Patent application number | Description | Published |
20100072710 | Gas Turbine Seal - A seal is provided for sealing two adjacent components of a gas turbine engine. The seal has first and second sealing surfaces that operate to seal the adjacent components to create an effective seal therebetween. Additionally, the seal has a first end and a second end, with the second end having a necked down portion, which is configured to internally engage the first end in a sliding, overlapping manner. | 03-25-2010 |
20100247300 | REDUCING INTER-SEAL GAP IN GAS TURBINE - A device for reducing inter-seal gap in gas turbines. Embodiments of a gas turbine with a first arcuate component adjacent to a second arcuate component; a first slot and a connected second slot on an end of the first arcuate component; a first seal disposed into the first slot and a first adjacent slot on the second arcuate component; a second seal disposed into the second slot and a second adjacent slot on the second arcuate component, leaving a gap between the first seal and the second seal; and a connector coupled to the first seal and the second seal and substantially covering the gap between the first seal and the second seal. | 09-30-2010 |
20110241297 | INTEGRAL SEAL AND SEALANT PACKAGING - An integral seal and sealant package includes a prefabricated seal element having multiple surfaces; a high-temperature sealant composition engaged with one or more of the multiple surfaces; and a backer material enclosing the prefabricated seal element and the high-temperature sealant composition. The backer material has composition permitting the backer material to be installed with the seal element and the sealant composition between adjacent components to be sealed. | 10-06-2011 |
20120189435 | ASSEMBLY FOR PREVENTING FLUID FLOW - According to one aspect of the invention, an assembly for preventing fluid flow between turbine components includes a shim and a first woven wire mesh layer that includes a first surface coupled to a first side of the shim and a second surface of the woven wire mesh layer opposite the first surface. The assembly also includes a first outer layer coupled to the second surface of the woven wire mesh layer, where the first outer layer includes a high temperature non-metallic material. | 07-26-2012 |
20130106066 | LAYERED SEAL FOR TURBOMACHINERY | 05-02-2013 |
20130134678 | SHIM SEAL ASSEMBLIES AND ASSEMBLY METHODS FOR STATIONARY COMPONENTS OF ROTARY MACHINES - A seal assembly for a rotary machine is provided. The seal assembly includes a shim seal including multiple seal plates forming a C-shaped shim seal or a box shaped shim seal. The C-shaped shim seal includes a first side portion having a smaller width than that of an opposing second side portion, and the second side portion of the C-shaped shim seal includes a gap between at least two straight faces with an inward angle for allowing positioning within the slot between stator components. The box shaped seal includes a plurality of cuts at two opposing sides or corners for allowing high pressure fluid to occupy the cavity of the box-shaped shim seal. The seal may be inserted within one or more slots between adjacent stator components of the rotary machine. | 05-30-2013 |
20130136609 | TURBINE NOZZLE AIRFOIL PROFILE - A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
20130161914 | ENHANCED CLOTH SEAL - The embodiments described herein provide a cloth seal for use with turbine components. The cloth seal includes first and second cloth layers. One or more central shims are positioned between the first and second cloth layers so as to block a leakage flow path. Another shim is positioned on and seals the opposite side of the first cloth layer from the one or more central shims positioned between the first and second cloth layers so as to block another leakage flow path. Yet another sealing shim may be positioned on the opposite side of the second cloth layer from the one or more central shims positioned between the first and second cloth layers to as to seal the opposite side of the second cloth layer and block another leakage flow path. | 06-27-2013 |
20130177411 | SYSTEM AND METHOD FOR SEALING A GAS PATH IN A TURBINE - A system for sealing a gas path in a turbine includes a stator ring segment, a shroud segment adjacent to the stator ring segment, and a first load-bearing surface between the stator ring segment and the shroud segment. A first non-metallic gasket is in contact with the first load-bearing surface between the stator ring segment and the shroud segment. A method for sealing a gas path in a turbine includes placing a non-metallic gasket between any two of a stator ring segment, a shroud segment, and a casing. | 07-11-2013 |
