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WO/2015/175051A2 |
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial ...
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WO/2015/175056A2 |
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edg...
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WO/2015/175044A2 |
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a ...
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WO/2015/175043A2 |
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defi...
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WO/2015/175214A1 |
A compressor wheel (12) adapted for use with a turbocharger that has a sleeve (18) of high-strength material, such as titanium, in a bore (14) of the compressor wheel (12) that is made of a different material, such as aluminum, than the ...
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WO/2015/173311A1 |
A method for preventing corrosion of an impeller-shaft assembly of a turbomachine comprises the steps of assembling an impeller (2) on a shaft (3) in order to define an impeller-shaft assembly (1); plating the assembly (1) by inserting s...
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WO/2015/175058A2 |
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailin...
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WO/2015/175045A2 |
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defi...
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WO/2015/175052A2 |
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangent...
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WO/2015/171145A1 |
A turbine airfoil including a central cavity defined by an outer wall including pressure and suction sides extending between and joined at leading and trailing edges, and a chordal axis extends generally centrally between the pressure an...
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WO/2015/171670A1 |
According to present embodiments or aspects thereof, a composite booster spool (31) with separable composite blades (50) is provided. The blades (50) are inserted radially from within the inner circumference of the spool (31) and extend ...
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WO/2015/170230A1 |
The present invention relates to a radial turbomachine, comprising: a fixed casing (6); at least one rotor disc (2,2') installed in the casing (6) and rotatable in the casing (6) around a respective rotation axis (X-X); a plurality of an...
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WO/2015/169555A1 |
A turbine assembly comprising a basically hollow aerofoil (14) with at least one cavity (16) spanning the aerofoil in span wise direction (18) of the aerofoil (12), an outer platform (20) and an inner platform (22), each comprising at le...
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WO/2015/170296A1 |
A method for balancing a rotor (1) of a gas turbine having a plurality of discs (2) arranged in succession along a line (A) includes the steps of: acquiring eccentricity measurements (ER1,..., ERP) of the discs (2) of the rotor (1) of a ...
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WO/2015/166831A1 |
Provided are: a heat-resistant metal member which has excellent heat resistance and durability and is capable of greatly improving high-temperature corrosion resistance of a metal base that is formed of Nb, an Nb-Hf-based alloy or an Nb-...
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WO/2015/167782A1 |
An arrangement (10) for laser deposition repair of a gas turbine engine component (20). A processing surface of the component (20) is precisely positioned relative to a laser material deposition device (12), while service induced distort...
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WO/2015/165678A2 |
The invention relates to a wheel disk assembly (1; 14; 26), comprising a wheel disk (2; 15; 27), a plurality of blade devices (3; 16; 28), which are fastened along the outer circumference of the wheel disk (2; 15; 27), and a plurality of...
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WO/2015/165662A1 |
Owing to the use of a nanostructured outer layer alone for protecting against CMAS, the useful life of ceramic heat-insulating layers which are subject to CMAS influence is considerably improved. A metal layer (7), which preferably compr...
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WO/2015/162389A1 |
The internal cooling of the moving blades of the turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-face and suction-face walls. To address this problem, ther...
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WO/2015/163786A1 |
The invention can be used for preparing blisks, primarily for rotors of gas turbine engines. A tool turret (2) of a blisk disk (4) rotation assembly is configured to be replaceable and is installed by means of a bushing in a replaceable ...
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WO/2015/163226A1 |
Provided is a turbine rotor material for geothermal power generation, said material comprising 0.20-0.30 mass% of C, 0.01-0.2 mass% of Si, 0.5-1.5 mass% of Mn, 2.0-3.5 mass% of Cr, more than 0.15 mass% and not more than 0.35 mass% of V, ...
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WO/2015/163871A1 |
A self-cooling fan in configured with a vent feature that draws air into a fan housing and over a heat sink to dissipate heat generated by the motor and/or control unit. The self-cooling fan has a conduit with an attached end opening tha...
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WO/2015/161980A1 |
The invention concerns a method for producing a component, in particular a turbine component, in which a base component is produced from a metal alloy, characterised in that a powder containing or made of a solder material is applied ove...
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WO/2015/163949A2 |
A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a...
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WO/2015/161058A1 |
A process and apparatus for solid freeform fabrication and repair of components on existing bodies (such as turbine blades), the innovative process and apparatus as well as the resultant product having the following advantages: a) Can bu...
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WO/2015/158541A1 |
The invention relates to a rotor (1), in particular gas turbine rotor, having a plurality of rotor discs (3), which each have an axial through-opening (2), which rotor discs are axially stayed by means of at least one tie rod (5), which ...
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WO/2015/158468A1 |
The present invention relates to an airfoil (100) for a gas turbine. The airfoil (100) comprises an outer shell (101) comprising an inner volume and an inner shell (110) arranged within the inner volume of the outer shell (101), wherein ...
