Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 1 - 50 out of 20,648

Document Document Title
WO/2017/031163A1
A coated substrate is provided that includes an environmental barrier coating on (e.g., directly on) a surface of a substrate (e.g., a ceramic matrix composite). The environmental barrier coating can include a barrier layer having a refr...  
WO/2017/028912A1
According to the invention, the use of a polymer coating (25) in the carrying flank region (24) minimizes damages. Moreover, a long-term separating effect between the components, e.g. rotor blade and rotor disk, is ensured. According to ...  
WO/2017/029008A1
The invention relates to steam turbine and to a method for operating said steam turbine. The steam turbine comprises a high-pressure part (1) and a separate, double-flow medium-pressure part (11), cooling steam from the high-pressure par...  
WO/2017/026908A1
A deswirler (1) for a cooling system and a cooling system of a turbomachine are presented. The deswirler (1) includes a hub, a disk extending annularly around the hub, and a plurality of deswirler blades. The disk includes a hub region s...  
WO/2017/025995A1
A turbine blade (120), a plurality of which are arranged in a row in an annular flow path in an axial-flow turbine, is provided with: a dorsal surface (106) which curves in a convex shape; a ventral surface (107) on the opposite side to ...  
WO/2017/025451A1
The invention relates to a CMC component, in particular a turbine component (I), in particular a guide vane or rotor blade (L), which comprises a succession of laminate-type layers (S), the layers consisting of different ceramic fiber-co...  
WO/2017/026904A1
A diffuser for a turbine engine includes a first wall that extends circumferentially about a centerline axis of the turbine engine. The diffuser also includes a second wall that extends circumferentially about the centerline axis. At lea...  
WO/2017/026875A1
The present invention relates to a gas turbine blade, which can: improve cooling efficiency by sufficiently cooling a blade part even when a large amount of cooling air flows therein, according to the formation, at the front end of a fil...  
WO/2017/025684A1
The invention relates to the field of turbomachine rotor blades and notably to a turbomachine rotor blade comprising a blade root and a blade tip which are separated by a blade height (h), and at least one intermediate portion (112a), ha...  
WO/2017/025682A1
The invention relates to a blade comprising a blade body (9) made of a fibre reinforced polymer matrix composite material and a leading-edge shield (10) made of a material having better resistance to point impacts than the composite mate...  
WO/2017/023258A1
A rotor blade (16) for a turbine of a gas turbine that includes an airfoil (25). The airfoil may have a leading edge, a trailing edge, an outboard tip, and an inboard end where the airfoil attaches to a root configured to couple the turb...  
WO/2017/021074A1
The invention relates to a method for driving out a blade (2), the blade root (3) of which is held in an elongated receiving groove (4) of a wheel disc (5) arranged on a stacked rotor. The method has the following steps: a) providing a d...  
WO/2017/020178A1
A rotor blade for a turbine (12) of a gas turbine (10) includes an airfoil (25). The airfoil (25) may have a leading edge (28), a trailing edge (29), an outboard (31), and an inboard end that attaches to a root (21) configured to couple ...  
WO/2017/021532A1
In a method for repairing a workpiece damaged in the form of a notch, the size of the notch is increased, and the notch is filled in a welding process. The device for carrying out said method comprises a scanning device for determining t...  
WO/2017/018981A1
A turbine blade (10) includes a generally elongated airfoil (32) extending span-wise along a radial direction, and a circumferentially extending shroud (70) coupled to a radially outer tip (24) of the airfoil (32). The shroud (70) includ...  
WO/2017/017475A1
The present invention relates to a water turbine arrangement (10) for extracting energy from a flow of water. The water turbine arrangement (10) comprises a turbine (22) and at least one blade (18) mounted for rotation and mechanically c...  
WO/2017/017392A1
The proposed invention is an air-flow straightening assembly for a turbine engine comprising: - a cylindrical platform (15) centred on an axis (X-X), - at least one straightener blade (20) extending from the platform, - a structural arm ...  
