Patents
Patents for F01D 5 - Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members (32,915)
12/2005
12/08/2005US20050271508 Flexible turbine blade
12/08/2005US20050271507 Turbine bucket with optimized cooling circuit
12/08/2005US20050271506 Supporting frame with locating function
12/08/2005US20050271505 Turbine engine shroud segment, hanger and assembly
12/08/2005US20050271504 Seal system
12/08/2005US20050268619 Method and apparatus for increasing the pressure of cooling fluid within a gas turbine engine
12/08/2005US20050268463 Method and apparatus for supporting turbine components for manufacture
12/08/2005US20050268461 Method and apparatus for securing turbine components for manufacture
12/08/2005DE10236273B4 Turax-Motor mit dreifachem Wirkungsprinzip Turax motor with triple action principle
12/08/2005DE10209347B4 Herstellungsverfahren für einen Turbinenradläufer Manufacturing method for a Turbinenradläufer
12/08/2005DE102004025321A1 Strömungsmaschinenschaufel Turbomachine blade
12/08/2005CA2502805A1 Turbine engine shroud segment, hanger and assembly
12/07/2005EP1602855A2 Balancing assembly for turbine rotor
12/07/2005EP1602804A2 Turbine nozzle support structure
12/07/2005EP1602802A1 Seal system
12/07/2005EP1602801A1 Rotor blade with a stick damper
12/07/2005EP1602800A1 Method for cooling an airfoil wall
12/07/2005EP1601860A1 Turbine nozzle airfoil
12/07/2005EP1601528A2 Thermal barrier coating having low thermal conductivity
12/06/2005US6971855 Blade arrangement for gas turbine engine
12/06/2005US6971852 Method of and structure for enabling cooling of the engaging firtree features of a turbine disk and associated blades
12/06/2005US6971851 Multi-metered film cooled blade tip
12/06/2005US6971850 Multiple alloy rotor and method therefor
12/06/2005CA2321330C Bowed compressor airfoil
12/06/2005CA2292384C Renewing a thermal barrier coating system
12/01/2005WO2005113941A1 Blade for turbomachinery comprising a shroud and a weight-optimised sealing strip
12/01/2005WO2005113858A1 Method for applying hot-gas anticorrosive coatings
12/01/2005WO2005113335A1 Boundary layer suction arrangement
12/01/2005WO2005113210A2 Method of producing unitary multi-element ceramic casting cores and integral core/shell system
12/01/2005WO2005112603A2 Durable thermal barrier coating having low thermal conductivity
12/01/2005US20050266266 Nickel aluminide coating with improved oxide stability
12/01/2005US20050266163 Extremely strain tolerant thermal protection coating and related method and apparatus thereof
12/01/2005US20050265851 Active elements modified chromium diffusion patch coating
12/01/2005US20050265849 Turbine blade retainer seal
12/01/2005US20050265847 Rotor assembly and annulus filler for gas turbine engine compressor
12/01/2005US20050265846 Balance assembly for rotary turbine component and method for installing and/or adjusting balance weight
12/01/2005US20050265845 Method and apparatus for balancing turbine rotors
12/01/2005US20050265844 Cooled rotor blade
12/01/2005US20050265843 Rotor blade with a stick damper
12/01/2005US20050265842 Cooled rotor blade
12/01/2005US20050265841 Cooled rotor blade
12/01/2005US20050265840 Cooled rotor blade with leading edge impingement cooling
12/01/2005US20050265839 Cooled rotor blade
12/01/2005US20050265838 Leading edge diffusion cooling of a turbine airfoil for a gas turbine engine
12/01/2005US20050265837 Vortex cooling of turbine blades
12/01/2005US20050265836 Cooled rotor blade and method for cooling a rotor blade
12/01/2005US20050265835 Gas turbine airfoil leading edge cooling
12/01/2005US20050265831 Method for coating gas turbine engine components
12/01/2005US20050265830 Turbine nozzle support structure
12/01/2005US20050265829 Internal core profile for a turbine nozzle airfoil
12/01/2005US20050265825 Spacing arrangement
12/01/2005US20050262965 Ternary carbide and nitride composites having tribological applications and methods of making same
12/01/2005DE102005021664A1 Process for modifying the surface of a ceramic core used on turbine parts comprises applying a ceramic-based material to the surface of the ceramic core using a direct scribing method according to a previously selected pattern
