Match Document Document Title
US20140271220 EROSION RESISTANT COATING  
A platinum plus chromium coating applied to the roots and firtrees of turbine blades where the inclusion of chromium creates a single phase outer zone which minimises diffusion paths for sulphur...
US20150147185 TURBINE BUCKETS WTIH HIGH HOT HARDNESS SHROUD-CUTTING DEPOSITS  
Turbine buckets include a pressure side, a suction side opposite the pressure side, and a bucket squealer tip attached to the pressure side and the suction side. The bucket squealer tip includes a...
US20140301861 AIRFOIL HAVING AN EROSION-RESISTANT COATING THEREON  
A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the...
US20110052406 AIRFOIL AND PROCESS FOR DEPOSITING AN EROSION-RESISTANT COATING ON THE AIRFOIL  
A process for depositing coatings, and particularly erosion-resistant coatings suitable for protecting surfaces subjected to collisions with particles, such as a compressor blade of a gas turbine...
US20110217178 TURBINE AIRFOIL HAVING OUTBOARD AND INBOARD SECTIONS  
A turbine airfoil usable in a turbine engine and formed from at least an outboard section and an inboard section such that an inner end of the outboard section is attached to an outer end of the...
US20090162199 SELF LOCKING TRIM TAB  
A trim tab assembly includes first and second shape memory alloy (SMA) actuators and a trim tab substrate which provide elastic/plastic locking in response to an induced strain actuation.
US20130078084 AIRFOIL AIR SEAL ASSEMBLY  
An air seal assembly for a gas turbine engine the air seal comprises a first assembly and a second assembly. One of the first assembly and the second assembly is rotatable relative to the other of...
US20130115097 CORROSION-RESISTANT DIFFUSION COATINGS  
A metal article such as a gas turbine component may include a super-diffusion coating with unusually high content of the desired constituent. The coating may be provided by combining two or more...
US20130323074 FRICTION WELDED TURBINE DISK AND SHAFT  
An assembly for use in a turbine of a gas turbine engine includes a turbine disk and a shaft. The turbine disk comprises a superalloy. The shaft is friction welded to the turbine disk at a shaft...
US20130058791 PROTECTIVE COATING FOR TITANIUM LAST STAGE BUCKETS  
Described herein a bucket for use in the last stage of a steam turbine engine. The bucket includes a titanium-based alloy having a leading edge wherein the leading edge includes titania having a...
US20120294729 COLD METAL TRANSFER HARDFACING OF BUCKETS  
In one embodiment, the invention provides a method of hardfacing a portion of a bucket subject to mechanical stress, the method comprising: contacting a surface of a bucket with a hardfacing...
US20120003102 DENSE VERTICALLY CRACKED THERMAL BARRIER COATINGS  
This invention relates to dense, vertically cracked thermal barrier coatings made from high purity yttria or ytterbia stabilized zirconia powders. The high purity yttria or ytterbia stabilized...
US20140311149 GAS TURBINE ENGINE FAN BLADE AIRFOIL PROFILE  
A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a...
US20140334939 HIGH PURITY POWDERS  
This invention relates to high purity yttria or ytterbia stabilized zirconia powders comprising from about 0 to about 0.15 weight percent impurity oxides, from about 0 to about 2 weight percent...
US20130294926 ANTIFOULING FILM, AIR BLOWER BLADE PROVIDED WITH SAME, AIR BLOWER, AND ANTIFOULING COATING MATERIAL  
An antifouling film is coated on a base, and contains a binder component, conductive particles, and a fluororesin. The conductive particles are bound together by the binder component; the binder...
US20130121839 TURBINE AIRFOIL AND METHOD FOR THERMAL BARRIER COATING  
A turbine airfoil including an airfoil body is disclosed. The airfoil includes a leading edge, a trailing edge, an exterior surface including a suction side extending from the leading edge to the...
