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Matches 1 - 50 out of 20,706

Document Document Title
WO/2017/045823A1
The invention is related to a turbomachine component (1), particularly a gas turbine combustor component or burner component, comprising a body (2) with a first (20), a second (21) and a third section (22), the first, second and third se...  
WO/2017/048903A1
A wind turbine condition monitoring system includes a light source configured to produce an emitted light beam and a plurality of optical sensors configured to be positioned on a wind turbine to receive the emitted light beam from the li...  
WO/2017/045809A1
The invention relates to a gas turbine guide vane segment (1) and the corresponding method of manufacturing. The gas turbine guide vane segment (1) comprises a first guide vane part (2) comprising an aerofoil (21) and a first platform se...  
WO/2017/046942A1
[Problem] To provide a thermal barrier coating which can be used on a member in a system used under high-temperature, high-pressure conditions, such as a supercritical CO2 turbine, and is made of a highly durable ceramic. [Solution] A th...  
WO/2017/048683A1
A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane...  
WO/2017/047502A1
A rotor blade (50) includes a blade path (71) that extends in the blade height direction (Dwh), a platform path (81) formed in a platform (60), and a linking path (75) that connects from the outer surface (93) of an axial mounting sectio...  
WO/2017/046851A1
Provided is a turbine rotor blade manufacturing method wherein a turbine rotor blade is manufactured using a Ni-based alloy for forging, which has excellent workability and high design flexibility for a cooling structure. This turbine ro...  
WO/2017/046534A1
The invention relates to a nozzle sector (22) for a turbine engine. The nozzle sector comprises a radially outer platform (24), a radially inner platform (26), a first end blade (81), a second end blade (84) and at least one first centra...  
WO/2017/045738A1
The invention relates to a turbine wheel (10) for a turbine of an exhaust gas turbocharger, comprising at least one turbine blade (14) against which exhaust gas can flow; the maximum ratio of the wheel outlet diameter (A) of the turbine ...  
WO/2017/041182A1
A shear flow turbomachinery device includes a housing having housing walls defining a cavity, a shaft extending into the cavity though a shaft opening in the housing wall at an end of the cavity, a rotor coupled to the shaft within the c...  
WO/2017/041969A1
Arrangement (66, 112) for a gas turbine (10), comprising: a rotor disk portion (68) comprising an engaging section (70); a blade unit portion (72) comprising an engaging section (74), wherein the respective engaging sections (70, 74) are...  
WO/2017/042497A1
The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a ho...  
WO/2017/039568A1
An air cooled turbine airfoil and method of cooling includes an outer wall (18) including pressure side wall and a suction side wall extend between a leading edge (12) and a trailing edge (14). A multiple pass serpentine flow cooling cir...  
WO/2017/039569A1
A turbine airfoil (10) includes an impingement structure (26A, 26B) comprising a hollow elongated main body (28) positioned in an interior portion (11) of an airfoil body (12). The main body (28) extends lengthwise along a radial directi...  
WO/2017/039607A1
The turbine component includes an endwall (46, 50) and an elongated airfoil (32) extending radially from the endwall (46, 50), the airfoil (32) having a leading edge (54), a trailing edge (56), and an intermediate portion (58) between th...  
WO/2017/039572A1
A turbine airfoil (10) includes a flow displacement element (26A-B, 26A'-B') positioned in an interior portion (11) of an airfoil body (12) between a pair of adjacent partition walls (24) and comprising a radially extending elongated mai...  
WO/2017/039566A1
An interlocking modular airfoil for a turbine. The airfoil includes at least one support column extending from a lower plate and at least one first filament having at least one first side aperture that receives the support column in a fi...  
WO/2017/039571A1
A turbine airfoil (10) includes a flow displacement element (26) occupying a space between a pair of adjacent partition walls (24) in an interior portion (11) of a generally hollow airfoil body (12). The flow displacement element (26) in...  
WO/2017/037804A1
This method for producing a turbine rotor (30) comprises: a shaping step (ST1) in which a base rotor material (30A) having a maximum outer diameter of at most 1000 mm is shaped from a low-alloy steel containing, in weight%, 0.20-0.35% of...  
WO/2017/036797A1
The invention relates to a turbine blade (10) comprising a platform edge surface (17) including an ultrasonic wave scattering feature (20) comprising surface irregularities adapted to alter a reflection path of an ultrasonic pulse wave.  
WO/2017/036625A1
Functional component of an engine or working machine, in particular a blade for a gas turbine, wherein the functional component in the engine or working machine can be installed such that, when in a defined installation position, it come...  
WO/2017/040111A1
A novel dual layer mask formulation is provided. In particular, the mask has a unique composition that protects the integrity of an underlying chromide coating, prevents chromium depletion from the chromide coating and prevents a subsequ...  
WO/2017/037399A1
The invention relates to a part (1) or an assembly of parts of a splitter stage of a turbofan, comprising a plurality of obstacles (4, 5, 6a, 6b) including at least one a blade (4) and at least one arm (5, 6a, 6b), and a platform (2) fro...  
WO/2017/037676A1
This disclosure describes a removable flow control device (102) which may be used in a rotating flow supply system in a gas turbine to optimize coolant flow by improving flow dynamics, reducing leakage of coolant, and reducing pressure l...  
WO/2017/033920A1
This turbine rotor blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a front edge-side cooling passage (64), a rear edge-side cooling passage (67), and an intermediate co...  
WO/2017/033726A1
A blade main body (51) of this gas turbine is provided with: a first cooling passage part (58); a second cooling passage part (59); a column part (60); and a plurality of protrusions. The first cooling passage part (58) is provided at th...  
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 ...  

Matches 1 - 50 out of 20,706