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Patent Searching and Data


Matches 1,001 - 1,050 out of 23,247

Document Document Title
WO/2016/185732A1
A guide surface which expands to the outer peripheral side as the guide surface extends from the upstream side to the downstream side is formed on a support section. A guided surface which expands to the outer peripheral side as the guid...  
WO/2016/184685A1
The invention relates to a method for producing a rotor of a flow engine, namely an integrally bladed rotor with an integral outer shroud, comprising at least the following steps: a rotor blank comprising the integral rotor blades and th...  
WO/2016/157020A3
A turbine of an organic Ranking cycle ORC is described. The turbine comprises a shaft supported by at least two bearings and a plurality of axial stages of expansion, defined by arrays of stator blades alternated with arrays or rotor bla...  
WO/2016/184782A1
A Centrifugal compressor impeller (4) comprising a plurality of blades (6) extending from an hub (7), each blade having a first wall (6A) defining a pressure side of the blade, and a second wall (6B) defining a suction side of the blade,...  
WO/2016/182688A1
A method, apparatus, and system for correcting unbalance of a turbocharger component relative to an axis of rotation of the turbocharger component. The method includes determining one or more unbalance characteristics for the turbocharge...  
WO/2016/178689A1
A turbine airfoil (10) with an internal cooling system (12) having one or more bladders (14) forming near-wall cooling channels (16) is disclosed. The bladder (14) may be conformed to a shape of an inner surface (44) forming a cavity (18...  
WO/2016/174345A1
Disclosed are a fibrous preform for a blade of a turbomachine, a one-piece blade made from a preform of said type, a bladed wheel, and a turbomachine comprising a blade of said type; the fibrous preform is obtained by a three-dimensional...  
WO/2016/173916A1
The invention relates to a turbine blade comprising an aerofoil (1) having a pressure-side and a suction-side side wall (3, 4) which are joined to one another at a leading edge (5) and at a trailing edge (6), extend in the longitudinal d...  
WO/2016/174358A1
The invention relates to a variable pitch stator blade for a turbo machine, comprising an aerofoil, a pivot member configured to cause the blade to pivot relative to a turbo machine casing, and a plate situated between the pivot member a...  
WO/2016/174412A1
Methods and apparatus are described for improving fit checking at the bonding interface of a first component, such as a fan blade (1), and a second component, such as an edge guard (2) for the fan blade (1), to be bonded by adhesive. A b...  
WO/2016/134907A3
The invention relates to a stator or rotor blade device (1) which is cast from a metal alloy and comprises at least one blade base (3) and an airfoil (4) designed as one piece with the blade base (3), a hollow space (6) extending from th...  
WO/2016/173875A1
The invention relates to a method for profiling a turbine rotor blade (14, 15) for an axial flow machine, having the following steps: providing a geometric model of a blade profile, having a camber line (3) of a profile section of the tu...  
WO/2016/174343A1
Disclosed is a preform for a blade of a turbomachine, comprising a main fibrous preform which is obtained by a three-dimensional weaving process and which includes a first longitudinal section forming a blade root (21), a second longitud...  
WO/2016/173793A1
The invention relates to a fluid flow engine (9), in particular compressor or turbine of a gas turbine engine (10), having a stationary engine casing (38) and a rotor assembly (39) rotatable supported in the engine casing (38), the rotor...  
WO/2016/174346A1
The invention relates to a preform for a turbine engine vane, obtained by means of three-dimensional weaving, comprising: a first longitudinal segment (31) intended to form at least one portion of a vane root; a second longitudinal segme...  
WO/2016/174357A1
The invention relates to a blade made of composite material, provided with a reinforcement (17) made of a stronger material with regard to a leading edge (5) likely to be struck by solid objects, which comprises, under the aerodynamic po...  
WO/2016/170114A1
A turbomachine airfoil component (15) is disclosed, having a leading edge (15L) and a trailing edge (15T). The airfoil component comprises a hole (21) extending from an inlet (21A) positioned at the leading edge (15L) towards the interio...  
