Patent application number | Description | Published |
20090003993 | Ceramic matrix composite turbine engine vane - A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion. | 01-01-2009 |
20090028697 | LOW TRANSIENT THERMAL STRESS TURBINE ENGINE COMPONENTS - A turbine vane includes a platform; and at least one airfoil mounted to the platform and having a trailing edge and a leading edge, wherein the vane is composed of a functionally graded material having a first material and a second material, wherein the trailing edge includes a greater amount of the first material than the second material, and the leading edge includes a greater amount of the second material than the first material. | 01-29-2009 |
20090208752 | LOW TRANSIENT AND STEADY STATE THERMAL STRESS DISK SHAPED COMPONENTS - A process for manufacturing a disk shaped component comprising fabricating a disk shaped component using a composite material having at least a first material and a second material, wherein the first material is disposed at and proximate to a center portion of the disk shaped component and the second material is disposed at and proximate to a rim of the disk shaped component, wherein the first material comprises a first coefficient of thermal expansion, a first stress value and a first oxidation resistance, and the second material comprises a second coefficient of thermal expansion, a second stress value and a second oxidation resistance, wherein the first coefficient of thermal expansion is greater than the second coefficient of thermal expansion, the first stress value is greater than the second stress value and the first oxidation resistance is less than the second oxidation resistance. | 08-20-2009 |
20090272122 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth. | 11-05-2009 |
20100021290 | Ceramic matrix composite turbine engine vane - A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a coefficient of thermal expansion (CTE) varying with depth. | 01-28-2010 |
20100101232 | COMPLIANT METAL SUPPORT FOR CERAMIC COMBUSTOR LINER IN A GAS TURBINE ENGINE - A combustion system for an engine, such as a gas turbine engine is provided. The combustion system has a ceramic component, such as ceramic combustor liner, and at least one metal support component, such as a metal ring or a plurality of metal cones, for providing radial and axial support to the ceramic component. The at least one metal support component includes a structure, such as axial slots or radial slots, for minimizing stress and for increasing compliance of the metal support component with respect to the ceramic component. | 04-29-2010 |
20100104433 | CERAMIC SHROUD ASSEMBLY - A ceramic shroud assembly suitable for use in a gas turbine engine comprises a metal clamp ring shrink fitted around a ceramic shroud ring and an insulating and compliant interlayer. The interlayer is positioned between the metal clamp ring and the ceramic shroud ring. | 04-29-2010 |
20100170264 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth. | 07-08-2010 |
20100189556 | SEGMENTED CERAMIC MATRIX COMPOSITE TURBINE AIRFOIL COMPONENT - A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates. In one embodiment, the gas path portion comprises an airfoil for a turbine blade. In another embodiment, the gas path portion comprises a removable platform for a turbine blade. In another embodiment, the gas path portion comprises an airfoil for a turbine vane. | 07-29-2010 |
20100242486 | FUEL-COOLED HEAT EXCHANGER WITH THERMOELECTRIC DEVICE COMPRESSION - An apparatus includes an inlet conduit assembly surrounding a gas flow path and a combustor arranged downstream of the inlet conduit assembly. The inlet conduit assembly includes a thermoelectric (TE) device configured to convert heat into electrical energy, a gas flow conduit arranged between the gas flow path and the TE device, and a resilient member configured to bias the TE device into contact with the gas flow conduit. | 09-30-2010 |
20100257864 | 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. | 10-14-2010 |
20100304107 | LAYERED COATING FOR EROSION PROTECTION - A coating for protecting a surface against erosion when contacted by particles having a range of particle sizes or by high velocity fluid impingement includes a first coating on the surface forming a high bulk or composite hardness coating; and a hard ceramic coating on the first coating having a hardness higher than the hardness of the first coating and the erosion particles. | 12-02-2010 |
20110052384 | CERAMIC TURBINE SHROUD SUPPORT - A turbine shroud includes a ceramic shroud ring configured to surround a plurality of turbine rotor blades, a plurality of slots circumferentially distributed around the ceramic shroud ring, a forward metallic support ring, a plurality of tabs attached to a forward edge of the forward metallic support ring configured to engage a turbine support case, and a plurality of tabs attached to an aft edge of the forward metallic support ring received by the slots of the ceramic shroud ring. Only two axially extending radial surfaces of each of the tabs attached to the aft edge of the forward metallic support ring are configured to contact the slots of the ceramic shroud ring. | 03-03-2011 |