US20140161624 METHOD FOR PRODUCING A RUN-IN COATING, A RUN-IN SYSTEM, A TURBOMACHINE, AS WELL AS A GUIDE VANE  
A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a...
US20110293438 PUMP WITH AXIAL CONDUIT  
In one aspect, a pump for moving air includes an inlet, an outlet, an outer housing adapted to couple to an inflatable device, and an inner housing located within the outer housing. An air conduit...
US20130177440 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...
US20130177441 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...
US20110084174 PASSIVE ADAPTIVE STRUCTURES  
Morphing an aerodynamic body's geometry in situ can optimize its aerodynamic properties, increasing range, reducing fuel consumption, and improving many performance parameters. The aerodynamic...
US20110033308 TITANIUM SHEATH AND AIRFOIL ASSEMBLY  
An airfoil assembly includes an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side. A first sheath having an outer side and an inner side forms a...
US20110085912 PROPELLER FOR A WIND MOTOR  
A propeller (1) for a wind motor (12), wherein: the propeller (1) is rotatable about a rotation axis (2) which is inclined by an angle of essentially 45 degrees with respect to the horizontal...
US20110162374 ARTICLES HAVING DAMPING COATINGS THEREON  
An article, such as a bucket, a blade, a nozzle, a vane, a strut, a fuel nozzle, a combustion casing, and a transition piece, the article having a damping coating comprising approximately 8 wt %...
US20140056578 Heating Fan  
A heating fan has a fastening means for fastening of said fan to a first surface. A stem connects the fastening means to a hub. The hub has a motor unit. The motor unit rotates a plurality of...
US20130108461 PROPELLER FAN AND MANUFACTURING METHOD THEREOF  
A propeller fan molded by injection molding using a resin material containing a continuous fiber, includes a hub having an end surface wall and a peripheral wall; and a plurality of blades on an...
US20110076152 VENTILATOR WHEEL OR FAN WHEEL WITH ANTIBACTERIAL COATING  
The present invention relates to a ventilator wheel or fan wheel composed of a hub and blades which are fastened in said hub. The hub and/or the blades are at least partially provided, on the...
US20110229321 VORTEX DYNAMICS TURBINE  
The invention relates to the use of Air and Hydro Turbines for power generation. It seeks to enhance the energy-capturing potential of air/water turbines, and hence expand the geography where they...
US20140199175 GAS TURBINE ENGINE COMPONENTS AND METHODS FOR THEIR MANUFACTURE USING ADDITIVE MANUFACTURING TECHNIQUES  
In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3D design model for the component, adding one or...
US20110206533 REPAIR OF A COATING ON A TURBINE COMPONENT  
A method is provided for repairing an area of damaged coating on a component of a turbine module in a gas turbine engine, the component formed of a base material having a diffusion coating applied...
US20140072442 NEAR-INFRARED RADIATION CURABLE MULTILAYER COATING SYSTEMS AND METHODS FOR APPLYING SAME  
Multilayer coating systems, methods of applying and related substrates are disclosed. The coating system may comprise a first coating comprising a near-IR absorber, and a second coating deposited...
US20130149163 Method for Reducing Stress on Blade Tips  
A turbine engine component has an airfoil portion with a tip portion and the tip portion has at least one chamfered edge on one side. If desired, the tip portion may have a first chamfered edge on...
US20150044444 METHOD OF FORMING THERMAL BARRIER COATING, THERMAL BARRIER COATING FORMED THEREBY, AND ARTICLE COMPRISING SAME  
A thermal barrier coating that includes a YAG-based ceramic is prepared by a solution precursor plasma spray method that includes injecting a precursor solution into a thermal jet, evaporating...
US20150044059 AIRFOIL FOR A TURBINE SYSTEM  
An airfoil includes a main portion formed of a base material. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising at...
US20130121823 CHROMIUM ALLOY  
A hypereutectic chromium alloy consisting of 9 to 12 at % tantalum, 4 to 15 at % silicon, 0 to 7 at % molybdenum, 0 to 7 at % aluminium, 0 to 7 at % titanium, 0 to 5 at % rhenium, 0 to 2 at %...
