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Matches 1 - 50 out of 22,544

Document Document Title
WO/2019/048230A1
The invention relates to a martensitic material (MarBN) that is suitable for use in compressor applications at higher temperatures due to a special heat treatment.  
WO/2019/049703A1
This steam turbine blade is provided with a blade body (7) which has a blade surface (70) extending in a blade height direction. The blade body (7) has: a first suction port (74) which extends in the blade height direction and opens on t...  
WO/2019/048177A1
The invention relates to a control system for reducing rotor vibrations, in particular the variability thereof, in shafting, in particular turbine shafting, in which the temperature of the bearing (6) of the shaft is measured and the oil...  
WO/2019/050879A1
A system and a method for removing debris from a flow path of a cooling flow is provided. The system includes a turbine including at least one airfoil. A cooling flow is communicated to cooling holes (40) via piping (60) that includes a ...  
WO/2019/046006A1
A blade assembly for a turbine includes an airfoil (10), a root (62) and a platform (52). The platform (52) is positioned radially between the airfoil (10) and the root (62). An airfoil fillet (16) joins the airfoil (10) to an upper surf...  
WO/2019/043330A1
The invention relates to a flow-straightener vane (1) of a bypass turbomachine (100) of longitudinal axis (X), the vane (1) comprising a plurality of vane sections (2) stacked radially with respect to the axis (X) along a stacking line (...  
WO/2019/042612A1
The invetion relates to a hollow vane (100) of an output stage for a steam turbine and to a method for producing said hollow vane (100). The hollow vane (100) has an outer wall and an internal structure (110) which is arranged in an inte...  
WO/2019/045671A1
Processes and systems are described herein for forming cooling channels (314) within a ceramic matrix composite component (300). The process introducing a ceramic material (18, 32) into a solid fiber material (14, 46) to produce a cerami...  
WO/2019/042700A1
A method for additively manufacturing a tip structure (G) on a pre-existing part (H) is presented, the method comprising: - a) placing the part (H) in a build space (30) of a beam- assisted additive manufacturing setup (100) and below a ...  
WO/2019/042970A1
A wall (1) of a hot gas component (2), comprises a hot (5) and a cold- gas sided surface (3), one film cooling hole (7) extending from an inlet (8) in the cold-gas sided surface to an outlet (9) in the hot-gas sided surface and comprisin...  
WO/2019/046036A1
A method of making a turbine airfoil includes generating a mold shell and generating an airfoil core (14) that includes a core exit along an extended portion of the trailing edge (32) outside of the airfoil part geometry. Float points (1...  
WO/2019/043229A1
A method of manufacturing a component (100) for a turbo machine. The component (100) comprises a main body (104) having a fluid inlet (103) and fluid outlet (200). A cooling passage (204) extends between a fluid inlet (103) and a fluid o...  
WO/2019/046022A1
A hybrid CMC component (25) for a gas turbine engine (100) is located in the turbine section (50) of the gas turbine engine (100). The hybrid CMC component takes advantage of features found within modular structures and within integral s...  
WO/2019/040079A1
Processes and systems are described herein which 3D print a ceramic fiber composite (24, 48) in a printed pattern (308) and deposit a thermal barrier coating (318) over the printed pattern (308) to define a three-dimensional abradable su...  
WO/2019/038500A1
Method for manufacturing a blade for a turbomachine, such as an outward guiding aerofoil blade, comprising the following steps: - arranging a first, fibrous wall preform, on a first portion of a mold (20); - placing at least one core on ...  
WO/2019/040316A1
A blade (10) and vane for a turbine engine comprisingan internal cooling system including an impingement cavity (38) positioned along the leading edge (22) of the blade or vane; and a showerhead arrangement including a first row (44) of ...  
WO/2019/037931A1
The present invention concerns a turbine blade foot (1) comprising a shank portion (2) which is adapted to be connected to a turbine blade (4) and a root portion (3) which is adapted to be mounted on a rotor wheel, wherein the shank port...  