WO/2017/016879A1
Sintered product having a chemical analysis such that, in percentages by mass based on the oxides, - ZrO2 partially stabilised with CeO2 and Y2O3: remainder up to 100%, - AI2O3: > 10% and < 19% - of an additive selected from CaO, the oxi...  
WO/2017/013053A1
An unshrouded turbomachine impeller (1) is disclosed. The impeller comprises a hub (3) and a plurality of sequentially arranged blades (5). Each blade extends from a blade root (5R) at the hub (3) to a blade tip (5T) and is comprised of ...  
WO/2017/013360A1
The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two...  
WO/2017/014993A1
Double blade airfoils and related systems are disclosed. The double blade design may efficiently use a minimal amount of material yet achieve exceptional aerodynamic efficiencies well above the previously understood theoretical maximum. ...  
WO/2017/012761A1
A compressor includes impellers each having its chord angle less than its stall angle. The impellers can be used in a contra-rotating impeller arrangement without static diffusers. The contra-rotating impeller arrangement provides for mu...  
WO/2017/013354A1
The invention relates to distributor blading (10) having a blade (12), including a pressure-side wall (16) and a suction-side wall (14), and an insert (20) placed in the blade (12) and including: a closed wall (22) having an outer skin (...  
WO2017010627A1
The present invention relates to a gas turbine that includes a cooling system provided with a cool-air supply path detouring to an outer casing and, more specifically, to a gas turbine that includes a cooling system and a cooling method ...  
WO2017009051A1
The invention relates to a blade (11) for a turbo engine, for example a gas turbine or an aero turbine. This blade has an internal space (29) through which cooling gas can be transported via channels (25) to the surface (23) of the blade...  
WO/2017/005592A1
The invention relates to a rotor blade arrangement (1) for a turbomachine having a blade carrier (9), on whose outer circumferential surface (3) there is formed a circumferential T-shaped slot (4), having a blade ring (5) which comprises...  
WO/2017/005460A1
Disclosed is a coating system for a substrate, said system comprising a first, second and third layer. In said system, the first layer is designed as an adhesion promoter layer, the second layer is a ductile metal layer with a columnar s...  
WO/2017/005484A1
The invention relates to a cast turbine blade (10) having a platform (16) and a hollow blade airfoil (18) arranged thereon, wherein the blade airfoil (18) has a pressure-side blade wall (34) and a suction-side blade wall (32) that extend...  
WO/2017/007485A1
An airfoil (12) for a turbine engine with a trailing edge cooling feature (40) includes a plurality of profiled partition walls (44A-E) connecting the pressure side (24) and the suction side (26) of an outer wall (18) of the airfoil (12)...  
WO/2017/007580A1
Airfoil outer wall thickness of a gas turbine engine blade is increased in the zone that is proximate the trailing edge and blade hub by forty to sixty percent (40- 60%) greater than comparable greatest wall thickness anywhere else along...  
WO/2017/006054A1
The invention relates to a rotary assembly of an aeronautical turbomachine comprising: a fan (2) disc (22) having at least one tooth (25) and at least one platform (30) mounted on the tooth (25) of the fan disc. The tooth of the fan disc...  
WO/2017/006033A1
The invention relates to a method for altering the law of twist of the aerodynamic surface of a gas turbine engine fan blade, in which method there is established, for a portion of the aerodynamic surface of the fan blade, an alteration ...  
WO/2017/005781A1
A method of manufacturing a vane (61), the vane (61) comprising a root part (62), an aerofoil (74) and a cooling channel (63) extending through at least the root part (62), the cooling channel (63) is defined by a wall (76) and comprises...  