US20110081251 FREE-STANDING, IMMERSIBLE POWER GENERATION PLANT COMPRISING AN AXIAL TURBINE  
The invention relates to an immersible power generation plant driven by a water flow, particularly a tidal current, comprising a water turbine in the form of an axial turbine with an associated...
US20080178593 Compressor wheel for a turbocharger system  
A turbocharger system for an internal combustion engine includes at least one compressor wheel. The at least one compressor wheel of a single stage or multiple stage turbocharger system is formed,...
US20120020804 TURBINE NOZZLE SEGMENT HAVING ARCUATE CONCAVE LEADING EDGE  
Turbine nozzle segments with trimmed leading edges are disclosed. In one embodiment of the invention, a turbine static nozzle airfoil includes: an arcuate concave leading edge; and a substantially...
US20140064981 Ni Base Forged Alloy and Gas Turbine Utilizing the Same  
An Ni base forged alloy is easy to make hot forging and miniaturization of crystal grains while excellent high-temperature strength and segregation property are compatible. The Ni base forged...
US20140119941 CREEP-RESISTANT, RHENIUM-FREE NICKEL BASE SUPERALLOY  
Disclosed is a nickel base alloy which is substantially free of rhenium and has a solidus temperature of more than 1320° C. Precipitates of a γ′-phase are present in a γ-matrix with a fraction of...
US20150198047 Mistuned Airfoil Assemblies  
A mistuned airfoil assembly for a gas turbine engine is disclosed. The mistuned airfoil assembly may comprise a hub and airfoils extending radially from the hub. The airfoils may consist of first...
US20120027617 TURBINE NOZZLE SEGMENT AND METHOD OF REPAIRING SAME  
A method is provided for repairing a metallic turbine component which includes at least two airfoils interconnected by a mid-span shroud. The method includes: (a) applying a reinforcement plate to...
US20110223019 SYSTEM AND METHOD FOR COLLECTING PARTICLES IN A WIND TURBINE ROTOR BLADE  
A particle trap for collecting loose particles includes a container having an enclosure and at least one opening, and a feed hopper, wherein the feed hopper is connected to the at least one...
US20150260165 ICE-RESISTANT PAINT FOR WIND TURBINE BLADES  
Ice-resistant paint for wind turbine blades comprising a paint base, which in turn comprises a solvent and a hydrophobe component, which comprises nanoparticles, in which the base paint is a...
US20150132143 WELDING PROCESS AND REDUCED RESTRAINT WELD JOINT  
A weld joint (30) having asymmetric sides and providing reduced restraint of weld metal shrinkage and a reduced propensity for weld centerline cracking. The weld joint may have a first side (38)...
US20110123348 FAN AND PROPELLER PERFORMANCE ENHANCEMENTS USING OUTSIZED GURNEY FLAPS  
The present invention relates to enhancing performance of fans and propellers using outsized Gurney flaps. Specifically, the current invention proposes the application of ‘outsized Gurney flaps’...
US20130230406 Corrosion Resistant Articles  
Gas turbine engine turbine blade includes a silicon-modified aluminide coating on at least an under platform region formed from a slurry composition being substantially free of hexavalent...
US20130336776 CLOSED IMPELLER WITH A COATED VANE  
A closed impeller has a base cover, which has a base interior surface, and a second cover. A vane, which has an inlet distal end and an outlet distal end, is on the base interior surface. The vane...
US20140064982 Ni Base Alloy and Gas Turbine Blade and Gas Turbine Utilizing the Same  
An Ni base alloy uses GTD-111 as a base to improve high-temperature strength while maintaining the weldability and corrosion resistance and a gas turbine blade utilizes the Ni base alloy. The Ni...
US20140328694 Protective Finish for Wing Tip Devices  
The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying...