Patent application number | Description | Published |
20120219404 | TURBINE SHROUD AND A METHOD FOR MANUFACTURING THE TURBINE SHROUD - A turbine shroud includes a body having a plurality of sides. A first inward facing groove is defined by a first side of the body, and a first seal covers the first inward facing groove to define a first fluid passage in the first inward facing groove along the first side of the body. A first inlet port through the first seal fluid communication through the first seal into the first fluid passage. A method for forming a turbine shroud includes forming an inner surface and forming an outer surface opposed to the inner surface, wherein the outer surface is configured for exposure to a hot gas path. The method further includes defining a first slot in the inner surface and extending a first seal across the first slot to define a first fluid passage in the first slot along the inner surface. | 08-30-2012 |
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 |
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 |
20130177386 | TURBINE ASSEMBLY AND METHOD FOR CONTROLLING A TEMPERATURE OF AN ASSEMBLY - According to one aspect of the invention, a turbine assembly includes a first component, a second component circumferentially adjacent to the first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to abut a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first side surface, a second slot formed longitudinally in the second side surface, wherein the first and second slots are configured to receive a sealing member, and a first groove formed in a hot side surface of the first slot, the first groove extending axially from a leading edge to a trailing edge of the first component. | 07-11-2013 |
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 |
20130177412 | Gas Turbine Stator Assembly - According to one aspect, a turbine assembly includes a second component circumferentially adjacent to a first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to be joined to a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first component which extends from a first slot inner wall to the first side surface and a second slot formed longitudinally in the second component which extends from a second slot inner wall to the second side surface. The assembly also includes a first groove formed in a hot side surface of the first slot, the first groove extending from the first slot inner wall to the first side surface, wherein the first groove comprises a tapered cross-sectional geometry. | 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 |
20130287546 | TURBINE SHROUD COOLING ASSEMBLY FOR A GAS TURBINE SYSTEM - A turbine shroud cooling assembly for a gas turbine system includes an outer shroud component disposed within a turbine section of the gas turbine system and proximate a turbine section casing, wherein the outer shroud component includes at least one airway for ingesting an airstream. Also included is an inner shroud component disposed radially inward of, and fixedly connected to, the outer shroud component, wherein the inner shroud component includes a plurality of microchannels extending in at least one of a circumferential direction and an axial direction for cooling the inner shroud component with the airstream from the at least one airway. | 10-31-2013 |
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 |
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 |
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 |
20140338772 | ACTIVE SEALING MEMBER - A sealing member, a component including a sealing member, and a method of sealing a hole are disclosed. In an embodiment, the sealing member includes a plug member for occluding a hole in a wall of a passageway. The plug member includes at least one cooling feature disposed on a distal end of the plug member exposed to the passageway. | 11-20-2014 |
20140341724 | STATIC CORE TIE RODS - A core tie having a varying cross sectional diameter, a component including such a core tie, and a method of casting a hot gas path component for a turbomachine are provided herein. In an embodiment, the core tie includes a tie member having an axial length; and a cross sectional diameter which varies along the axial length of the tie member. A variation in the cross sectional diameter of the tie member positively secures a position of the core tie relative to the core. | 11-20-2014 |
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 |
20150013345 | GAS TURBINE SHROUD COOLING - A shroud segment for a casing of gas turbine includes a body configured for attachment to the casing proximate a localized critical process location within the casing. The body has a leading edge, a trailing edge, and two side edges. The critical process location is located between the leading edge and the trailing edge when the body is attached to the casing. A cooling passage is defined in the body along one of the side edges with one of an inlet or an outlet proximate the critical process location. The cooling passage is configured large enough to cool the one side edge adjacent the cooling passage to a desired level during operation of the gas turbine. The critical process locations may be related to temperatures, pressures or other measurable features of the gas turbine environment when in use. | 01-15-2015 |