Matches 1 - 50 out of 81 1 2 >


Match Document Document Title
US20150082798 COMPONENT FOR ATTACHING TO A WALL  
A tile for attaching to a wall of a gas turbine engine. The tile has a main body. The tile also has a bridging structure that projects outwardly from the main body and has a hole configured to...
US20150176843 COMBUSTION CHAMBER  
A double wall structured combustor having an outer wall having an inner surface and an outer surface and an inner wall comprising a plurality of tiles. Each tile has at least one interlocking...
US20140144146 TILE FASTENING ARRANGEMENT OF A GAS-TURBINE COMBUSTION CHAMBER  
The present invention relates to a tile fastening arrangement of a gas-turbine combustion chamber having a combustion chamber wall with tiles fastened to said combustion chamber wall at a distance...
US20120210719 CERAMIC COMBUSTOR LINER PANEL FOR A GAS TURBINE ENGINE  
A combustor assembly includes a support structure and at least one combustor liner panel selectively attached to the support structure. The combustor liner panel includes an uncooled ceramic...
US20120125005 CERAMIC COMBUSTOR LINER PANEL FOR A GAS TURBINE ENGINE  
A combustor assembly includes a support structure and at least one combustor liner panel selectively attached to the support structure. The combustor liner panel includes an uncooled ceramic...
US20140311152 REVERSE FLOW CERAMIC MATRIX COMPOSITE COMBUSTOR  
A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor...
US20130086914 TURBINE SYSTEM  
A turbine system is disclosed. The turbine system includes a transition duct having an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis,...
US20100236250 COMBUSTION CHAMBER BRAZED WITH CERAMIC INSERTS  
A housing for a combustion chamber assembly is provided. The housing includes a wall device made of metal material, and an insert device made of ceramic material. The insert device is attached to...
US20100011776 ELIMINATION OF PLATE FINS IN COMBUSTION BASKETS BY CMC INSULATION INSTALLED BY SHRINK FIT  
A combustor basket (20) is provided comprising a generally tubular wall (22) defining a cavity (24) and a liner (26) of a ceramic matrix composite material disposed within the cavity (24), wherein...
US20080187877 Gasifier liner  
A liner for use within a gasifier vessel includes a plurality of elongated channels and a plurality of ceramic sheaths. The elongated channels pass coolant through the gasifier. The ceramic...
US20110030378 COMBUSTOR TILE MOUNTING ARRANGEMENT  
A tile is provided for lining the hot side of a wall of a combustor. The tile has a tile body with one or more bosses protruding from the cold side thereof. The or each boss extends, in use,...
US20090235667 Gas-turbine combustion chamber with ceramic flame tube  
A gas turbine combustion chamber includes an essentially cylindrical flame tube 2, which is made of a ceramic material and circumferentially divided into several circumferential elements 10, 11, 12.
US20080110175 Cowling for connecting a hot gas source to a stirling engine or a turbine  
Ceramic cowlings that are used as the connection between a hot gas source and a Stirling engine or a turbine. The ceramic cowling is designed and fabricated with non-dusting, high temperature,...
US20140065433 COATINGS FOR DISSIPATING VIBRATION-INDUCED STRESSES IN COMPONENTS AND COMPONENTS PROVIDED THEREWITH  
A coating material suitable for use in high temperature environments and capable of providing a damping effect to a component subjected to vibration-induced stresses. The coating material defines...
US20090193810 Combustion chamber lining  
A combustion chamber for a gas turbine has a metallic supporting structure 6 and several circumferentially distributed ceramic bodies 2 attached to the supporting structure 6. The ceramic bodies 2...
US20070028592 Thermal shield, especially for lining the wall of a combustion chamber  
The aim of the invention is to provide a highly durable, high-strength thermal shield element for the interior lining of the combustion chamber of a gas turbine. For this purpose, the thermal...
US20090260364 Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell  
An apparatus for a gas turbine engine, such as a transition (225, 325), includes a metal shell (200, 300) surrounding a body (230, 330) that is comprised of a ceramic matrix composite...
US20120210718 Plating of ceramic matrix composite parts as joining method in gas turbine hardware  
Method of joining a ceramic matrix composite article to a metallic component by providing the ceramic matrix composite article with a metallic region which bonds to the metallic component.
US20080115495 System and method employing direct gasification for power generation  
A power generation system (10) and method of operating a power generation system (10). An exemplary power generation system (10) shown in FIG. 1 includes a gasification system (2) for generating a...
US20130019603 INSERT FOR GAS TURBINE ENGINE COMBUSTOR  
A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert adjacent to the support shell and the heat shield panel.
US20080104963 Heat Shield Element, Method for Its Production, Hot Gas Lining, and Combustion Chamber  
Disclosed is a thermal shield element comprising a hot side that is to face a hot medium, a cold side which is to face away from the hot medium, circumferential areas that connect the hot side to...
US20090249790 GAS TURBINE COMBUSTION CHAMBER HAVING INNER AND OUTER WALLS SUBDIVIDED INTO SECTORS  
An annular combustion chamber has an inner wall and an outer wall of ceramic matrix composite material, together with a chamber end wall that is connected to the inner and outer walls....
US20110219775 HIGH TOLERANCE CONTROLLED SURFACE FOR CERAMIC MATRIX COMPOSITE COMPONENT  
A ceramic matrix composite (CMC) component includes a hardenable material that can be machined to provide a desired dimension and surface finish.