20130272870 | MICA-BASED SEALS FOR GAS TURBINE SHROUD RETAINING CLIP - A gas turbine, a gas turbine shroud, and a method for sealing a gas turbine shroud with a non-metallic seal are provided. The gas turbine shroud includes an inner shroud and an outer shroud. A non-metallic seal is located between the inner shroud and the outer shroud while a shroud retainer clip applies a compression force upon the inner shroud and the outer shroud. The compression force compresses the non-metallic seal to fill a gap space between the inner shroud and the outer shroud to control fluid flow between a flow path and a non-flow path. | 10-17-2013 |
20140062032 | SPRING-LOADED SEAL ASSEMBLY - A seal assembly is provided. The seal assembly includes a first outer shim and a second outer shim The second outer shim is operably coupled to the first outer shim and comprises at least one substantially impermeable portion that spans across a gap between at least two turbomachine components. The second outer shim further engages the at least two turbomachine components to substantially seal the gap. The substantially impermeable portion is substantially planar at least along a width of the seal assembly. The seal assembly further includes a resilient member that is either coupled to at least a portion of an outer surface of the first outer shim or comprises an integral portion of the first outer shim The resilient member engages the seal assembly to contact bottom surfaces of a cavity defined between the at least two turbomachine components. | 03-06-2014 |
20140062034 | GAS PATH LEAKAGE SEAL FOR A TURBINE - A gas path leakage seal for a turbine includes a flexible manifold having opposed raised edges; at least one cloth seal layer on one side of the manifold between the opposed raised edges; and a filter material covering at least one end of the at least one cloth seal layer. | 03-06-2014 |
20140091531 | SPLINE SEAL WITH COOLING PATHWAYS - The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path. | 04-03-2014 |
20140099183 | TURBINE COMPONENTS WITH PASSIVE COOLING PATHWAYS - The present application provides a turbine component for use in a hot gas path of a gas turbine. The turbine component may include an outer surface, an internal cooling circuit, a number of cooling pathways in communication with the internal cooling circuit and extending through the outer surface, and a number of adaptive cooling pathways in communication with the internal cooling circuit and extending through the outer surface. The adaptive cooling pathways may include a high temperature compound therein. | 04-10-2014 |
20140154062 | SYSTEM AND METHOD FOR SEALING A GAS PATH IN A TURBINE - A seal for placement in a slot between two turbine components of a gas turbine to seal a gap between the components may include a sealing element sized so as to be capable of placement within the slot and of substantially sealing the gap during operation of the gas turbine. A sacrificial coating may be located on the sealing element. The sacrificial coating may be configured with a size substantially conforming to a size of the slot, the sacrificial coating including a material that is removable from the sealing element via heating to a temperature achieved during operation of the gas turbine. Related gas turbine assemblies and methods of assembly are also disclosed. | 06-05-2014 |
20140348642 | CONJOINED GAS TURBINE INTERFACE SEAL - A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an āLā-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer. | 11-27-2014 |
20150059357 | METHOD AND SYSTEM FOR PROVIDING COOLING FOR TURBINE COMPONENTS - A system for providing cooling for a turbine component that includes an outer surface exposed to combustion gases is provided. A component base includes at least one fluid supply passage coupleable to a source of cooling fluid. At least one feed passage communicates with the at least one fluid supply passage. At least one delivery channel communicates with the at least one feed passage. At least one cover layer covers the at least one feed passage and the at least one delivery channel, defining at least in part the component outer surface. At least one discharge passage extends to the outer surface. A diffuser section is defined in at least one of the at least one delivery channel and the at least one discharge passage, such that a fluid channeled through the system is diffused prior to discharge adjacent the outer surface. | 03-05-2015 |
20150068629 | THREE-DIMENSIONAL PRINTING PROCESS, SWIRLING DEVICE AND THERMAL MANAGEMENT PROCESS - A three-dimensional printing process, a swirling device, and a thermal management process are disclosed. The three-dimensional printing process includes distributing a material to a selected region, selectively laser melting the material, and forming a swirling device from the material. The swirling device is printed by selective laser melting. The thermal management process includes providing an article having a swirling device printed by selective laser melting, and cooling a portion of the article by transporting air through the swirling device. | 03-12-2015 |