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Matches 1 - 50 out of 22,640

Document Document Title
WO/2019/097286A1
A labyrinth seal lip (5) comprises, standing on one of its lateral faces (7), a deflector (13) which channels the flow of gas tangent to the lip (5) towards the facing seal (4) so as to disturb the leakage flow (22) through the gap and d...  
WO/2019/099000A1
A gas turbine engine component (10) is repaired via the removal of the defective portion (12) and then the filling in of the resulting cavity (14) with filler material (16). The filler material (16) fills in the cavity (14) via selective...  
WO/2018/080699A8
A propeller blade (18) spanning radially from a root (32) to a tip (34) and spanning axially from a leading edge (36) to a trailing edge (38) spaced from the leading edge forming an airfoil (39) therebetween where a sweep line (62) can b...  
WO/2019/097162A1
The invention relates to a nickel-based superalloy comprising, in weight percentages, 4.0 to 5.5 % rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0 % cobalt, 0.3 to 1.0 % molybdenum, 3.0 to 5.0 % chromium, 2.5 to 4.0 % tungsten, 4.5 to 6.5 % a...  
WO/2019/096757A1
The invention concerns a device (2) for holding a centripetal air sampling member (1) for a rotor assembly comprising at least an upstream rotor disc (42a), an adjacent downstream rotor disc (42b) and a centripetal air sampling member (1...  
WO/2019/100082A1
A system for wirelessly monitoring temperatures of a gas turbine engine comprising a wireless sensor positioned on or in a component of the engine, one or more interrogating antennas capable of transmitting an RF signal to the wireless s...  
WO/2019/099009A1
A clearance control system for controlling a clearance between rotating blades and a boundary adjacent to tips of the rotating blades is provided. Electrical heating circuitry (62) may be embedded within or otherwise disposed onto a vane...  
WO/2019/091965A1
A turbine rear structure for a gas turbine engine which comprises primary and secondary exhaust gas guide vanes and wherein the second set of vanes are offset so as to be closer to one of the primary guide vanes than another.  
WO/2019/092679A1
The present invention relates to a method for the construction of rotor and stator elements of turbomachines, comprising: readying an ingot (1) of material to be machined; performing cuts in the ingot (1) so as to delimit blocks (10) of ...  
WO/2019/093075A1
This turbine blade is provided with a blade body and a plurality of cooling passageways which extend in a blade height direction in the blade body and communicate with each other, forming a serpentine flow passageway. The cooling passage...  
WO/2019/094036A1
A method of manufacturing a hard-to-weld material by a beam-assisted additive manufacturing process is presented. The method includes depositing a first layer for the material onto the substrate, the first layer including a major fractio...  
WO/2019/088992A1
A turbine blade (1) includes a tip cap (32) disposed over an outer wall (12) of a blade airfoil (10). A trench (40) is defined on a radially outer side of the tip cap (32) facing a hot gas path fluid. The trench (40) is formed by a trenc...  
WO/2019/086215A1
Method to create a good bonding between a free standing thermal barrier coating and a green CMC. By providing a (partially) sintered free standing TBC (7) which is pressed onto a green CMC substrate (4) and sintering this composite struc...  
WO/2019/087281A1
This turbine rotor blade connects to a rotation shaft and is rotated about an axis, wherein the turbine rotor blade comprises: a hub having a hub surface that is inclined with respect to the axis, in a cross section along the axis; a rot...  
WO/2019/088064A1
A method for producing a metal member comprising a first part (12) and a second part (14), which comprises: a first modeling step for modeling the first part (12) by powder bed type three-dimensional metal deposition modeling; and a seco...  
WO/2019/086213A1
A shark skin effect is achieved with a simple geometric arrangement, and can be used particularly for compressor blades.  
WO/2019/081471A1
A compressor aerofoil (70) for a turbine engine. The compressor aerofoil (70) comprises a tip portion (100) comprising a tip wall (106) which extends from the aerofoil leading edge (76) to the aerofoil trailing edge (78). The tip wall (1...  
WO/2019/083595A1
A turbine engine including: rotor blades circumferentially arrayed about a rotor wheel; a connection assembly by which each of the rotor blades connects to the rotor wheel, the connection assembly including: an axially oriented slot form...  
WO/2019/081218A1
A fine-grained structure can be achieved by using an inoculant during cold metal transfer.  
WO/2019/081860A1
The invention relates to a method for balancing a set of blades (5) intended to be arranged on a bare disc (7) of an aircraft engine, the bare disc (7) comprising a defined number of numbered cells (ai) intended to receive the same defin...  
WO/2019/077237A1
Turbomachine hollow turbine blade comprising a plurality of rising cavities (23, 25, 29, 31) communicating with a channel (18) of the blade via a plurality of standard dust-removal holes (21A, 21B, 21C) intended for the removal of dust, ...  
WO/2019/077333A1
A nickel-based alloy composition consisting, in weight percent, of: between 9.5 and 14.4% chromium, between 3.8 and 9.6% cobalt, between 0.0 and 4.0% iron, between 0.6 and 5.1% molybdenum, between 0.7 and 6.2% tungsten, between 2.6 and 3...  
WO/2019/076980A1
The invention relates to an exhaust gas turbine, comprising a turbine rotor (12) having a plurality of turbine rotor blades (2) with a turbine rotor blade height H. The exhaust gas turbine further comprises a diffuser arrangement (20) ha...  
