Patent application number | Description | Published |
20100124492 | TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME - Turbine nozzles and methods of manufacturing the turbine nozzles are provided. In an embodiment, by way of example only, a turbine nozzle includes a first ring, a vane, and a first joint. The first ring comprises a single unitary component and having a first opening and including a first metal alloy. The vane includes a first end disposed in the first opening and includes a second metal alloy. The first joint is formed in the first opening between the first ring and the vane and includes a first braze layer and an oxide layer. The first braze layer is disposed adjacent to the oxide layer, and the first braze layer and the oxide layer are disposed between the first ring and the vane. | 05-20-2010 |
20100307166 | COMBUSTOR-TURBINE SEAL INTERFACE FOR GAS TURBINE ENGINE - A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal. | 12-09-2010 |
20110020118 | TURBINE NOZZLE ASSEMBLY INCLUDING RADIALLY-COMPLIANT SPRING MEMBER FOR GAS TURBINE ENGINE - Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE. | 01-27-2011 |
20110129342 | TURBINE ASSEMBLIES WITH IMPINGEMENT COOLING - A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion. | 06-02-2011 |
20120219808 | PROTECTIVE COATINGS AND COATED COMPONENTS COMPRISING THE PROTECTIVE COATINGS - A coated component is provided comprising a silicon-based substrate and a braze layer overlying the silicon-based substrate. The braze layer comprises silicon, tantalum, and a metal element having substantially the same melt temperature with silicon as tantalum has with silicon. The braze layer further comprises ceramic particles. Protective coatings are also provided. | 08-30-2012 |
20130058768 | GAS TURBINE ENGINES WITH ABRADABLE TURBINE SEAL ASSEMBLIES - A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager. | 03-07-2013 |
20140321965 | TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME - A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. | 10-30-2014 |
20150267550 | TURBINE NOZZLES WITH SLIP JOINTS IMPREGNATED BY OXIDATION-RESISTANT SEALING MATERIAL AND METHODS FOR THE PRODUCTION THEREOF - Embodiments of a turbine nozzle having slip joints impregnated by an oxidation-resistant sealing material are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the method includes providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring. The plurality of vanes extends radially from the support ring into a plurality of circumferentially-spaced slots provided in the slip joint ring to form a plurality of slip joints therewith. The plurality of slip joints are impregnated with a silicon-modified aluminide sealing material. The silicon-modified aluminide sealing material impedes gas flow into the radial slip joints during operation of the turbine nozzle, while also fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints. | 09-24-2015 |