Class / Patent application number | Description | Number of patent applications / Date published |
060753000 | Ceramic | 40 |
20090071160 | Wavy CMC Wall Hybrid Ceramic Apparatus - A ceramic hybrid structure ( | 03-19-2009 |
20090193810 | Combustion chamber lining - A combustion chamber for a gas turbine has a metallic supporting structure | 08-06-2009 |
20090235667 | Gas-turbine combustion chamber with ceramic flame tube - A gas turbine combustion chamber includes an essentially cylindrical flame tube | 09-24-2009 |
20090249790 | 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. Elastically-deformable link elements connect the inner wall and the outer chamber walls to inner and outer metal casings. Each of the inner and outer chamber walls is subdivided circumferentially into adjacent sectors along longitudinal edges, each sector extending continuously from the end wall to the opposite end of the chamber and being folded outwards from the chamber at each of its longitudinal edges to form a portion having a U-shaped cross-section terminated by a folded-back margin that is spaced apart from the outer face of the corresponding chamber wall. The link elements are connected to the inner and outer chamber walls by being fastened to the sector margins. | 10-08-2009 |
20090260364 | 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 ( | 10-22-2009 |
20090293490 | 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. The efficiency of the cooling ring is improved. | 12-03-2009 |
20100011776 | ELIMINATION OF PLATE FINS IN COMBUSTION BASKETS BY CMC INSULATION INSTALLED BY SHRINK FIT - A combustor basket ( | 01-21-2010 |
20100162717 | 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 component though a flexible retainer. In one form the covering is made from ceramic matrix composite. The flexible retainer has a closed position and an open position. The retainer secures the protrusion to the hot section component when it engages part of the protrusion when in the closed position. | 07-01-2010 |
20100236250 | 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 the wall device such that the insert device forms a part of an inner wall of the housing and the wall device forms an outer wall of the housing. | 09-23-2010 |
20100251721 | 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 of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material. | 10-07-2010 |
20110030378 | 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, through the wall of the combustor and has a threaded recess formed therein for threadingly connecting with a bolt which is inserted into the recess from the cold side of the combustor wall. The bolt fastens the tile to the combustor wall. | 02-10-2011 |
20110219775 | 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. | 09-15-2011 |
20110271684 | 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 composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement. | 11-10-2011 |
20120125005 | 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 portion, a cooled ceramic portion and a support that receives the cooled ceramic portion. | 05-24-2012 |
20120210718 | 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. | 08-23-2012 |
20120210719 | 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 portion, a cooled ceramic portion and a support that receives the cooled ceramic portion. | 08-23-2012 |
20130086914 | 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, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The turbine system further includes a turbine section connected to the transition duct. The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures. | 04-11-2013 |
20130152591 | 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 from and in a process for CMC (Ceramic Matrix Composite). One or more liner baffles such as outer baffle and inner baffle, are provided to reduce the pressure drop across the liner, allowing the addition of more cooling holes and thereby reducing the cooling hole spacing while not increasing the required amount of cooling air. CMC liners are incorporated, as desired, to take advantage of shapes and hole dispositions made possible by use of CMC over past designs. | 06-20-2013 |
20140116057 | 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. | 05-01-2014 |
20140144146 | 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 from the latter, characterized in that the tile is provided with an annular flange arranged on its side assigned to the combustion chamber wall, said flange being dimensioned to match a recess of the combustion chamber wall and fastened to the combustion chamber wall by means of a fastening element which engages in the combustion chamber wall. | 05-29-2014 |
20140165573 | 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 ceramic (K), closing the casting mold so that the casting composition is under a defined static pressure after closure; orienting vibration of the casting mold in the direction (V) of a normal (N) to a surface of the refractory ceramic (K) to be produced, and subsequently removing the casting from the mold and firing the cast component. | 06-19-2014 |
20140311152 | 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 and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite. | 10-23-2014 |
20140360196 | 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 ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber. | 12-11-2014 |
20150082798 | 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 receive an elongate fastener so that the tile can be attached to the wall of the gas turbine engine by passing the elongate fastener through a hole in the wall of the gas turbine engine and the hole in the bridging structure. | 03-26-2015 |