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WO/2015/158514A1 |
The invention relates to a turbine blade (1) with a turbine blade airfoil (3) in which a cavity (5) is formed that is divided by a rib element (15), the height (25) of said rib element extending from a front wall (6) of the turbine blade...
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WO/2015/158513A1 |
The invention relates to a method for assembling and/or disassembling a rotor section of a turbomachine, in particular of the turbine-side rotor section of a gas turbine, said rotor section having a plurality of rotor discs (2, 3, 4) wit...
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WO/2015/081922A9 |
The invention relates to a method for producing a component from a titanium-aluminum base alloy. The component is intended in particular as a component for turbocharger units of internal combustion engines. The method comprises the follo...
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WO/2015/158542A1 |
The invention relates to a wheel disc (1) with at least one sealing metal sheet (2), which is fixed to the wheel disc (1) in a movable manner in the circumferential direction of the wheel disc, and with at least one securing device (6), ...
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WO/2015/160466A1 |
A method is provided for remanufacturing a machine component (118). First and second sets of holes (302, 304) are selected from holes (124) of the machine component (118) based on the holes (124) being within positional tolerances of cor...
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WO/2015/154442A1 |
A cooling device with a tiny diagonal rib/recess composite structure, comprising a substrate (10), a cooling channel (11), a plurality of diagonal ribs (12) and a plurality of recesses (13). The cooling channel (11), the plurality of dia...
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WO/2015/155446A1 |
The invention relates to a turbine engine rotor lock, especially for a turbojet fan, for holding a blade (15) axially in relation to a disk (13) of the rotor, said lock (28) comprising: a composite body (50) comprising a woven fibrous st...
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WO/2015/156182A1 |
A rotor blade having high resistance to erosion, an erosion shield forming method and a rotor blade manufacturing method are provided. This rotor blade (15) comprises: a blade main body (24) having a tip (26) which is the upstream end in...
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WO/2015/157780A1 |
An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained within an aft cooling cavity (76) to form nearwall coolin...
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WO/2015/155119A1 |
The method of protecting a component of a turbomachine from liquid droplets erosion provides covering at least one region of a component surface exposed to a flow of a fluid containing a liquid phase to be processed by the turbomachine w...
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WO/2015/156816A1 |
A turbine airfoil usable in a turbine engine and having at least one cooling system with one or more turbulators having one or more downstream anti-vortex ribs is disclosed. At least a portion of the cooling system may include one or mor...
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WO/2015/156180A1 |
A management method of a powder supply head which can stabilize the supply state of a welding metal, an erosion shield forming method and a device are provided. The method is for managing a powder supply head having a double tube which s...
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WO/2015/156181A1 |
An overlay welding device which forms an erosion shield with high erosion resistance, an erosion sheet forming method and a rotor blade manufacturing method are provided. This overlay welding device is provided with a powder supply head ...
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WO/2015/155448A1 |
The invention relates to a method for the treatment of an alloy based on titanium aluminide. The method comprises the following steps during which no hot isostatic pressing is carried out: a semi-finished product (7) produced by centrifu...
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WO/2015/150034A1 |
What is described is a soldering process for repairing a surface (10) of a turbine component (115, 117) which comprises the following steps: material is removed from a damaged region of the surface (14) of the turbine component, a prefab...
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WO/2015/153411A1 |
In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an a...
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WO/2015/150019A1 |
The invention introduces a method for generating, in layers, an application structure (420) made of high heat resistant super alloys on a substrate (415). A powdery construction material is melted by an energy beam at a working point, wh...
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WO/2015/149904A1 |
The invention relates to a turbine wheel (12) for a turbine, in particular of an exhaust gas turbocharger, comprising a main body (14), to which turbine-wheel blades (10) are connected, which each have at least one thickness and an exten...
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WO/2015/149575A1 |
Disclosed is an impeller of a compressed gas engine, which comprises impeller teeth (101) provided in an equally distributed manner along a rotating peripheral face (a1) of the impeller, the side of the impeller teeth (101) which faces t...
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WO/2015/152381A1 |
Vane arrays define a flow path (R) through which a working fluid (G) flows and are formed in an annular shape by including a plurality of vane dividers (10) in a circumferential direction, each vane divider including a vane body (11). Th...
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WO/2015/144402A1 |
The invention relates to a coating method (10) for applying a cover layer (17) to a base material (16). A solder positioned on a surface of the base material (16) is heated (13) until it is molten, for joining the solder to the base mate...
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WO/2015/147964A2 |
A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for...
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WO/2015/145016A1 |
The invention relates to a rotationally symmetrical part, such as a disk (24'), for a turbine engine rotor. Said part has a rotational axis (A) and comprises, on the periphery thereof, an annular row of teeth (22'), said teeth defining g...
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