| Patents for F01D 5 - Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members (32,915) |
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| 12/29/2005 | US20050286998 Chevron film cooled wall |
| 12/29/2005 | US20050286997 Airfoil insert with castellated end |
| 12/29/2005 | US20050284127 Detonation engine and flying object provided therewith |
| 12/29/2005 | DE102005026525A1 Verfahren und Vorrichtung zur Kühlung von Gasturbinenlaufschaufeln Method and apparatus for cooling gas turbine blades |
| 12/29/2005 | DE102005026318A1 Verfahren und Vorrichtung zur Herstellung von Gasturbinentriebwerken Method and apparatus for the production of gas turbine engines |
| 12/29/2005 | DE102004029830A1 Turbinenrad in einer Abgasturbine eines Abgasturboladers Turbine wheel in an exhaust gas turbine of an exhaust turbocharger |
| 12/29/2005 | CA2510670A1 Venting tube for low-pressure shaft of a turbine engine |
| 12/28/2005 | EP1609951A1 Integral shroud segment for rotor blade |
| 12/28/2005 | EP1609950A2 Airfoil insert with castellated end |
| 12/28/2005 | EP1609949A1 Film cooled wall with chevron-shaped cooling holes |
| 12/28/2005 | EP1609948A2 Integrally bladed rotor airfoil fabrication and repair techniques |
| 12/28/2005 | EP1608483A1 Method and device for restoring and producing geometrically complex components |
| 12/28/2005 | CN2748643Y Last stage rotor blade of large-scale steam turbine |
| 12/28/2005 | CN1712673A Integral cover bucket design |
| 12/27/2005 | US6979498 aluminide diffusion coating material is selected from platinum aluminides and simple aluminides, and overlay alloy coating material is selected from MCrAlX, wherein M is iron, cobalt, nickel or alloys, X is Zr, Pt, Pd, Ta, Hf, Si, Y and Re |
| 12/27/2005 | US6979180 Hollow component with internal damping |
| 12/27/2005 | US6979178 Cylindrical blades for axial steam turbines |
| 12/27/2005 | US6979176 Cooled turbine component and cooled turbine blade |
| 12/27/2005 | US6979173 Turbine blade or vane |
| 12/22/2005 | WO2005120824A2 Durable thermal barrier coating having low thermal conductivity |
| 12/22/2005 | US20050281677 Powder/wrought alloy composite turbine disc |
| 12/22/2005 | US20050281675 Cooling system for a showerhead of a turbine blade |
| 12/22/2005 | US20050281674 Internal cooling system for a turbine blade |
| 12/22/2005 | US20050281673 Drillable super blades |
| 12/22/2005 | US20050281671 Gas turbine airfoil trailing edge corner |
| 12/22/2005 | US20050281668 Low-mid turbine temperature abradable coating |
| 12/22/2005 | US20050281667 Cooled gas turbine vane |
| 12/22/2005 | US20050281663 Double impingement vane platform cooling |
| 12/22/2005 | US20050279481 Method and device for producing precision investment-cast ne metal alloy members and ne metal alloys for carrying out said method |
| 12/22/2005 | US20050279100 High area-ratio inter-turbine duct with inlet blowing |
| 12/22/2005 | US20050278950 Process for manufacturing a reinforcing leading or trailing edge for a fan blade |
| 12/22/2005 | DE102005024475A1 Verfahren zur Beschichtung von Gasturbinentriebwerkskomponenten A process for coating of gas turbine engine components |
| 12/22/2005 | DE102004046100A1 To bond two components together, e.g. the shaft and wheel for an IC motor turbine, their contact surfaces are heated by friction for the softened shaft end to be pushed into the wheel hollow zone for a positive fit |
| 12/22/2005 | DE102004026386A1 Schaufelblatt einer Strömungsmaschine sowie Strömungsmaschine Blade of a turbomachine and turbomachine |
| 12/22/2005 | DE102004026365A1 Turbine engine e.g. aircraft engine, outer cover band compensating device, has plate-shaped section including U-shaped area, where device is made of a plastically deformed wire-shaped unit whose cross section has round form |
| 12/22/2005 | DE102004024016A1 Air suction arrangement for aircraft, has branch line to draw bleed air from high-pressure region of engine so as to drive turbine of turbo-supercharger |
| 12/21/2005 | EP1607612A1 Gas turbine engine |
| 12/21/2005 | EP1607585A1 Fatigue failure diagnostic method of turbocharger and fatigue failure diagnostic apparatus for turbocharger |
| 12/21/2005 | EP1607579A1 Locking means for gas turbine engines |
| 12/21/2005 | EP1607578A1 Cooled rotor blade |
| 12/21/2005 | EP1607577A2 Turbine engine blades with drillable film cooling holes |
| 12/21/2005 | EP1607576A2 Airfoil cooling passageway turn and manufacturing method therefore |
| 12/21/2005 | EP1607575A1 Method for cooling an airfoil wall |
| 12/21/2005 | EP1607574A1 High area-ratio inter-turbine duct with boundary layer blowing |
