| Patent application number | Description | Published |
|---|
| 20080253884 | Out-flow margin protection for a gas turbine engine - A cooled turbine exhaust case assembly includes a plenum defined at least in part by a forward outer diameter flowpath ring and a turbine case, a probe positioned at a probe opening formed in the forward outer diameter flowpath ring, and an inlet opening in the turbine case for introducing cooling air to the plenum. | 10-16-2008 |
| 20090028703 | Airfoil mini-core plugging devices - A turbine engine component, such as a high pressure turbine vane, has an airfoil portion and at least one coolant system embedded within the airfoil portion. Each coolant system has an exit through which a cooling fluid flows, which exit has at least one device for preventing deposits from interfering with the flow of cooling fluid from the exit. The at least one device may be at least one depression and/or at least one grill structure formed from elongated ribs. | 01-29-2009 |
| 20090097977 | SERPENTINE MICROCIRCUIT COOLING WITH PRESSURE SIDE FEATURES - In accordance with the present invention, there is provided a turbine engine component having an airfoil portion with a pressure side and a suction side, a first microcircuit embedded in a wall forming the pressure side, an internal cavity containing a supply of cooling fluid, the first microcircuit having an inlet leg, an intermediate leg, and an outlet leg, and a plurality of communication holes between the internal cavity and the outlet leg. In a preferred embodiment, the outlet leg is provided with at least one set of features for locally accelerating cooling flow in the outlet leg and for increasing heat pick-up ability. | 04-16-2009 |
| 20090208343 | SERPENTINE MICROCIRCUITS FOR HOT GAS MIGRATION - A turbine engine component, such as a turbine blade, has an airfoil portion with a pressure side and a suction side. The turbine engine component also has a first cooling circuit within the pressure side for cooling the pressure side of the airfoil portion and a second cooling circuit within the suction side for cooling the suction side of the airfoil portion and for cooperating with a wrap around leading edge cooling circuit for creating a cooling film over the pressure side. | 08-20-2009 |
| 20090238675 | AIRFOIL THERMAL MANAGEMENT WITH MICROCIRCUIT COOLING - A turbine engine component, such as a turbine engine blade, has an airfoil portion with a pressure side wall and a suction side wall, a plurality of ribs extending between the pressure side wall and the suction side wall, and a plurality of supply cavities located between the ribs. The component further has an arrangement for cooling the airfoil portion. The cooling arrangement comprises a first cooling circuit embedded within the suction side wall for convectively cooling the suction side wall, a second cooling circuit embedded within the pressure side wall for cooling the pressure side wall, and a third passageway for increasing a temperature of at least one of the ribs by conduction. | 09-24-2009 |
| 20090238694 | RADIAL SPLIT SERPENTINE MICROCIRCUITS - A turbine engine component, such as a turbine blade has an airfoil portion with an airfoil mean line, a pressure side, and a suction side. A first region on the pressure side of the airfoil portion has a first array of cooling microcircuits embedded in a wall forming the pressure side. A second region on the pressure side has a second array of cooling microcircuits embedded in the wall. The first region is located on a first side of the mean line and the second region is located on a second side of the mean line. | 09-24-2009 |
| 20100000197 | IMPINGEMENT COOLING FOR TURBOFAN EXHAUST ASSEMBLY - A cooling system for a turbine exhaust assembly comprises an annular case, a flowpath ring and a splash plate. The flowpath ring is coaxially disposed within the annular case. The splash plate extends axially between the annular case and the flowpath ring. A plurality of cooling fluid apertures is formed in the annular case, in order to provide cooling fluid flow onto the splash plate. A plurality of impingement holes is formed in the splash plate, in order to provide impingement flow onto the flowpath ring. | 01-07-2010 |
| 20100008758 | LEADING EDGE COOLING WITH MICROCIRCUIT ANTI-CORIOLIS DEVICE - A turbine engine component, such as a high pressure turbine blade, has an airfoil portion having a pressure side, a suction side, and a leading edge. A cooling system is provided within the leading edge. The cooling system includes at least one peripheral leading edge cooling channel for creating anti-Coriolis forces in the leading edge of the airfoil portion. | 01-14-2010 |
| 20100126960 | Serpentine Microcircuit Vortex Turbulators for Blade Cooling - A cooling microcircuit for use in a turbine engine component is provided. The cooling microcircuit has at least one leg through which a cooling fluid flows. A plurality of cast vortex generators are positioned within the at least one leg to improve the cooling effectiveness of the cooling microcircuit. | 05-27-2010 |
| 20100150735 | Multi-Peripheral Serpentine Microcircuits For High Aspect Ratio Blades - A cooling arrangement for a pressure side of an airfoil portion of a turbine engine component is provided. The cooling arrangement comprises a pair of cooling circuits embedded within a wall forming the pressure side. The pair of cooling circuits includes a first serpentine cooling circuit and a second circuit offset from the first serpentine cooling circuit. | 06-17-2010 |
| 20100247328 | Microcircuit cooling for blades - A turbine engine component, such as a turbine blade, includes at least one cooling circuit having a plurality of legs through which a cooling fluid flows, and a plurality of cooling devices in at least one of the legs. Each of the cooling devices has a heat transfer multiplier in the range of from 1.8 to 2.4 and a reattachment length in the range of from 1.9 to 2.5. | 09-30-2010 |
