Patent application number | Description | Published |
20120099961 | ROTARY MACHINE HAVING NON-UNIFORM BLADE AND VANE SPACING - A system, including a rotary machine including: a stator, a rotor configured to rotate relative to the stator, wherein the rotor comprises a plurality of blades having a non-uniform spacing about a circumference of the rotor. | 04-26-2012 |
20120099995 | ROTARY MACHINE HAVING SPACERS FOR CONTROL OF FLUID DYNAMICS - A system includes a rotary machine with a fluid flow path extending along an axis of the rotary machine, a plurality of airfoils disposed about the axis, and a plurality of spacers disposed about the axis. Each spacer of the plurality of spacers is disposed circumferentially between adjacent airfoils of the plurality of airfoils to define a circumferential spacing of the airfoils about the axis. | 04-26-2012 |
20120099996 | ROTARY MACHINE HAVING GROOVES FOR CONTROL OF FLUID DYNAMICS - A system includes a rotary machine including, a stator, a rotor configured to rotate relative to the stator, a plurality of axial grooves disposed along a circumference of the stator or the rotor, a plurality of blade segments disposed along the circumference, wherein each blade segment of the plurality of blade segments comprises a blade coupled to a mounting base supported in a respective axial groove of the plurality of axial grooves, and the plurality of blades has a non-uniform blade spacing about the circumference. | 04-26-2012 |
20120181370 | SYSTEM AND METHOD FOR REINFORCING A SUBSTRATE - A system for reinforcing a substrate includes a rotary device, a first guide connected to the rotary device, and a form positioned against the first guide. A reinforcement is supplied to wind around the form and against the first guide. A method for reinforcing a substrate includes connecting a first guide to a rotary device and positioning a form on a first side of the first guide. The method further includes winding a reinforcement around the form and against the first side of the first guide. | 07-19-2012 |
20120237355 | TURBINE BLADE ASSEMBLY - A turbine blade assembly is disclosed. In one embodiment, the turbine blade assembly may generally include a turbine blade having a root portion and an airfoil. The airfoil may extend radially from the root portion to an airfoil tip. Additionally, the turbine blade assembly may include a composite rod extending within the turbine blade. The composite rod may include a first end coupled to the airfoil at the airfoil tip and a second end coupled to the root portion. Moreover, the coefficient of thermal expansion of the composite rod may be designed to be less than or equal to the coefficient of thermal expansion of the airfoil. | 09-20-2012 |
20120275920 | ADAPTOR ASSEMBLY FOR COUPLING TURBINE BLADES TO ROTOR DISKS - An adaptor assembly for coupling a blade root of a turbine blade to a root slot of a rotor disk is disclosed. The adaptor assembly may generally include an adaptor body having a root configured to be received within the root slot. The adaptor body may also define a slot having an open end configured to receive the blade root. The adaptor body may further define a channel. The adaptor assembly may also include a plate having an outwardly extending foot. The foot may be configured to be received within the channel. Additionally, the plate may be configured to cover at least a portion of the open end of the slot when the foot is received within the channel. | 11-01-2012 |
20130094968 | ADAPTOR ASSEMBLY FOR COUPLING TURBINE BLADES TO ROTOR DISKS - An adaptor assembly for coupling a blade root of a turbine blade to a root slot of a rotor disk is described. The adaptor assembly includes a turbine blade having a blade root and an adaptor body having an adaptor root. The adaptor body defines a slot having an open end configured to receive the blade root of the turbine blade such that the adaptor root of the adaptor body and the blade root of the turbine blade are adjacent to one another when the blade root of the turbine blade is positioned within the slot. Both the adaptor root of the adaptor body and the blade root of the turbine blade are configured to be received within the root slot of the rotor disk. | 04-18-2013 |
20130110476 | SYSTEM AND METHOD FOR OBTAINING AND DE-NOISING VIBRATORY DATA | 05-02-2013 |
20130177439 | CREEP RESISTANT COATING FOR CERAMIC TURBINE BLADES - A gas turbine blade having a surface may have a bond layer applied to a first section of the surface, wherein the bond layer is not applied to a second section of the surface. One or more protective layers may be applied such that the protective layers cover and overlap the bond layer making direct contact with an area of the surface immediately outside the first section of the surface and forming a mechanical constraint geometry about the edge of the bond layer. | 07-11-2013 |