| 12/21/2005 | EP1607573A1 Compressor blade with reduced aerodynamic vibration induction |
| 12/21/2005 | EP1607379A1 Material for thermal barrier coating |
| 12/21/2005 | EP1607169A1 Method of repairing a turbine blade element |
| 12/21/2005 | EP1606494A1 Coolable layer system |
| 12/21/2005 | EP1309773B1 Turbine vane system |
| 12/21/2005 | CN1710255A Drillable super blades |
| 12/21/2005 | CN1232720C Abradable seal |
| 12/20/2005 | US6977233 Sintered silicon nitride |
| 12/20/2005 | US6976827 Rotor balancing device and method |
| 12/20/2005 | US6976826 Turbine blade dimple |
| 12/20/2005 | US6976824 Reducing clearance in a gas turbine |
| 12/18/2005 | CA2509863A1 Double impingement vane platform cooling |
| 12/18/2005 | CA2509744A1 High area-ratio inter-turbine duct with inlet blowing |
| 12/15/2005 | WO2005119030A1 Turbine hub cooling system for exhaust-gas turbines |
| 12/15/2005 | WO2005119028A1 Gas turbine compression system and compressor structure |
| 12/15/2005 | US20050276698 Cooling passageway turn |
| 12/15/2005 | US20050276697 Method and apparatus for cooling gas turbine rotor blades |
| 12/15/2005 | US20050276692 Lightened interblade platform for a turbojet blade support disc |
| 12/15/2005 | US20050276691 Inter-vane platform with lateral deflection for a vane support of a turbine engine |
| 12/15/2005 | US20050276687 Methods and apparatus for fabricating gas turbine engines |
| 12/15/2005 | US20050276684 Centrifugal fan with resonant silencer |
| 12/15/2005 | US20050274701 Homogeneous welding via pre-heating for high strength superalloy joining and material deposition |
| 12/15/2005 | US20050274112 Fatigue failure diagnostic method of turbocharger and fatigue failure diagnostic apparatus for turbocharger |
| 12/15/2005 | US20050274011 Fillet machining without adaptive probing and parts finished thereby |
| 12/15/2005 | US20050274010 Method of replacing damaged aerofoil |
| 12/15/2005 | US20050274009 Braze repair of shroud block seal teeth in a gas tubine engine |
| 12/15/2005 | US20050274008 Method for repairing a damaged blade of a BLISK |
| 12/15/2005 | DE102005024160A1 Innenkernprofil für ein Leitschaufelblatt einer Turbine Inner core profile for a turbine airfoil |
| 12/15/2005 | DE102004025139A1 Verfahren zur Aufbringung von Heißgas-Korrosionsschutzschichten A process for the application of hot gas corrosion protection layers |
| 12/15/2005 | DE102004025049A1 Abgasturbolader Exhaust gas turbocharger |
| 12/15/2005 | CA2509803A1 Process for reparing a blade component |
| 12/14/2005 | EP1605138A2 Cooled rotor blade with leading edge impingement cooling |
| 12/14/2005 | EP1605137A1 Cooled rotor blade |
| 12/14/2005 | EP1605136A2 Cooled rotor blade |
| 12/14/2005 | EP1605135A2 Method of making and joining an aerofoil and root |
| 12/14/2005 | EP1605134A2 Device for balancing a gas turbine rotor and gas turbine engine comprising such a device |
| 12/14/2005 | EP1605074A1 Thermal recovery treatment for a service-degraded component of a gas turbine |
| 12/14/2005 | EP1605068A2 Homogeneous welding via pre-heating for high strength superalloy joining and material deposition |
| 12/14/2005 | EP1604770A2 Method of replacing damaged aerofoil |
| 12/14/2005 | CN1708634A Self-regulating turbine |
| 12/14/2005 | CN1708633A Turbo engine |
| 12/14/2005 | CN1708598A Intermetallic material and use of said material |
| 12/14/2005 | CN1707076A Fatigue failure diagnostic method of turbocharger and fatigue failure diagnostic apparatus for turbocharger |
| 12/14/2005 | CN1707069A Method and apparatus for cooling gas turbine rotor blades |
| 12/13/2005 | US6974637 comprises aluminide bond coating; improved spallation resistance |
| 12/13/2005 | US6974636 Protective coating for turbine engine component |
| 12/13/2005 | US6974619 Hierarchical materials |
| 12/13/2005 | US6974508 Nickel base superalloy turbine disk |
| 12/13/2005 | US6974308 High effectiveness cooled turbine vane or blade |
| 12/13/2005 | US6974306 Blade inlet cooling flow deflector apparatus and method |
| 12/10/2005 | CA2509385A1 Homogeneous welding via pre-heating for high strength superalloy joining and material deposition |
| 12/08/2005 | WO2005116404A1 Vane comprising a transition zone |
| 12/08/2005 | US20050271886 Oxidation resistant superalloy and article |
| 12/08/2005 | US20050271513 Compressor blade with reduced aerodynamic blade excitation |
| 12/08/2005 | US20050271511 Device for axially retaining blades on a turbomachine rotor disk |
| 12/08/2005 | US20050271510 Fan blade and disk assembly |