20110274538 | CERAMIC GAS TURBINE SHROUD - An example gas turbine engine shroud includes a first annular ceramic wall having an inner side for resisting high temperature turbine engine gasses and an outer side with a plurality of radial slots. A second annular metallic wall is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs in communication with the slot of the first annular ceramic wall. The tabs of the second annular metallic wall and slots of the first annular ceramic wall are in communication such that the first annular ceramic wall and second annular metallic wall are affixed. | 11-10-2011 |
20110287239 | Multilayered Coating For Improved Erosion Resistance - An erosion resistant coating for a substrate includes two or more coating layers affixed to the substrate having an increasing modulus of elasticity and hardness from an innermost layer of the coating adjacent to the substrate to an outermost layer of the coating furthest from the substrate. A method of applying a coating system to a substrate includes applying a first layer of a high hardness and high modulus of elasticity material combined with an added metal to the substrate. A second layer of the high hardness and high modulus of elasticity material combined with the added metal is applied to the first layer, resulting in a coating system wherein the second layer has a modulus of elasticity and hardness greater than the modulus of elasticity and hardness of the first layer. | 11-24-2011 |
20120007286 | LOW TRANSIENT AND STEADY STATE THERMAL STRESS DISK SHAPED COMPONENTS - A process for manufacturing a disk shaped component comprising fabricating a disk shaped component using a composite material having at least a first material and a second material, wherein the first material is disposed at and proximate to a center portion of the disk shaped component and the second material is disposed at and proximate to a rim of the disk shaped component, wherein the first material comprises a first coefficient of thermal expansion, a first stress value and a first oxidation resistance, and the second material comprises a second coefficient of thermal expansion, a second stress value and a second oxidation resistance, wherein the first coefficient of thermal expansion is greater than the second coefficient of thermal expansion, the first stress value is greater than the second stress value and the first oxidation resistance is less than the second oxidation resistance. | 01-12-2012 |
20120070276 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained. | 03-22-2012 |
20120328996 | Reverse Flow Combustor Duct Attachment - A reverse flow combustor has an inlet end. A flowpath extends downstream from the inlet end through a turn. The turn directs the flowpath radially inward and reversing an axial flow direction. A large exit duct (LED) is along the turn. A small exit duct (SED) is along the turn and joined by a joint to a mounting structure to resist separation in a first axial direction. The joint comprises: a first surface on the SED facing partially radially inward; and a mounting feature engaging the first surface. | 12-27-2012 |
20130008176 | GAS TURBINE SHROUD ARRANGEMENT - A system for supporting a shroud used in an engine has a shroud positioned radially outboard of a rotor, which shroud has a plurality of circumferentially spaced slots; a forward support ring for supporting the shroud; the forward support ring having a plurality of spaced apart first tabs on a first side for functioning as anti-rotation devices; the forward support ring having a plurality of spaced apart second tabs on a second side; and the second tabs engaging the slots in the shroud and circumferentially supporting the shroud. | 01-10-2013 |
20130011248 | REDUCTION IN THERMAL STRESSES IN MONOLITHIC CERAMIC OR CERAMIC MATRIX COMPOSITE SHROUD - A shroud for use in a gas turbine engine has a ring with a plurality of protrusions and a plurality of slots and each of the protrusions having an arc length and parallel sides. | 01-10-2013 |
20130011271 | CERAMIC MATRIX COMPOSITE COMPONENTS - A CMC component has an integral airfoil and root portion formed by a plurality of plies extending in a spanwise direction and an external feature formed by a plurality of bent plies. | 01-10-2013 |
20130094946 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud for a gas turbine engine includes a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that break up the leading portion into circumferentially spaced segments separated by the first set of slots, and a trailing portion adjacent to the leading portion. The trailing portion has a trailing edge. | 04-18-2013 |
20140190167 | Ceramic combustor can for a gas turbine engine - A combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween. An air fuel mixer and an igniter are mounted to the support assembly secured to the ceramic combustion can which receives the ignition products of the ignited fuel and air mixture. | 07-10-2014 |
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 |