WO/2016/167214A1
Provided are: a steam turbine rotor blade that is both wear resistant and reliable; and a method for manufacturing a steam turbine rotor blade capable of obtaining such a steam turbine rotor blade. The steam turbine rotor blade according...  
WO/2016/163980A1
A turbine airfoil (10) with a cooling system (12) including a serpentine cooling channel (14) with at least one flow splitter (16) forming inner and outer cooling fluid flow paths (18, 20) in at least one turn (22) is disclosed. The inne...  
WO/2016/162249A1
A blade (51) and an assembly tool (87) for assembling a blade set to a rotor disc (35) is disclosed. The blade (51) comprises a root portion (50), an aerofoil (54) and a shroud (56), the root portion (50) has two lateral sides each defin...  
WO/2016/163975A1
An airfoil cooling system (54) for a gas turbine engine (10) is disclosed. The airfoil cooling system (54) may be formed from at least a first cooling fluid supply system (56), and a second cooling fluid supply system (58). The first coo...  
WO/2016/164649A1
A. turbine assembly system and apparatus for a Hyper) etâ„¢ and method for making same is provided. Specifically, the turbine assembly provides a power generation system for a turbine engine and includes a plurality of stages. Each stage...  
WO/2016/163977A1
An airfoil cooling system (54) for a gas turbine engine (10) is disclosed. The airfoil cooling system (54) may be formed from at least a first cooling fluid supply system (56), and a second cooling fluid supply system (58). The first coo...  
WO/2016/160029A1
The present disclosure provides a core structure comprising a trailing edge section including a plurality of rib-forming apertures (126) defined by a plurality of radially-extending channel elements (130) and axially-extending passage el...  
WO/2016/156200A1
The present invention relates to a vane device (100) for a gas turbine. The vane device (100) comprises: an inner shroud (110) and an outer shroud (120), an aerofoil (101, 115) arranged between the inner shroud (110) and the outer shroud...  
WO/2016/160030A1
A turbine airfoil (10) with an internal cooling system (12) including features, such as, but not limited to, turbulators (16), mini-grooves (18) and mini-ribs (20), taking advantage of cooling fluid flow characteristics due to rotating C...  
WO/2016/157530A1
A rotor blade (22) provided in an axial flow compressor (1) equipped with: a rotary shaft; a casing (3); a diffuser section (4) provided on the downstream side of the casing (3) and forming a diffuser flow path (DC) that communicates wit...  
WO/2016/157020A2
A turbine of an organic Ranking cycle ORC is described. The turbine comprises a shaft supported by at least two bearings and a plurality of axial stages of expansion, defined by arrays of stator blades alternated with arrays or rotor bla...  
WO/2016/157127A1
The invention refers to a sandwich arrangement comprising at least two peripheral disposed ceramic panels (101a, 101b) and a ceramic felt (110) which is inserted be- tween a first and second ceramic panel, The material of the first ceram...  
WO/2016/156203A1
A blade (51) for a rotor (35) of a gas turbine (28, 30) comprises a cast substrate (70) including: a root (55) for connecting the blade (51) to a rotor (35) of a gas turbine (28, 30), a platform (54) having a lower surface (61) from whic...  
WO/2016/159933A1
A hybrid component (45) is provided including a plurality of laminates (10) stacked on one another to define a stacked laminate structure (58). The laminates (10) include a ceramic matrix composite material (22) and at least one opening ...  
WO/2016/086914A3
The invention relates to a component of a turbo device comprising a compressor and a turbine. Said component includes a component member which is made at least in part of a titanium-aluminum alloy composed of 40 to 60 atomic percent tita...  
WO/2016/151849A1
A turbine rotor blade according to an embodiment of the present invention comprises: a hub part that is connected to one end of a rotating shaft; a plurality of main blades that are provided on a peripheral surface of the hub part so as ...  