WO/2017/006927A1
Provided is a high-strength, heat-resistant, Ni-base alloy member comprising Co: 5 to 12%, Cr: 5 to 12%, Mo: 0.5 to 3.0%, W: 3.0 to 6.0%, Al: 5.5 to 7.2%, Ti: 1.0 to 3.0%, Ta: 1.5 to 6.0%, Re: 0 to 2.0%, and C: 0.01 to 0.20%. The balance...  
WO/2017/001822A1
A turbomachinery rotor blade is provided having an aerofoil body, and a hole penetrating the aerofoil body from a suction surface to a pressure surface thereof. The hole is suitable to receive a lacing wire. The blade further has a protr...  
WO/2017/001139A1
The invention relates to an arrangement (1) for a turbine comprising a metallic support structure having at least one radial support strut (3, 4, 5) and a multiplicity of plate-shaped, fiber-reinforced ceramic segments (6) which are arra...  
WO/2017/003416A1
A turbine component (10) including a shrouded airfoil (32) with a flow conditioner (70, 70a, 70b) configured to direct leakage flow and coolant to be aligned with main hot gas flow is provided. The flow conditioner (70, 70a, 70b) is posi...  
WO/2017/003455A1
A turbine stator vane (10) having a cooling circuit (62) formed within the vane (10) including a plurality of channels, at least a first pass channel (12), a second pass channel (14), and a final pass channel (16) and an inter-stage purg...  
WO/2017/001801A1
The invention relates to a turbine engine blade (12) comprising a hollow body defining a cavity, and also comprising a downstream trailing edge (16). The blade (12) further comprises at least one hole (18) which communicates with the cav...  
WO/2017/003457A1
A turbine blade (10) and method of cooling. The turbine blade (10) having multiple aft flowing cooling circuits formed within the blade (10) including at least a leading edge circuit (12) and a trailing edge circuit (14). Each cooling ci...  
WO/2017/001751A1
The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall gro...  
WO/2017/001752A9
The invention relates to a moulding unit (210) for producing a turbomachine blade blank. The moulding unit (210) has an upstream portion (270) and a downstream portion (280). According to the invention, the moulding unit (210) comprises ...  
WO/2017/001752A1
The invention relates to a moulding unit (210) for producing a turbomachine blade blank. The moulding unit (210) has an upstream portion (270) and a downstream portion (280). According to the invention, the moulding unit (210) comprises ...  
WO/2016/208211A1
The vibration reduction damper (13) according to the present disclosure is disposed in the interior of a center vent tube (12) having vent holes (12a) which penetrate in the radial direction, and is provided with a sliding part (13a) tha...  
WO/2016/210189A1
A frame which includes adjacent, spaced-apart segments that define adjacent, spaced-apart, and parallel closed-loop tracks supporting two or more articulated foils between the adjacent frame segments. Opposite distal ends of the foils co...  
WO/2016/206944A1
The present invention relates to a turbine assembly (10) comprising at least one basically hollow aerofoil (12) with at least one trailing edge (14) comprising at least two wall segments (16, 18) that each comprises an inner surface (20,...  
WO/2016/206702A1
Coating system (1) for coating a surface (3) of a substrate (5), the coating system (1) comprising; a coating (7), and an adhesive layer (9), that is disposed between the substrate (5) and the coating (7), wherein the adhesive layer (9) ...  
WO/2016/209576A1
A method of welding with low shrinkage stress, including forming an excavation (42, 70) in a surface (24, 76) of a substrate (24, 76) with a shallow geometry (D, W, A) limited to surfaces oriented within 45 degrees of the surface. Molten...  
WO/2016/202495A1
A dense vertical cracked microstructure in a ceramic layer system made of an underline partially stabilized zirconia layer and an above laying fully stabilized zirconia layer show good erosion resistance and long life time.  
WO/2016/198210A1
The invention relates to a method for producing a turbine blade (1) with a blade root portion (2), a blade aerofoil portion (3), adjoining the blade root portion (2), and a blade tip portion (4), adjoining the blade aerofoil portion (3),...  

Matches 1 - 50 out of 20,648