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Patent Searching and Data


Matches 1,151 - 1,200 out of 23,244

Document Document Title
WO/2016/079743A1
A pressurized, fluid-filled channel network embedded in an elastic structure, asymmetrically to the neutral plane, is used to create a deformation field within the structure by the pressurization of the embedded fluidic network, which ca...  
WO/2016/078851A1
The invention relates to a hollow blade body for a hollow blade (1), comprising a blade wall (6) which has a pressure side (4) which has at least one first blade connection element on the inner side (9) thereof, and a suction side (5) wh...  
WO/2016/080025A1
An axial-flow-machine blade according to the present invention is provided with: a blade body (39) that extends in a radial direction; a platform (end wall)(41) that is provided at an end section (40) of the blade body (39) in the radial...  
WO/2016/076374A1
A rotor assembly for a turbine, provided with a rotor shaft and a plurality of blades, the rotor shaft having: two protruding parts; two bearing surfaces; two first opposing surfaces that constitute a portion of a wall surface of a blade...  
WO/2016/076750A1
The invention relates to the field of power plant engineering and thermal power engineering and can be used in developing steam-turbine power installations. A turbine-generator shaft train contains rotors of a multi-cylinder steam turbin...  
WO/2016/075391A1
According to the invention, a blade (12') is friction-welded to a rotor disk (10') of a turbomachine, the disk comprising a projecting block (18) having an outer surface to which the blade (12') is to be welded. To this end: a surfacing ...  
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)...  
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...  
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...  
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...  
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,...  
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...  
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...  
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 ...  
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...  
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 ...  
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.  
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...  
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...  
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...  
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 ...  
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...  
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...  
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.  
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...  
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 ...  
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...  
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...  
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...  
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...  
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...  
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 (...  
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 ...  
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 ...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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...  
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)...  
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)...  
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.  
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...  
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...  
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...  
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.  
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...  

Matches 1,151 - 1,200 out of 23,244