WO/2016/153816A1
A nozzle segment (451) for a turbine nozzle (450) of a gas turbine engine (100) is disclosed. The nozzle segment (451) includes an upper endwall (453), a lower endwall (463) spaced apart from the upper endwall (453), a pressure portion (...  
WO/2016/151234A1
Ceramic core used for the production of a hollow turbine blade of a turbomachine by the lost-wax casting method and shaped to constitute the cavities of said blade in a single component, comprising, in order to jointly supply the interio...  
WO/2016/152985A1
Provided are: a Ni-based super heat-resistant alloy having excellent high-temperature strength after hot working; and a turbine disk using same. The Ni-based super heat-resistant alloy has a composition comprising, in % by mass, 0.005%-0...  
WO/2016/152573A1
A blade having a flow path forming plate (60o) that defines a portion of a combustion gas flow path. Multiple rear passages (75) opening at a rear end surface (62b) are formed in the flow path forming plate (60o). The opening density of ...  
WO/2016/150782A1
The invention relates to a shaft element (1) of a turbomachine (2), in particular of a combined steam turbine (4), comprising at least two shaft subsegments (15, 16) integrally joined to each other by means of a weld (23), wherein differ...  
WO/2016/147282A1
The present invention provides a highly-durable thermal barrier coating, which can be used on a member in a system used under high-temperature/high-pressure conditions. The thermal barrier coating comprises a ceramic layer formed on the ...  
WO/2016/148695A1
An airfoil (10) for a gas turbine engine is disclosed in which the airfoil (10) includes an internal cooling system (14) formed from one or more midchord cooling channels (16) with at least one inner wall (18) positioned within the midch...  
WO/2016/148693A1
An airfoil (10) is disclosed for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more converging-diverging exit slots (20) configured to increase the effectiveness of the cooling system...  
WO/2016/148690A1
A turbine blade including a pressure sidewall (24) and a suction sidewall (26), and at least one partition rib (34) extends between the pressure and suction sidewalls (24, 26) to define a serpentine cooling path (35) having adjacent cool...  
WO/2016/146285A1
Exhaust-gas turbocharger (1) for an internal combustion engine, having a turbine housing (2), in which a turbine wheel (3) with a shaft (4) is arranged rotatably, wherein the shaft is mounted rotatably in a bearing housing (5) by means o...  
WO/2016/147364A1
Disclosed is a strain measurement method for a high temperature component wherein a bonding layer (22) and a heat blocking layer (23) are stacked in this order on a base material (21). The method has: a step for forming a plurality of re...  
WO/2016/147461A1
The present invention generates a level difference between a metal sheath and a coating material layer formed on a blade face of a blade main body. This coating device comprises: a jig (10) that supports a guide vane (V) which has a meta...  
WO/2016/148694A1
A shrouded turbine airfoil (10) with a leakage flow conditioner (12) configured to direct leakage flow to be aligned with main hot gas flow is disclosed. The leakage flow conditioner (12) may be positioned on a radially outer surface (18...  
WO/2016/148691A1
A shrouded turbine airfoil (10) with a tapered knife edge seal (12) for weight reduction at the turbine airfoil tip (14) and for enhanced contact is disclosed. The shrouded turbine airfoil (10) may include one or more shrouds (16) attach...  
WO/2016/142962A1
The purpose of the present invention is to provide a Ni-based alloy for casting that has excellent castability and high-temperature strength characteristics, and to provide a cast component for a turbine. The Ni-based alloy for casting a...  
WO/2016/142963A1
The purpose of the present invention is to provide austenitic heat-resistant steel which has sufficiently low linear expansion coefficient, while having excellent embrittlement resistance characteristics. Austenitic heat-resistant steel ...  
WO/2015/075227A3
The invention refers to a blade assembly (100) of a power plant on the basis of a modular structure, wherein blade elements comprise at least one blade airfoil (110), at least one footboard mounting part (120,130). Blade elements have at...  

Matches 1,001 - 1,050 out of 23,247