20130177440 | Continuous Fiber Reinforced Mesh Bond Coat for Environmental Barrier Coating System - A gas turbine blade may have a bond coat applied to its surface. A porous substrate may be applied to the bond layer and one or more protective layers may be applied to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer to prevent creep. | 07-11-2013 |
20130177441 | Compositional Bond Coat for Hindering/Reversing Creep Degradation in Environmental Barrier Coatings - A gas turbine blade may have a bond coat applied to its surface. The bond coat may include silicon and a reactive material. The reactive material may react with thermally grown oxide generated at the bond layer to prevent and reverse creep. One or more protective layers may be applied to the bond layer. | 07-11-2013 |
20130210299 | REINFORCED COATINGS AND METHODS OF MAKING THE SAME - A reinforced coating for a substrate includes a bond coat layer bonded to a surface of the substrate; an intermediate layer bonded to the bond coat layer; a reinforced layer bonded to the intermediate layer, wherein the reinforced layer comprises a woven fiber mesh disposed in the reinforced layer in a substantially planar position. | 08-15-2013 |
20140003905 | TURBOMACHINE MONITORING SYSTEM AND METHOD | 01-02-2014 |
20140030464 | TURBINE REPAIR PROCESS, REPAIRED COATING, AND REPAIRED TURBINE COMPONENT - A turbine repair process, a repaired coating, and a repaired turbine component are disclosed. The turbine repair process includes providing a turbine component having a higher-pressure region and a lower-pressure region, introducing particles into the higher-pressure region, and at least partially repairing an opening between the higher-pressure region and the lower-pressure region with at least one of the particles to form a repaired turbine component. The repaired coating includes a silicon material, a ceramic matrix composite material, and a repaired region having the silicon material deposited on and surrounded by the ceramic matrix composite material. The repaired turbine component a ceramic matrix composite layer and a repaired region having silicon material deposited on and surrounded by the ceramic matrix composite material. | 01-30-2014 |
20140065433 | 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 a damping coating layer of a coating system that lies on and contacts a substrate of a component and defines an outermost surface of the component. The coating system includes at least a second coating layer contacted by the damping coating layer. The damping coating layer contains a ferroelastic ceramic composition having a tetragonality ratio, c/a, of greater than 1 to 1.02, where “c” is a c axis of a unit cell of the ferroelastic ceramic composition and “a” is either of two orthogonal axes, a and b, of the ferroelastic ceramic composition. | 03-06-2014 |
20140093381 | TURBINE COMPONENT, TURBINE BLADE, AND TURBINE COMPONENT FABRICATION PROCESS - A turbine component, a turbine blade, and a turbine component fabrication process are disclosed. The turbine component includes ceramic matrix composite plies and a feature configured for preventing interlaminar tension of the ceramic matrix composite plies. The feature is selected from the group consisting of ceramic matrix composite tows or precast insert tows extending through at least a portion of the ceramic matrix composite plies, a woven fabric having fiber tows or a precast insert preventing contact between a first set of the ceramic matrix composite plies and a second set of the ceramic matrix composite plies, and combinations thereof. The process includes laying up ceramic matrix composite plies in a preselected arrangement and securing a feature configured for interlaminar tension. | 04-03-2014 |
20140112794 | BLADE ATTACHMENT ASSEMBLY - An assembly and method for affixing a turbomachine rotor blade to a rotor wheel are disclosed. In an embodiment, an adaptor member is provided disposed between the blade and the rotor wheel, the adaptor member including an adaptor attachment slot that is complementary to the blade attachment member, and an adaptor attachment member that is complementary to the rotor wheel attachment slot. A coverplate is provided, having a coverplate attachment member that is complementary to the rotor wheel attachment slot, and a hook for engaging the adaptor member. When assembled, the coverplate member matingly engages with the adaptor member, and retains the blade in the adaptor member, and the assembly in the rotor wheel. | 04-24-2014 |
20140154073 | APPARATUS HAVING ENGINEERED SURFACE FEATURE AND METHOD TO REDUCE WEAR AND FRICTION BETWEEN CMC-TO-METAL ATTACHMENT AND INTERFACE - An apparatus having reduced wear and friction between CMC-to-metal attachment and interface of the apparatus, including a CMC component having a surface. The CMC component surface is configured for sliding contact with a surface of a metal component, the sliding contact resulting in formation of debris along the contacting surfaces. The surface of the CMC component has an engineered surface feature formed therein to substantially prevent an accumulation of debris along the contacting surfaces. | 06-05-2014 |