WO/2019/040291A1
A seal arrangement for a turbine stage includes a vane assembly including a radially inner vane platform (12), a radially outer vane platform (30), and an airfoil (28). The seal arrangement further includes a rim seal feature (14) includ...  
WO/2019/040272A1
A blade airfoil (10) for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits (40) with a leading edge circuit (22) and a trailing edge circuit (24). The entrance (54) of a cavity in the leading edge ...  
WO/2019/040171A1
The present invention is related to a seal plate assembly (300) for a rotor disk assembly (100) of a gas turbine engine, wherein the seal plate assembly includes a plurality of adjacent seal plate segments (320, 340). Shiplaps (322,323,3...  
WO/2019/036222A1
A turbine blade tip (30) includes a tip cap (32) disposed over a blade airfoil (10) and having a pressure side edge (44) and a suction side edge (46). A notch (50) is formed by a radially inward step adjacent to the suction side edge (46...  
WO/2019/035800A1
A blade tip (30) for a turbine blade (1) includes a tip cap (32) disposed over an airfoil outer wall (12) and at least one squealer tip wall (34, 36) extending radially outward of the tip cap (32) and extending along a chord-wise directi...  
WO/2019/035813A1
A cored filler wire (10) used in a laser metal deposition (LMD) process and method of using the same. The cored filler wire includes an outer shell (12) surrounding an inner filler material (14). The outer shell is formed from a first ma...  
WO/2019/035802A1
A turbine blade tip (30) includes a squealer tip wall (34) having a forward surface (34b) that is continuous with an outer surface (14b) of an airfoil pressure sidewall (14). A plurality of cooling channels (50) are provided spaced apart...  
WO/2019/030314A1
A component (300, 400) for use in a turbomachine is provided. The component (300, 400) comprises a platform (310, 410) having a leading end (312, 412) longitudinally spaced apart from a trailing end (312, 412), an aerofoil portion (320, ...  
WO/2019/032356A1
Systems and methods for monitoring components are provided. A component has an exterior surface. A method includes performing a first analysis of a first image of a surface feature configured on the exterior surface of the component, the...  
WO/2019/030210A1
An iron-based alloy is described. Also described is a component having a surface layer 12 of an iron-based alloy, a method of providing a surface layer of an iron-based alloy on a component, an apparatus arranged to provide a surface lay...  
WO/2019/030201A1
The invention relates to a functional structure (1) for use in an energy converter and/or a turbomachine. The structure (1) comprises a lattice comprising at least one lattice cell (2), comprising lattice nodes (3) and lattice connecting...  
WO/2019/029968A1
Method of additively manufacturing a structure on a pre- existing component out of the powder bed A method of additive manufacturing a structure (1) on a pre- existing component (2) is provided, the method comprising disposing the pre-ex...  
WO/2019/032364A1
A process includes agitating at least one core of a core alloy together with a braze binder to form at least one coated core comprising the at least one core coated with a first layer of the braze binder. The process also includes agitat...  
WO/2019/027661A1
A gas turbine (10) includes a turbine section (24), and a diffuser (30) located downstream of a row of turbine blades (26) of the turbine section (24). The diffuser (30) includes an annular duct (34) extending axially along a diffuser ax...  
WO/2019/028208A1
A turbine component (1) such as a blade or vane includes at least one platform (6) provided with a platform cooling circuit (30). The platform cooling circuit (30) includes an inlet (32) for receiving a coolant (K), and a cooling channel...  
WO/2019/025194A1
A method of manufacturing a test piece (300) for testing a rotor blade design (200) for a turbomachine, the test piece comprising: a plurality of monolithically-formed body portions. There is provided a main body portion (302) correspond...  
WO/2019/020287A1
The invention relates to a turbomachine (10), in particular for a fuel cell system (1). The turbomachine (10) comprises an impeller wheel (15) arranged on a shaft (14). The impeller wheel (15) is designed as a radial impeller, and a work...  
