| Document |
Document Title |
|
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...
|
|
WO/2019/001981A1 |
The present invention relates to a turbine assembly (10) and a method of assembling such an assembly. The turbine assembly (10) comprises a basically hollow aerofoil (12), an impingement tube (15), and an impingement tube sleeve (200). T...
|
|
WO/2019/003590A1 |
This turbine blade comprises: a blade part which has a hollow part extending along a blade height direction, and in which is formed a plurality of film-cooling holes aligned along the blade height direction; and an insert which is provid...
|
|
WO/2019/005121A1 |
The present invention is directed to a component (10) including a substrate (12) of a ceramic matrix composite material (14); a thermal barrier coating layer (18) disposed over the substrate (12); and an intermediate thermal protection a...
|
|
WO/2018/237101A1 |
The present invention is generally related to the attachment of ceramic matrix composite high pressure turbine blades to a rotor disk. To improve structural integrity and minimize interlaminar tensile stress, a root attachment (10) havin...
|
|
WO/2018/232539A1 |
The present invention relates to a high-speed dewatering and pulverising turbine (1) for obtaining solid pulverised particles and separating the water present, which is formed by: a) a stator (6) having circular geometry with a duct (7) ...
|
|
WO/2018/236618A2 |
A repair method (72) for extending a service life of a power turbine disk (12) having corrosion damage, wherein the power turbine (14) includes stages (16, 18, 20, 22) and interstage gaps (26, 28, 30, 32). The method (72) includes conduc...
|
|
WO/2018/229409A1 |
A coated turbomachine part comprises a substrate (21) and a layer for protection against the calcium and magnesium aluminosilicates CMAS (24) present on the substrate (21). The layer (24) comprises a first phase (240) of a material for p...
|
|
WO/2018/230411A1 |
An axial flow rotating machine is provided with: a rotor (20); a plurality of stator vanes (42); and a medium flow modification member (60). The stator vanes (42) include an inner shroud (44) and one or more seal fins (49). A rotor shaft...
|
|
WO/2018/229406A1 |
A coated turbomachine part (20) comprises a substrate (21) and a layer for protection against the calcium and magnesium aluminosilicates CMAS (22) present on the substrate (21). The protective layer (22) comprises a first phase (220) of ...
|
|
WO/2018/226219A1 |
Methods (1000) for structural braze repair of damaged industrial machine components, e.g., gas turbine engine components (10). The method includes the step of placing a bilayer braze material (200) onto a surface (12) of the component. T...
|
|
WO/2018/224574A1 |
The invention relates to a turbine blade (1) for a gas turbine, comprising a blade platform (2) and a blade body (3) which protrudes in a longitudinal direction (L) from the blade platform (2), has a circumferential wall (4) with a sucti...
|
|
WO/2018/222326A1 |
A blade (10) for a turbine engine that includes an internal cooling system (56) formed from at least one cavity (58) positioned within a generally elongated airfoil (12). A squealer tip (36) and at least one densified oxide dispersion st...
|
|
WO/2018/221597A1 |
The present invention minimizes decreases in strength in a blade root section when a composite material is used in a moving blade. Provided is a composite material blade (1) that is formed by layering composite material layers in which r...
|
|
WO/2018/219587A1 |
The invention relates to a method for cleaning a receiving groove (4) formed on a rotor (2) of an axial flow machine, said receiving groove serving to receive a blade root of a rotor blade. In said method, an elongate base body (6) of a ...
|
|
WO/2018/222174A1 |
A service apparatus for use in maintaining a turbine assembly (100) includes a carriage (132, 304) configured to move through a cavity of the turbine assembly (100), a motorized system (218, 500, 600, 700, 800) coupled to the carriage (1...
|
|
WO/2018/221577A1 |
This blade vibration monitoring device comprises: a rotary machine that is provided with a rotation shaft that extends along an axis and a plurality of moving blades that have moving blade bodies that extend radially from the rotation sh...
|
|
WO/2018/218530A1 |
Provided is a centering and twist lock combination mechanism (10) for a multistage high-speed steam turbine, comprising a rotary shaft (12) and a plurality of stage impellers (16, 18, 20, 22) mounted on said rotary shaft (12); said plura...
