoil to platform and supplies impingement air to the airfoil walls. The air subsequently flows across the airfoil internal wall and finally exits the airfoil through airfoil holes to provide film cooling to the airfoil fillet. | 12-09-2010 |
