| Patent application number | Description | Published |
|---|
| 20080219854 | TURBINE COMPONENT WITH AXIALLY SPACED RADIALLY FLOWING MICROCIRCUIT COOLING CHANNELS - An airfoil for a gas turbine engine component such as a turbine blade or a vane includes at least one microcircuit cooling channel having a plurality of sub-channels extending along a radial direction of the airfoil. The plurality of channels are axially spaced, and are fed by radially spaced inlets. | 09-11-2008 |
| 20080277090 | Investment casting cores and methods - An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. The metallic casting core includes a plurality of body sections. The first region is along at least some of the body sections. The metallic casting core includes a plurality of springs spanning gaps between adjacent body sections and unitarily formed therewith. | 11-13-2008 |
| 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 |
| 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 |
| 20090238695 | FULL COVERAGE TRAILING EDGE MICROCIRCUIT WITH ALTERNATING CONVERGING EXITS - A turbine engine component has an airfoil portion with a pressure side wall, a suction side wall, and a trailing edge. The turbine engine component further has at least one first cooling circuit core embedded within the pressure side wall, with each first cooling circuit core having a first exit for discharging a cooling fluid, at least one second cooling circuit core embedded within the suction side wall, with each second cooling circuit core having a second exit for discharging a cooling fluid, and the first and second exits being aligned in a spanwise direction of the airfoil portion. | 09-24-2009 |
| 20100054915 | AIRFOIL INSERT - An airfoil insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior extending inside the insert wall from a first end to second end, and an exterior extending outside the insert wall from the first end to the second end. The contact element is formed on the exterior of the insert wall. The flow director is formed on the insert wall at a boundary between the interior and the exterior. The flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall. | 03-04-2010 |
| 20100129194 | Castings, Casting Cores, and Methods - The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least one additional casting core. The metallic casting core has opposite first and second faces. The metallic core and at least one additional casting core extend spanwise into the airfoil of the pattern material. In at least a portion of the pattern material outside the airfoil of the pattern material, the metallic casting core is bent transverse to the spanwise direction so as to at least partially surround an adjacent portion of the at least one additional casting core. | 05-27-2010 |
| 20100129195 | Castings, Casting Cores, and Methods - The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a plurality of metallic casting cores. Each metallic casting core has opposite first and second faces and a respective portion along the trailing edge of the airfoil. At least two of the metallic cores have sections offset between the pressure side and the suction side. | 05-27-2010 |
| 20100129217 | Castings, Casting Cores, and Methods - A gas turbine engine component has a leading edge and a trailing edge and a pressure side and a suction side. The pressure side and suction side extend between the leading edge and trailing edge. One or more cooling passageways extend through the airfoil and comprise a trunk extending from an inlet. At the inlet, there is an additional passageway adjacent the trunk and having at least one edge recessed relative to the trunk. | 05-27-2010 |
| 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 |
| 20110123310 | TURBINE AIRFOIL PLATFORM COOLING CORE - A gas turbine engine component has a platform and an airfoil extending from the platform. The platform has a pressure side and a suction side. A cooling passage is formed within the platform, and extends along a pressure side of the platform. Air leaves the passage through an air outlet on a suction side of the platform. | 05-26-2011 |
| 20110123311 | SERPENTINE CORED AIRFOIL WITH BODY MICROCIRCUITS - A gas turbine engine component has an airfoil that extends from a leading edge to a trailing edge, and a suction side and has a pressure side. There are cooling passages extending from a root of the airfoil toward a tip of the airfoil. The cooling passages include a straight passage extending from the root toward the tip and adjacent the leading edge. A serpentine passage has at least three connected paths and is spaced from the straight passage toward the trailing edge. A cooling circuit is provided between the pressure wall and each of the three serpentine paths, and the straight path. A cooling circuit is provided between the suction wall and the straight passage. There is no cooling between at least a downstream one of the at least three paths of the serpentine passage and the suction wall. | 05-26-2011 |