|
|
WO/2018/219611A1 |
In summary, the invention relates to a compressor stator vane (14) for axial compressors (10), comprising a cantilevered airfoil (22) attached to a compressor casing (18) via a blade root, the airfoil (22) comprising an airfoil tip (28) ...
|
|
WO/2018/221596A1 |
The present invention minimizes wear in a turbine disk and a blade root section of a moving blade when a composite material is used in the moving blade. This composite material blade (1) comprises a blade section (10) and a blade root se...
|
|
WO/2018/222192A1 |
An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, wh...
|
|
WO/2018/215207A1 |
The invention relates to a turbine blade (1), in particular a rotor blade or guide vane, comprising a blade body (3) which is at least substantially radially penetrated by a cooling channel (12), and a sheet metal insert (15) which is in...
|
|
WO/2018/215143A1 |
An aerofoil (200) for turbo machinery. The aerofoil comprises a first wall (202) having an outer surface (206) and an inner surface (208), and a second wall (204) having an outer surface (210) and an inner surface (212). The first wall a...
|
|
WO/2018/215718A1 |
In order to limit the air flow required to cool its blade member, a blade (30) for an aircraft turbomachine turbine comprises, in its blade member (34), a main passage (50) configured to collect a main air flow (F1) from an air inlet and...
|
|
WO/2018/215323A1 |
The invention relates to a method for producing a vibration-damping structure combination (18) for damping vibrations for movable masses (10), said structure combination having a first structure (2) and a further structure (3), the furth...
|
|
WO/2018/215370A2 |
A gas turbine engine rotor disc is presented. The rotor disc includes a hub, a web, a blade retention arrangement, a rotational axis, a first axial side and a second axial side. The hub has a central bore around the rotational axis. The ...
|
|
WO/2018/217213A1 |
System (10) and methods (1000) for structural braze repair of high gamma prime nickel base gas turbine components (1). The system may include a controller (200) operably connected to a heating system (100), e.g., a vacuum furnace, for co...
|
|
WO/2018/215519A1 |
The invention relates to a method for producing a turbine blade (1), wherein the turbine blade (1) is manufactured by means of an additive manufacturing technique, wherein the turbine blade (1) is formed section-by-section comprising a c...
|
|
WO/2018/215712A1 |
The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage (50...
|
|
WO/2018/211222A1 |
The invention relates to a method for regulating the internal temperature of the vanes of an impeller comprising a circuit for supplying cooling gas and a plurality of vanes (100) each comprising a pressure-side wall (108) and a suction-...
|
|
WO/2018/209374A1 |
The invention relates to a method for improving the wear resistance of a highly loaded component provided with a corrosion protection layer, according to which a chemical nickel layer is deposited on the component as a corrosion protecti...
|
|
WO/2018/206860A1 |
Translational flight is provided by a propeller or rotor. There are single propellers or rotors and contra-rotating double propellers or rotors. The first propeller or rotor evacuates the depression in front of the propeller or rotor for...
|
|
WO/2018/206306A1 |
The invention relates to a method for maintaining an axial-flow turbomachine (1), which has a support structure (2) and a plurality of axially adjacent guide vane rings (3, 4, 5) each of which has a plurality of guide vanes (6), each gui...
|
|
WO/2018/207702A1 |
Provided are a composite material blade and a method for manufacturing the composite material blade such that the degree of contour and precision of thickness can be sufficiently ensured, and the manufacturing cost can be reduced. The co...
|
|
WO/2018/208577A1 |
An axial compressor (12) of a turbine engine (10) includes a plurality of disk and spacer pairs (14) oriented along a common axis of rotation. Each of a disk (16) and a spacer (18) of the disk and spacer pairs (14) has a contacting face ...
|
|
WO/2018/202738A1 |
These new thrusters simultaneously use wheels of the CARPYZ THRA "Turbo Powered Helicopter Reactor" type and wheels of the CARPYZ TaG ''Bucket Turbines'' type or wheels of the CARPYZ TaC ''Scoop Turbines" type, representing real global t...
|
|
WO/2018/198932A1 |
A shaft 13 for turbo chargers comprises a low-strength section 25 set to a breaking strength at which same breaks when a preset prescribed load is applied, said section being in an area between a compressor-side bearing 15 and a compress...
|
