Patent application number | Description | Published |
20090208326 | RIM SEAL FOR A GAS TURBINE ENGINE - The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material. | 08-20-2009 |
20130051979 | TURBINE SHROUD SEGMENT WITH INTEGRATED IMPINGEMENT PLATE - A turbine shroud segment is metal injection molded (MIM) about an insert having a cooling air cavity covered by an impingement plate. The insert is held in position in an injection mold and then the MIM material is injected in the mold to form the body of the shroud segment about the insert. | 02-28-2013 |
20130051987 | TURBINE SHROUD SEGMENT WITH INTER-SEGMENT OVERLAP - A turbine shroud has a plurality of shroud segments disposed circumferentially one adjacent to another. Each segment has a flow restrictor projecting integrally from one end face thereof and overlapping a corresponding end face of a circumferentially adjacent segment. The overlap between the circumferentially adjacent segments restricts gas leakage through the inter-segment gap between adjacent shroud segments. | 02-28-2013 |
20130052007 | TURBINE SHROUD SEGMENT - A turbine shroud segment is metal injection molded (MIM) about a core to provide a composite structure. In one aspect, the core is held in position in an injection mold and then the MIM material is injected in the mold to form the body of the shroud segment about the core. Any suitable combination of materials can be used for the core and the MIM shroud body, each material selected for its own characteristics. The core may be imbedded in the shroud platform to provide a multilayered reinforced platform, which may offer resistance against crack propagation. | 02-28-2013 |
20130052074 | MANUFACTURING OF TURBINE SHROUD SEGMENT WITH INTERNAL COOLING PASSAGES - A turbine shroud segment is metal injection molded (MIM) about a low melting point material insert. The low melting point material is dissolved using heat during the heat treatment cycle required for the MIM material, thereby leaving internal cooling passages in the MIM shroud segment without extra manufacturing operation. | 02-28-2013 |
20130223982 | THERMAL EXPANSION JOINT CONNECTION FOR SHEET METAL ASSEMBLY - A thermal expansion joint suited for metal sheet component assemblies and method of connection is described. The expansion joint connection is formed by overlapping edge portions of components which are subject to different temperatures. Slot apertures are formed in the edge portion of a first component at predetermined locations and hole apertures are formed in the edge portion of the second component and disposed for confronting alignment with the slot apertures. A connecting sleeve is disposed in each hole aperture and projects through the hole and associated slot and a retention washer is secured over an end of the connecting sleeve on the other side of the second component. A fastener extends through the retention washer and the connecting sleeve to clampingly interconnect the overlapped edge portions of the first and second components. | 08-29-2013 |
20130224012 | GAS TURBINE ENGINE CASE BOSSES - A gas turbine engine case has a metallic composite boss mounted thereto. The boss may have a main metal injection molded (MIM) part, and a separately formed flange part integrated to the main MIM part and projecting laterally outwardly therefrom. The MIM part and the flange part may be made of different materials. The material of the flange part is selected to provide a suitable mounting interface with the gas turbine engine case. | 08-29-2013 |