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WO/2016/076834A1 |
The present disclosure provides a turbine blade (12) comprising a leading edge cooling circuit (30), a trailing edge cooling circuit (34), a mid-section cooling circuit (32) comprising a first channel (32a), an intermediate channel (32b)...
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WO/2016/076003A1 |
Provided are a cooling structure for a turbine, and a gas turbine, which are configured so as to reduce power required for cooling cooling-air and so as to increase a turbine output. A cooling structure for a turbine is configured such t...
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WO/2016/075423A1 |
The manufacture method comprises steps of producing a preform by selective melting, the preform comprising an assembly surface to be brazed to the part to be repaired and containing a brazing material, and then joining the preform to the...
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WO/2016/075984A1 |
A jet engine (1) is provided with: a hollow shaft (10); a center vent tube (12) inserted through the shaft (10); an annular support section (130) protruding from the inner wall surface (10a1) of the shaft (10); and an annular spacer ring...
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WO/2016/076704A1 |
The invention relates toa method for inspecting and/or repairing surface damage of a component in a device via an access opening, using fluorescent penetrant inspection (FPI), with a borescope inspection kit comprising flexible conduits,...
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WO/2016/076305A1 |
A heat shielding coating (11) comprises a bond coat layer (12) as a metal bonding layer layered on a base material (10), and a top coat layer (13) including a zirconia-based ceramic layered on the bond coat layer (12), the porosity of th...
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WO/2016/071620A1 |
The invention relates to a turbine blade (1) of a turbine engine including an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14), and a squealer tip (2) at the top thereof, wherein said squealer tip (2) i...
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WO/2016/071883A1 |
A turbine blade is provided with at least one cooling channel (20) and a plurality of cooling holes (21); each cooling hole (21) being provided with an outlet section (26) having an elongated shape along a principal axis (E); the height ...
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WO/2016/071348A1 |
The invention relates to a compressor (1) for compressing supply air for a power generating machine, comprising an electric drive (4) and a compressor wheel (5) rotatably connected to said electric drive (4) via a shaft (6), the compress...
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WO/2016/071881A1 |
According to a process for manufacturing a piece having a relatively big size, in particular a blade for a turbine engine, at least two sectors (2) are manufactured separately from each another, so that each of them comprises: a portion ...
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WO/2016/071094A1 |
A higher service life even in the presence of CMAS impurities is ensured by using a fully stabilized zirconium oxide layer and thus a higher yttrium content and the segmentation.
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WO/2016/072734A1 |
An impulse turbine system of an independent type wing is disclosed. The impulse turbine system according to an embodiment of the present invention is characterized by an inlet through which a working fluid flows, and in that working flui...
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WO/2016/072998A1 |
A compressor includes a purge flow extraction path extending radially and configured to direct an airflow radially inwardly. Also included is a center bore at least partially defined by a rotor structure extending axially and fluidly cou...
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WO/2016/072473A1 |
One steam turbine rotor blade for forming a rotor blade row in a steam turbine is equipped with a rotor blade main body having: a blade part; a blade root part provided at one end of the blade part; a first connecting part provided at th...
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WO/2016/068859A1 |
An airfoil attachment system (10) for a modular turbine vane (12) of a gas turbine engine (14) including an outer attachment system (10) with forward and aft radially extending axial hooks (20, 22) configured to be coupled directly to a ...
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WO/2016/066932A1 |
The invention relates to a rotor vane for a turbine engine, comprising a body (170) locally defining a blade provided at the radially outer end with a root (33), characterised in that the rotor vane also comprises at least one sealing el...
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WO/2016/066954A1 |
Fibrous preform for a turbomachine blade and monobloc blade that can be formed from such a preform, bladed disk and turbomachine comprising such a blade; the fibrous preform, obtained by three-dimensional weaving, comprising a first long...
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WO/2016/066414A1 |
After remelting in a suitable mold for reducing grain boundaries, an oxidation-resistant material is epitaxially grown so that the oxidation resistance of a repaired material or also of a new part is improved.
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WO/2016/066511A1 |
The invention relates to a turbine rotor blade (10) for a thermal continuous flow machine, wherein a transition region (16), as well as an aerodynamically shaped turbine blade connected to same, follows a blade foot (14) for securing the...
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WO/2016/069599A1 |
An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels ...
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WO/2016/068860A1 |
An airfoil (10) includes at least one cooling passage (20) for delivering cooling fluid (CF) from a chamber (15) defined within the airfoil (10) to an outer surface (16) of the airfoil (10). The cooling passage(s) (20) includes an entran...
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WO/2016/068862A1 |
A gas turbine exhaust section having a pair of concentrically spaced rings including an outer ring (48) and an inner ring (46), and a plurality of strut structures (64) extending radially between the rings (46, 48), interconnecting and s...
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WO/2016/066412A1 |
The invention relates to a wheel disk assembly (1), comprising a wheel disk (2), a plurality of blade devices (3), which are fastened along an outer circumference of the wheel disk (2), a plurality of sealing plates (4), which are accomm...
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WO/2016/066394A1 |
The invention relates to a wheel disc arrangement (1; 16) having a wheel disc (2; 17), having multiple vane devices which are fastened along an outer circumference of the wheel disc (2; 17), having at least one sealing plate (3; 18) whic...
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WO/2016/068856A1 |
An airfoil (10) in a gas turbine engine includes a substrate (12) having an inner surface (14), an opposed outer surface (16), and pluralities of radially outer cooling passages (20), radially inner cooling passages (22), and mid-span co...
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WO/2016/064463A1 |
A method of forming a component for a gas turbine engine, including: casting a component around a ceramic core, wherein the ceramic core forms a pilot channel (40) in the component, the pilot channel oriented from a base (176) to a tip (...