12/01/2005DE102004024299A1 Geschweisstes Bauteil Welded component
12/01/2005DE102004023623A1 Strömungsmaschinenschaufel Turbomachine blade
12/01/2005CA2565011A1 Boundary layer suction arrangement
12/01/2005CA2549091A1 Durable thermal barrier coating having low thermal conductivity
11/2005
11/30/2005EP1600607A2 Device to control the radial clearance of the rotor of a gas turbine
11/30/2005EP1600605A2 Cooled rotor blade
11/30/2005EP1600604A1 Cooler rotor blade and method for cooling a rotor blade
11/30/2005EP1600518A2 Nickel aluminide coating with improved oxide stability
11/30/2005EP1599657A1 Device for effecting heat transfer to rotating equipment, in particular gas turbines
11/30/2005EP1320662B1 Seal system
11/30/2005CN1702302A Internal core profile for a turbine nozzle airfoil
11/30/2005CN1701951A Bi-layer hvof coating with controlled porosity for use in thermal barrier coatings
11/29/2005US6969821 Airfoil qualification system and method
11/29/2005US6969558 Low sulfur article having a platinum-aluminide protective layer, and its preparation
11/29/2005US6969555 Aluminate coating for a silicon containing substrate
11/29/2005US6969240 Integral turbine composed of a cast single crystal blade ring diffusion bonded to a high strength disk
11/29/2005US6969239 Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine
11/29/2005US6969238 Tri-property rotor assembly of a turbine engine, and method for its preparation
11/29/2005US6969237 Turbine airfoil cooling flow particle separator
11/29/2005US6969233 Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity
11/29/2005US6969232 Flow directing device
11/29/2005US6969230 Venturi outlet turbine airfoil
11/29/2005US6968991 Diffusion bond mixture for healing single crystal alloys
11/29/2005US6968721 Method of manufacturing blade retainer and manufacturing devices therefor
11/29/2005US6968696 Part load blade tip clearance control
11/29/2005CA2123135C Aluminide - silicide coatings, coating compositions, process for coating and improved coated products
11/28/2005CA2508009A1 Method and apparatus for balancing turbine rotors
11/27/2005CA2501160A1 Rotor blade with a stick damper
11/25/2005CA2507192A1 Method for coating gas turbine engine components
11/24/2005WO2005111379A1 Blade fixing relief mismatch
11/24/2005WO2005111378A1 Fan blade curvature distribution for high core pressure ratio fan
11/24/2005WO2005111377A1 Natural frequency tuning of gas turbine engine blades
11/24/2005WO2005111376A1 Bladed disk fixing undercut
11/24/2005US20050260435 Low thermal conductivity, a high thermal coefficient of expansion and a high sintering temperature, good phase stability up to temperatures in excess of 1300 degrees, Ba(Mg1/3Ta2/3)O3
11/24/2005US20050260434 Bi-layer HVOF coating with controlled porosity for use in thermal barrier coatings
11/24/2005US20050260425 Plasma spraying a coating of magnesia-alumina- spinel containing calcium oxide, having regions of relative oxide or nitride imbalance on titanium alloy aerospace component
11/24/2005US20050260346 Method for aluminide coating a hollow article
11/24/2005US20050260078 Laminated turbomachine airfoil with jacket and method of making the airfoil
11/24/2005US20050260076 Gas turbine blade cooling circuit having a cavity with a high aspect ratio
11/24/2005US20050260069 Heat-dissipating device
11/24/2005US20050260068 Automotive compressor
11/24/2005US20050260067 Variable geometry turbine
11/24/2005US20050258577 Method of producing unitary multi-element ceramic casting cores and integral core/shell system
11/24/2005US20050257863 Cold-forming a predetermined, pretreated Ti alloy into a cold-formed shape; subjecting the cold-formed shape to a post-forming annealing cycle comprising: heating the cold-formed shape, holding, cooling the cold-formed shape to room temperature
11/24/2005US20050257522 Turbocharger
11/24/2005DE102005020470A1 Cooling insert and nozzle assembly for use by gas turbine, has cooling insert having flexible edge portion which is inserted between adjacent ribs of nozzle
11/24/2005DE102005019652A1 Turbulator auf der Unterseite einer Turbinenschaufelspitzenumleitbiegung und zugehöriges Verfahren Turbulator on the underside of a Turbinenschaufelspitzenumleitbiegung and associated method