US20090071160 Wavy CMC Wall Hybrid Ceramic Apparatus  
A ceramic hybrid structure (207, 502, 602, 608) that includes a wavy ceramic matrix composite (CMC) wall (214, 532, 603, 609) bonded with a ceramic insulating layer (230, 538, 604, 610) having a...
US20140360196 SHELL AND TILED LINER ARRANGEMENT FOR A COMBUSTOR  
A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The...
US20120144835 COMBUSTION CHAMBER  
A combustion chamber has an outer wall supporting a number of wall elements or tiles. The tiles are located on the wall by bosses so that a cooling space is provided between the wall and the...
US20100162717 SHIELDING FOR A GAS TURBINE ENGINE COMPONENT  
One embodiment of the present application includes a hot section component of a gas turbine engine having a covering. The covering includes a protrusion and is attached to the hot section...
US20140116057 PUSH-LOCK PIN  
A push-lock pin for connecting a plate to surface includes a cylindrical pin housing and a shaft within the housing. The shaft has a ball-lock mechanism and a push-down pop-up mechanism.
US20110271684 GAS TURBINE ENGINE COMBUSTOR WITH CMC HEAT SHIELD AND METHODS THEREFOR  
A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix...
US20070289307 Heat Shield Element, Method and Mold for the Production Thereof, Hot-Gas Lining and Combustion Chamber  
There is described a heat shield element comprising a hot side which is turned towards the hot medium, a cold side which is turned away from the hot medium, peripheral sides which connect the hot...
US20090100838 WALL ELEMENT FOR USE IN COMBUSTION APPARATUS  
A tile for use as part of an inner wall of a gas turbine engine combustor, the tile being provided with deformable cooling pedestals extending into a space between the tile and the outer wall. The...
US20140165573 PROCESS FOR PRODUCING REFRACTORY CERAMICS FOR GAS TURBINE PLANTS  
A process for producing refractory ceramics (K) for use as heat shield in the hot gas path of gas turbine plants: introducing a casting composition into a component casing mold for the refractory...
US20090293490 Combustor wall with improved cooling  
A combustor for a turbine engine has a cooling ring. The cooling ring has an internal corner that is shaped to cause a flow of hot or fuel rich gas flowing over the wall to separate from the wall....
US20100186365 Heat Shield Element, in Particular for Lining a Combustion Chamber Wall  
A highly durable, high-strength thermal shield element is provided for the interior lining of the combustion chamber of a gas turbine. For this purpose, the thermal shield element comprises a base...
US20130152591 SYSTEM OF INTEGRATING BAFFLES FOR ENHANCED COOLING OF CMC LINERS  
A system of integrating baffles for enhanced cooling of CMC liners is comprised of a combustor assembly having a dome mount assembly, outer liner and inner liner. Liners include those manufactured...
US20150247640 RETAINING ELEMENT FOR RETAINING A HEAT SHIELD TILE AND METHOD FOR COOLING THE SUPPORTING STRUCTURE OF A HEAT SHIELD  
A retaining element (22, 54) for retaining a heat shield tile on a supporting structure: A fastening section (23) fastened to the supporting structure. A retaining section (24) having a retaining...
US20130025291 SYSTEM AND METHOD FOR PROTECTION OF HIGH TEMPERATURE MACHINERY COMPONENTS  
A system comprises a plurality of components disposed to define a gas path. At least one component comprises a silicon-bearing substrate over which is disposed a coating, and the coating comprises...
US20100251721 Stacked laminate gas turbine component  
A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process...
US20170176007 ARTICLE HAVING MULTI-LAYERED COATING  
An article such as a heat shield panel includes a substrate and a multi-layered coating supported on the substrate. The multi-layered coating can include alternating layers of different ceramic...
US20170159460 ENHANCED ADHESION THERMAL BARRIER COATING  
A gas turbine engine including a compressor section, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a plurality...
US20170146241 SHELL AND TILED LINER ARRANGEMENT FOR A COMBUSTOR  
A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The...
US20170138597 COMBUSTOR TILE WITH MONOLITHIC INSERTS  
An annular assembly for a gas turbine engine and a method of making the annular assembly. The annular assembly comprises a supporting member comprising metal and including a support hole...
US20170138596 LINER FOR A COMBUSTOR OF A GAS TURBINE ENGINE  
A liner for a combustor includes a support member, an intermediate member, and a liner member. The intermediate member is positioned intermediate the support member and the liner member and has a...
US20170089579 CMC ARTICLES HAVING SMALL COMPLEX FEATURES FOR ADVANCED FILM COOLING  
An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface...
US20170089578 CMC ARTICLES HAVING SMALL COMPLEX FEATURES FOR ADVANCED FILM COOLING  
An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface...
US20170059167 COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE  
A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and...
US20170059166 COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE  
A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and...
US20170059160 COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE  
A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end...
US20170059159 CMC COMBUSTOR SHELL WITH INTEGRAL CHUTES  
A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the...
US20170051917 CASE AND LINER ARRANGEMENT FOR A COMBUSTOR  
A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic case forming a cavity and a ceramic liner arranged in the cavity of the metallic case. The...

Matches 1 - 50 out of 81 1 2 >