WO/2019/020289A1
The invention relates to a turbomachine (10), in particular for a fuel cell system (1). The turbomachine (10) comprises a shaft (14), an impeller wheel (15) and an axial bearing disk (30). The impeller wheel (15) and the axial bearing di...  
WO/2019/018220A1
Systems can be used to harness energy from winds. For example, this document describes scalable systems having multiple wing-like blades that can efficiently convert wind power into electricity and other types of energy.  
WO/2019/010964A1
Disclosed is a recess-film hole cooling structure for cooling turbine blades, the structure comprising a recess (2) provided in an inner wall of a cooling blade (1), and a film hole (3) passing through the cooling blade (1), wherein the ...  
WO/2019/013178A1
The purpose of the present invention is to reduce a loss in motion energy causing rotor blades rotate, the loss being due to interference between a leakage flow at the distal end of the rotor blade and a main flow causing the rotor blade...  
WO/2019/012102A1
Compressor blade (42) for an axial compressor (10), comprising a blade root (19) and a cantilevered airfoil (20) attached to said blade root (19), the airfoil (20, 22) comprising a suction side and a pressure side extending in a span dir...  
WO/2019/012168A1
The invention relates to a system for propelling ships by means of tubes having respective helical mechanisms inside, of different gauges, which propel the water through said tubes in a turbulance-free manner and at great speed, and char...  
WO/2019/011535A1
The invention relates to a method for machining a component (2) by removing material, in particular by removing chips, in particular within a groove (1) provided in the component, in which method: spatially resolved measurement data, whi...  
WO/2019/008724A1
[Problem] To provide a turbine wherein an anti-rotation structure is prevented from being damaged by a high-temperature operating fluid, thereby preventing deterioration in the anti-rotation function. [Solution] A turbine according to an...  
WO/2019/009331A1
This turbine blade comprises: a blade part; a cooling passage that extends along a blade height direction on the inside of the blade part; a plurality of cooling holes that are formed in a trailing edge part of the blade part so that the...  
WO/2019/008656A1
This turbine blade (34) is provided with: a plurality of cooling holes (47) formed in the turbine blade (34), each of the cooling holes (47) having an inflow opening (47a), an outflow opening, and a flow passage (47b) which is formed bet...  
WO/2019/008294A1
The invention concerns an assembly comprising a shaft (12) and an element (16) configured to be coupled on the shaft (12) by shrink-fitting, the shaft (12) comprising an inner cavity (20) in an axial shrink-fitting portion (P12), an inte...  
WO/2019/004272A1
After a free-form surface has been machined on an elongate material 1 in a state in which a protruding portion 3 and a blade 4 are being gripped, the entire elongate material 1 deforms when gripping of the protruding portion 3 is release...  
WO/2019/005425A1
A turbine airfoil (10) includes a trailing edge coolant cavity (40f) located in an airfoil interior (11) between a pressure sidewall (14) and a suction sidewall (16). The trailing edge coolant cavity (40f) is positioned adjacent to and e...  
WO/2019/002274A1
The invention is directed to a turbomachine component (1), particularly an aerofoil (5), more particularly an aerofoil (5) of a blade (38) or a vane (40) for a gas turbine engine (10), the turbomachine component (1) comprising a first ca...  
WO/2019/001980A1
A compressor aerofoil (70) for a turbine engine. The compressor aerofoil (70) comprises a root portion (72) spaced apart from a tip portion (100) by a main body portion (102). The main body portion (102) is defined by : a suction surface...  
WO/2019/001979A1
A compressor aerofoil (70) rotor blade for a turbine engine. The compressor aerofoil (70) comprises: a root portion (72) spaced apart from a tip portion (100) by a main body portion (102). The main body portion (102) is defined by : a su...  

Matches 1 - 50 out of 22,544