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WO/2016/062952A1 |
The invention relates to an assembly of two parts (2, 4), one of the parts (4) being made of a composite material having a fibrous reinforcement obtained from a fibrous preform created by means of three-dimensional weaving and densified ...
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WO/2016/063604A1 |
This axial flow turbine is provided with: a rotor having a plurality of rotor blades on an outer periphery thereof; and a stationary member provided on the outer periphery side of the rotor and having an annular wall face facing the tip ...
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WO/2016/062531A1 |
The invention relates to a stator (1) for a turbomachine (10), in particular a compressor (10), and to a turbomachine (10) comprising an entry stator (1) of this type. The stator (1) has at least one blade (4) comprising a vane (3) aroun...
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WO/2016/060686A1 |
A spindle bolt structure (60) including a spindle bolt (42a) having a shaft portion (68) extending through turbine disks(30a, 30b, 30c, 30d) of a gas turbine engine (10). The spindle bolt (42a) extends through the bolt hole (58) in a sea...
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WO/2016/060655A1 |
A thermal boundary protection system (10) including one or more carbon nanotubes (12) for increased durability is disclosed. In at least one embodiment, the thermal boundary protection system (10) may be formed from one or more bond coat...
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WO/2016/060654A1 |
A die cast system (10) in which an external shell (12) and an internal core (14) usable to form a component (16) of a gas turbine engine are formed together is disclosed. In at least one embodiment, the external shell (12) and internal c...
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WO/2016/058855A1 |
The invention relates to a turbomachine, in particular a steam turbine (2, 12, 13), with a shield (27) and a coolant supply (36) which causes cold intermediate superheater steam to flow onto the rotor (21), wherein additionally supply ho...
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WO/2016/059338A1 |
The invention relates to a method for carrying out work on a metal turbine engine rotor, such as a drum, in order to maintain the rotor operational, consisting in: grinding an upstream and/or downstream face (343) of a circumferential gr...
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WO/2016/058900A1 |
The invention relates to a turbine blade having a shell and an inner module, wherein the inner module can be flown through by a cooling medium both in the longitudinal and radial direction, the inner module being mounted with the shell b...
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WO/2016/055606A1 |
The invention relates to a device (10) for influencing the flow in a turbomachine (1), which device comprises a housing (1a) and at least one blade ring (9), which has a plurality of blades (15) and rotates within the housing (1a). There...
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WO/2016/055355A1 |
The invention relates to a tensioning system (1) for pre-tensioning a tie rod (40) of a turbomachine (2), which has a tensioning disk (11) or a tensioning tube (12), and also a pressure plate (100) which has a first bearing surface (101)...
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WO/2016/055328A1 |
A pair of circumferentially adjacent blades (80) for a rotor assembly, each blade comprises a root portion (50), an aerofoil (54) and a shroud (56). Each shroud (56) defines at least one boss (84, 90) having an interlock surface (86, 94)...
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WO/2016/055324A1 |
By the use of highly pure zirconium oxide material for the outermost thermal barrier coating of a two-layer thermal barrier coating system, improved and durable layer systems for high-temperature use are achieved.
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WO/2016/056654A1 |
A method for manufacturing a shaft body by welding multiple shaft members together, said method comprising: a primary tempering step, carried out before the shaft members are welded together, for subjecting at least one of the shaft memb...
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WO/2016/055354A1 |
The invention relates to a gas turbine (1) comprising at least one rotor (2) and an inner housing part (3) in order to form an annular chamber (4) between the rotor (2) and the inner housing part (3). The annular chamber (4) is fluidical...
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WO/2016/057107A1 |
A forward running wind turbine includes a rotor having a hub and at least one blade adapted for attachment to said hub by means of a spacer, said spacer being adapted so as to provide a forward axial orientation of the spacer relative to...
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WO/2016/055350A1 |
By applying material along parallel welding lines per welding layer and by changing the direction of extension of the welding tracks by 90° for the next welding layer, good results are achieved.
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WO/2016/057110A1 |
A wind turbine includes a rotor having a hub and at least one blade adapted for attachment to said hub by means of a root so as to provide a forward axial orientation of the root relative to a plane that is normal to the axis of rotation...
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WO/2016/052114A1 |
A steam corrosion-resistant multilayered film formed on a base material containing a silicon carbide composite material, said steam corrosion-resistant multilayered film being characterized by comprising: an eutectic structure layer cont...
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WO/2016/051054A1 |
The invention relates to a mobile vane (34) for a turbine engine, comprising a root (41) designed to be inserted into a receiving element (62) of a rotor disk (38) for a turbine engine, a platform (48) carried by the root (41), and a bla...
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WO/2016/051531A1 |
This turbine is provided with: a housing which includes a shroud section having an inlet (61), an outlet (62), and a shroud surface (6) extending between the inlet and the outlet; and a turbine rotor section which is housed inside the ho...
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WO/2016/050669A1 |
The invention relates to a return stage (RS) of a radial turbo fluid energy machine, in particular of a radial turbo compressor (TCO), having an axis of rotation (X), the return stage (RS) comprising an annular flow channel (CH) for feed...
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WO/2016/043743A1 |
A nano-yarn composite material (10) formed from a base material (12) and at least one nano-yarn (14) positioned within the base material (12) for strengthening the base material (12) is disclosed. In at least one embodiment, the base mat...
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WO/2016/043742A1 |
A core structure (10) includes a first core element (16) including a leading edge section (30), a tip section (32), and a turn section (34) joining the leading edge and tip sections (30, 32). The first core element (16) is adapted to be ...
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