20140193577 | PRE-FORM CERAMIC MATRIX COMPOSITE CAVITY AND METHOD OF FORMING AND METHOD OF FORMING A CERAMIC MATRIX COMPOSITE COMPONENT - A pre-form CMC cavity and method of forming pre-form CMC cavity for a ceramic matrix component includes providing a mandrel, applying a base ply to the mandrel, laying-up at least one CMC ply on the base ply, removing the mandrel, and densifying the base ply and the at least one CMC ply. The remaining densified base ply and at least one CMC ply form a ceramic matrix component having a desired geometry and a cavity formed therein. Also provided is a method of forming a CMC component. | 07-10-2014 |
20140234117 | APPARATUS AND METHOD TO REDUCE WEAR AND FRICTION BETWEEN CMC-TO-METAL ATTACHMENT AND INTERFACE - An apparatus to reduce wear and friction between CMC-to-metal attachment and interface, including a metal layer configured for insertion between a surface interface between a CMC component and a metal component. The surface interface of the metal layer is compliant relative to asperities of the surface interface of the CMC component. A coefficient of friction between the surface interface of the CMC component and the metal component is about 1.0 or less at an operating temperature between about 300° C. to about 325° C. and a limiting temperature of the metal component. | 08-21-2014 |
20150093237 | CERAMIC MATRIX COMPOSITE COMPONENT, TURBINE SYSTEM AND FABRICATION PROCESS - A ceramic matrix composite component, turbine system and fabrication process are disclosed. The ceramic matrix composite (CMC) component includes a CMC material, an environmental barrier coating (EBC) on the CMC material, and a hard wear coating applied over the EBC. The turbine system includes a rotatable CMC component having a hard wear coating, and a stationary turbine component, the stationary turbine component having an abradable coating arranged and disposed to be cut by the silicon carbide material. The fabrication process includes positioning the rotatable CMC a pre-determined distance from the stationary turbine component and rotating the rotatable CMC component. The hard wear coating on the rotatable CMC component cuts the abradable coating on the stationary turbine component. | 04-02-2015 |
20150147184 | PROCESS OF PRODUCING A CERAMIC MATRIX COMPOSITE TURBINE BUCKET, INSERT FOR A CERAMIC MATRIX COMPOSITE TURBINE BUCKET AND CERAMIC MATRIX COMPOSITE TURBINE BUCKET - A process of producing a ceramic matrix composite turbine bucket, an insert for a ceramic matrix composite turbine bucket, and a ceramic matrix composite turbine bucket are disclosed. The process includes providing a bucket preform having a dovetail cavity, the dovetail cavity being enclosed within a dovetail shank of the bucket preform, positioning an insert within the dovetail cavity, then forming the ceramic matrix composite turbine bucket in a furnace. The insert includes a geometry configured to be fit within a dovetail cavity of the ceramic matrix composite turbine bucket, a bucket preform, or both. The insert is foam material or a plurality of ceramic matrix composite plies. The ceramic matrix composite turbine bucket includes a dovetail shank and a dovetail cavity enclosed within the dovetail shank. The dovetail cavity is arranged and disposed for receiving an insert. | 05-28-2015 |
20150192029 | TURBOMACHINE BLADE TIP INSERT - Embodiments of the present disclosure are directed toward systems including a tip shroud insert having a retained portion configured to be retained within a pocket of a turbomachine blade and an exposed portion configured to form a dynamic seal with a stationary structural component surrounding the turbomachine blade. | 07-09-2015 |
20150345314 | TURBINE BUCKET ASSEMBLY AND TURBINE SYSTEM - A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a non-segmented airfoil having a root section and a tip section integral with the root section, the tip section having a tip end with a second axial length, the second axial length being less than the first axial length; and a turbine wheel having a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The turbine wheel includes a turbine wheel material and the single-lobe joint and the non-segmented airfoil include a turbine bucket material, the turbine bucket material having a higher heat resistance and a lower thermal expansion than the turbine wheel material. | 12-03-2015 |
20150345388 | GAS TURBINE COMPONENT AND PROCESS FOR PRODUCING GAS TURBINE COMPONENT - A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof. | 12-03-2015 |