20150300645 | COMBUSTION CHAMBER ARRANGEMENT - A combustion chamber arrangement including an outer wall and an inner wall spaced from the outer wall and the outer wall supports the inner wall. The inner wall including at least one row of circumferentially arranged tiles. At least one tile in the at least one row of tiles having an L, or V, shaped downstream end and the downstream end of the tile in the row of tiles having a first portion extending from the downstream end of the tile towards and sealing with an inner surface of the outer wall and a second portion extending from the first portion in a downstream direction and away from the inner surface of the outer wall. The first portion of the downstream end of the tile having a plurality of apertures to supply coolant over an inner surface of the second portion of the downstream end of the tile. | 10-22-2015 |
20150330633 | SHELL AND TILED LINER ARRANGEMENT FOR A COMBUSTOR - A combustor for use in a gas turbine engine includes a liner with a plurality of tiles coupled to a shell via a plurality of fasteners. Each of the plurality of fasteners extends through at least one of the tiles. | 11-19-2015 |
20150345790 | ATTACHMENT OF CERAMIC MATRIX COMPOSITE PANEL TO LINER - A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed. | 12-03-2015 |
20160010862 | ANNULAR COMBUSTION CHAMBER WALL ARRANGEMENT | 01-14-2016 |
20160047549 | CERAMIC MATRIX COMPOSITE COMPONENTS WITH INSERTS - A gas turbine engine is disclosed that includes a compressor, a combustor, and a turbine. The turbine includes a turbine shroud having a blade track formed from a ceramic matrix composite material. The combustor includes a combustor liner formed from one or more ceramic matrix composite tiles. | 02-18-2016 |
20160109129 | HEAT SHIELD TILE FOR A HEAT SHIELD OF A COMBUSTION CHAMBER - A heat shield tile detachably arranged on a bearing structure of a heat shield by at least one retaining element. The heat shield tile has a cold side facing the bearing structure, a hot side, arranged opposite the cold side and to which hot gases can be applied, and lateral surfaces that connect the cold side to the hot side. The heat shield tile reduces the amount of cooling air needed to flush the expansion gaps between the heat shield tiles of the heat shield. The heat shield tile has a main body and a number of segments. The segments are arranged adjacent to each other on the main body over the entire area of the main body such that expansion gaps are left. The segments are joined to the main body, such that at least the hot side of the heat shield tile is substantially formed by the segments. | 04-21-2016 |
20160153659 | GAS TURBINE ENGINE CERAMIC COMPONENT ASSEMBLY AND BONDING MATERIAL | 06-02-2016 |
20160161121 | GAS TURBINE ENGINE WITH CERAMIC PANEL - A gas turbine engine ceramic panel assembly includes a ceramic liner that has a slot and includes a hole. An insert is received in the slot and provides a female fastening element aligned with the hole. A method of manufacturing a ceramic panel assembly includes the steps of forming a ceramic liner with a slot, installing an insert into the slot, and securing the ceramic liner to a structure using a fastening assembly. | 06-09-2016 |
20160178198 | GAS TURBINE COMBUSTION CHAMBER WITH MODIFIED WALL THICKNESS | 06-23-2016 |
20160185666 | PRODUCT HAVING A HIGH ALUMINA CONTENT - A sintered refractory product having the form of a block and consisting—of a granulate formed by all the grains having a size larger than 100 μm, referred to as “coarse grains”, and—a matrix binding said coarse grains and consisting of the grains having a size smaller than or equal to 100 μm, the granulate representing between 45% and 90% by mass of the product, said product having a composition such that, in a mass percentage based on the oxides: —Al2O3>80%, —SiO2<15%, —Na2O<0.15% —Fe2O3<0.05%, —CaO<0.1%,—the other oxides forming the remainder up to 100%, the Na2O content in the matrix being greater than 0.010%, in a mass percentage based on the mass of the product. | 06-30-2016 |
20160186999 | RETENTION SYSTEM FOR GAS TURBINE ENGINE ASSEMBLIES - A combustor of a gas turbine engine and a turbine shroud for a turbine of a gas turbine engine are disclosed. The combustor is configured to ignite a mixture of compressed air and fuel in a combustion chamber included therein. The turbine shroud is configured to direct products of the combustion reaction toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate. | 06-30-2016 |
20160201910 | PROTECTIVE PANEL AND FRAME THEREFOR | 07-14-2016 |
20160201911 | COMBUSTOR BULKHEAD HEAT SHIELD | 07-14-2016 |
20160252248 | ATTACHMENT ASSEMBLY FOR PROTECTIVE PANEL | 09-01-2016 |
20160252250 | INTERNAL THERMAL COATINGS FOR ENGINE COMPONENTS | 09-01-2016 |
20160377292 | COMBUSTION SYSTEMS - A combustor for a gas turbine engine includes an inner combustor wall and an outer combustor wall radially outboard of the inner combustor wall. The inner and outer combustor walls define a combustion space therebetween with an upstream inlet and a downstream outlet. A combustor dome connects between inner and outer combustor walls at the upstream inlet of the combustion space. The combustor dome includes a plurality of circumferentially spaced apart nozzles and a plurality of tiles mounted to the combustor dome to fluidly separate a downstream side of the combustor dome from an upstream side of the combustor dome. | 12-29-2016 |