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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.
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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...
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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...
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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...
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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,...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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 ...
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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 (...
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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...
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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...
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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 ...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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WO/2016/142241A2 |
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...
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WO/2016/142982A1 |
An axial-flow turbine (10) according to an embodiment is provided with: a plurality of heat shield plates (21) that surrounds a turbine rotor (12) via cooling spaces (S1, S2); and a leg part (40) that supports the heat shield plates (21)...
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