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Patent Searching and Data


Matches 951 - 1,000 out of 23,147

Document Document Title
WO/2016/195657A1
A locking spacer assembly in a gap between adjacent blade structures (22) in a turbine engine includes opposed side edge members(48,50), opposed end members (100,102), and a cap member (130). The side edge members include a recessed port...  
WO/2016/195689A1
An attachment system (10) for a turbine airfoil (12) including one or more roots (14) to attach the turbine airfoil (12) to a rotor is disclosed, whereby the roots (14) have teeth (20) configured with bearing surfaces positioned at diffe...  
WO/2016/142241A3
The invention relates to a turbine wheel assembly (1) for a turbine, in particular a waste heat recovery device, comprising - a turbine wheel (2), - a magnetic coupling (4) having a first and a second rotor (5, 6), which can each be rota...  
WO/2016/190822A1
The present invention relates to an airfoil-shaped medium so as to generate an aerodynamic force. The present invention more particularly relates to an airfoil of a wing, a propulsion system blade attachment or sailboat keel. For instanc...  
WO/2016/189612A1
Provided are: a niobium silicide-based composite material which achieves a good balance between toughness and mechanical characteristics in an ultra-high temperature range (at 1,200°C or higher) at high levels; a high-temperature compon...  
WO/2016/188524A1
The invention relates to a rotor (1) for an exhaust gas turbocharger (2), having a turbine impeller (5), a radial sealing section (6) which adjoins the turbine impeller (5) on the compressor side and is fixed in rotation with the turbine...  
WO/2016/188697A1
Disclosed is a rotor blade (1) for a gas turbine (100), said rotor blade comprising an aerofoil (2) having a pressure side (10) and an intake side (12) which transition into a platform (14) to which an attachment region (16) is connected...  
WO/2016/188855A2
A silicide-based composite material is disclosed, comprising a silicide of Mo, B, W, Nb, Ta, Ti, Cr, Co, Y, or a combination thereof, Si3N4, and at least an oxide, as well as and a process for producing the same.  
WO/2016/184549A1
The invention relates to a radial compressor (10), in particular for an exhaust gas turbocharger of an internal combustion engine, comprising at least one housing part (12) by means of which a receiving chamber (14) for a compressor whee...  
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) et™ 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...  

Matches 951 - 1,000 out of 23,147