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Patent Searching and Data


Matches 1 - 50 out of 20,551

Document Document Title
WO/2017/005592A1
The invention relates to a rotor blade arrangement (1) for a turbomachine having a blade carrier (9), on whose outer circumferential surface (3) there is formed a circumferential T-shaped slot (4), having a blade ring (5) which comprises...  
WO/2017/005460A1
Disclosed is a coating system for a substrate, said system comprising a first, second and third layer. In said system, the first layer is designed as an adhesion promoter layer, the second layer is a ductile metal layer with a columnar s...  
WO/2017/005484A1
The invention relates to a cast turbine blade (10) having a platform (16) and a hollow blade airfoil (18) arranged thereon, wherein the blade airfoil (18) has a pressure-side blade wall (34) and a suction-side blade wall (32) that extend...  
WO/2017/007485A1
An airfoil (12) for a turbine engine with a trailing edge cooling feature (40) includes a plurality of profiled partition walls (44A-E) connecting the pressure side (24) and the suction side (26) of an outer wall (18) of the airfoil (12)...  
WO/2017/007580A1
Airfoil outer wall thickness of a gas turbine engine blade is increased in the zone that is proximate the trailing edge and blade hub by forty to sixty percent (40- 60%) greater than comparable greatest wall thickness anywhere else along...  
WO/2017/006054A1
The invention relates to a rotary assembly of an aeronautical turbomachine comprising: a fan (2) disc (22) having at least one tooth (25) and at least one platform (30) mounted on the tooth (25) of the fan disc. The tooth of the fan disc...  
WO/2017/006033A1
The invention relates to a method for altering the law of twist of the aerodynamic surface of a gas turbine engine fan blade, in which method there is established, for a portion of the aerodynamic surface of the fan blade, an alteration ...  
WO/2017/005781A1
A method of manufacturing a vane (61), the vane (61) comprising a root part (62), an aerofoil (74) and a cooling channel (63) extending through at least the root part (62), the cooling channel (63) is defined by a wall (76) and comprises...  
WO/2017/006927A1
Provided is a high-strength, heat-resistant, Ni-base alloy member comprising Co: 5 to 12%, Cr: 5 to 12%, Mo: 0.5 to 3.0%, W: 3.0 to 6.0%, Al: 5.5 to 7.2%, Ti: 1.0 to 3.0%, Ta: 1.5 to 6.0%, Re: 0 to 2.0%, and C: 0.01 to 0.20%. The balance...  
WO/2017/001822A1
A turbomachinery rotor blade is provided having an aerofoil body, and a hole penetrating the aerofoil body from a suction surface to a pressure surface thereof. The hole is suitable to receive a lacing wire. The blade further has a protr...  
WO/2017/001139A1
The invention relates to an arrangement (1) for a turbine comprising a metallic support structure having at least one radial support strut (3, 4, 5) and a multiplicity of plate-shaped, fiber-reinforced ceramic segments (6) which are arra...  
WO/2017/003416A1
A turbine component (10) including a shrouded airfoil (32) with a flow conditioner (70, 70a, 70b) configured to direct leakage flow and coolant to be aligned with main hot gas flow is provided. The flow conditioner (70, 70a, 70b) is posi...  
WO/2017/003455A1
A turbine stator vane (10) having a cooling circuit (62) formed within the vane (10) including a plurality of channels, at least a first pass channel (12), a second pass channel (14), and a final pass channel (16) and an inter-stage purg...  
WO/2017/001801A1
The invention relates to a turbine engine blade (12) comprising a hollow body defining a cavity, and also comprising a downstream trailing edge (16). The blade (12) further comprises at least one hole (18) which communicates with the cav...  
WO/2017/003457A1
A turbine blade (10) and method of cooling. The turbine blade (10) having multiple aft flowing cooling circuits formed within the blade (10) including at least a leading edge circuit (12) and a trailing edge circuit (14). Each cooling ci...  
WO/2017/001751A1
The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall gro...  
WO/2017/001752A1
The invention relates to a moulding unit (210) for producing a turbomachine blade blank. The moulding unit (210) has an upstream portion (270) and a downstream portion (280). According to the invention, the moulding unit (210) comprises ...  
WO/2016/208211A1
The vibration reduction damper (13) according to the present disclosure is disposed in the interior of a center vent tube (12) having vent holes (12a) which penetrate in the radial direction, and is provided with a sliding part (13a) tha...  
WO/2016/210189A1
A frame which includes adjacent, spaced-apart segments that define adjacent, spaced-apart, and parallel closed-loop tracks supporting two or more articulated foils between the adjacent frame segments. Opposite distal ends of the foils co...  
WO/2016/206944A1
The present invention relates to a turbine assembly (10) comprising at least one basically hollow aerofoil (12) with at least one trailing edge (14) comprising at least two wall segments (16, 18) that each comprises an inner surface (20,...  
WO/2016/206702A1
Coating system (1) for coating a surface (3) of a substrate (5), the coating system (1) comprising; a coating (7), and an adhesive layer (9), that is disposed between the substrate (5) and the coating (7), wherein the adhesive layer (9) ...  
WO/2016/209576A1
A method of welding with low shrinkage stress, including forming an excavation (42, 70) in a surface (24, 76) of a substrate (24, 76) with a shallow geometry (D, W, A) limited to surfaces oriented within 45 degrees of the surface. Molten...  
WO/2016/202495A1
A dense vertical cracked microstructure in a ceramic layer system made of an underline partially stabilized zirconia layer and an above laying fully stabilized zirconia layer show good erosion resistance and long life time.  
WO/2016/198210A1
The invention relates to a method for producing a turbine blade (1) with a blade root portion (2), a blade aerofoil portion (3), adjoining the blade root portion (2), and a blade tip portion (4), adjoining the blade aerofoil portion (3),...  
WO/2016/198790A1
The invention relates to a method (100) for manufacturing a turbomachine fan comprising a plurality of blades mounted on a disc extending along a longitudinal axis, said method comprising the following steps of: - measuring (102) at leas...  
WO/2016/194593A1
Provided is an air turbine drive spindle in which movement of the thrust position of a rotating shaft is sufficiently inhibited. The air turbine drive spindle is provided with: a rotating shaft (1) comprising a shaft section (1A) and a t...  
WO/2016/195656A1
An attachment system (10) for a turbine airfoil (12) including one or more roots (14) to attach the turbine airfoil (12) to a rotor, whereby the roots (14) have one or more curved teeth (18) that substantially limit, if not completely el...  
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/2016/190822A1
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/2016/184782A1
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/2016/173875A1
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...  

Matches 1 - 50 out of 20,551