WO/2019/076875A1
The invention relates to a device (1) for cleaning turbine blades (82) of a turbine stage (81) of a jet engine (80). Said device (1) comprises a cleaning lance (2) for insertion in a jet engine (80) through a through-opening (83), said c...  
WO/2019/077271A1
The invention relates to a turbine component comprising a substrate made from monocrystalline nickel-based superalloy comprising rhenium, which has a γ-γ' Ni phase, and an average weight fraction of chromium of less than 0.08, a sublay...  
WO/2019/074059A1
The present invention addresses the problem of providing: a heat-resistant titanium alloy member having high mechanical strength and high oxidation resistance at high temperatures, the titanium alloy member having low mechanical anisotro...  
WO/2019/074514A1
A component includes an outer wall that includes an exterior surface, and at least one plenum defined interiorly to the outer wall and configured to receive a cooling fluid therein. The component also includes a coating system disposed o...  
WO/2019/074784A1
A first component, such as a hub (10) of a gas turbine engine (2) is assembled or disassembled from a second component, such as a shaft (12) by induction heating, using a flexible heating jacket (40) that is wrapped about an outer circum...  
WO/2019/072408A1
The invention relates to an impeller for a turbocharger. The impeller (1) is mounted in a housing of the turbocharger (3) in a rotatable manner about an axis of rotation, wherein the impeller (1) and has an impeller hub (5) comprising an...  
WO/2019/070158A1
A device for locking the rotor blades of a gas turbine engine compressor on a rotor disk comprises an insert capable of engaging with a retaining window in the disk when the blade locking device is in a working position, a lock capable o...  
WO/2019/068985A1
The invention relates to a device for assembling a turbine engine, intended for centring a shaft (4) of a second module relative to a longitudinal axis (X) of the hollow central hub (21) placed in front of a first module (5), said first ...  
WO/2019/067727A1
An axial flow fan includes a hub rotatable about a fan axis and a plurality of fan blades mounted to the hub. One of the plurality of fan blades includes at least one wave extending in a span wise direction over the fan blade and at leas...  
WO/2019/065241A1
This control device controls the temperature of a shaft seal portion provided around a rotating shaft of a rotating machine to an appropriate temperature by adjusting a supply amount of cooling air supplied to the shaft seal portion. The...  
WO/2019/066750A2
Instead of cooling the turbine disk blades of the gas turbine engines using a very stressful and expensive method of stealing from the compressor air at a temperature of 650 degrees Celsius, it is possible to provide a much effective coo...  
WO/2019/064761A1
Provided is a blade in which secondary flow loss has been reduced without changing the aerodynamic design of a base blade. This blade comprises: a base blade part; and a protruding part provided on a positive-pressure surface in the vici...  
WO/2019/063384A1
The invention relates to a diffuser for a compressor, comprising - a flow channel which is delimited in the flow direction by a first lateral wall and a second lateral wall, wherein the lateral walls run at least partly divergent relativ...  
WO/2019/067465A1
A compressor for a heating, ventilating, air conditioning, and refrigeration (HVAC & R) unit includes an impeller, a shaft configured to rotate the impeller, and a fastener. The impeller includes an opening and does not include keys, spl...  
WO/2019/063329A1
The invention relates to a turbine housing (1) with a connecting piece (2), by means of which a flow fluid flows into the turbine housing (1) through a recess (3) in the turbine housing (1). The connecting piece (2) is formed, in the reg...  
WO/2019/063909A1
A turbomachine rotor blade comprising a radially outer end equipped with a heel, the heel being provided with at least one sealing wiper (3), the or each sealing wiper (3) projecting beyond the heel along a first axis (z), the first axis...  
WO/2019/058054A1
A method for producing a part from composite material comprises the following steps: - injecting into a fibrous texture (10) a slurry (BC) comprising at least one powder of refractory ceramic particles (CR) suspended in a liquid phase, -...  
WO/2019/058046A1
A method for manufacturing a part made from CMC, i.e. ceramic matrix composite material, provided with at least one cutout, and such a part made from CMC provided with at least one cutout, the method comprising the following steps: provi...  
WO/2019/057743A1
The invention relates to a blade for a turbine blade, comprising a suction-side side wall (22) and a pressure-side side wall (24) that enclose a cavity at least partially in a manner which extends along a profile centre line (32) from a ...  
WO/2019/058068A1
The invention relates to a turbine part, such as a turbine blade or a distributor fin, for example, comprising a substrate made of superalloy based on monocrystalline nickel, comprising rhenium and/or ruthenium, and having a γ'-NisAI ph...  
WO/2019/058394A1
An improved showerhead arrangement for gas turbine blades using jet impingement cooling system is disclosed. The arrangement includes impingement inserts (1) which are structurally supported and has number of holes (8) /impingement tubes...  
WO/2019/058069A1
The invention relates to a method for manufacturing a part using CMC, i.e. a ceramic matrix composite material, as well as such a part made of CMC, the method comprising the following steps: providing (E1) a fibrous reinforcement (10); i...  
WO/2019/057655A1
A vane assembly (100) comprising a plurality of vane units (1) and a connecting part (30), wherein each vane unit comprises a base (10) having a through-hole (12) positioned and extending between opposing longitudinal faces of the base, ...  
WO/2019/057424A1
A high-purity zirconium oxide layer having little sintering tendency and thus improved and prolonged thermo-mechanical properties can be produced by defining the impurities and the corresponding maximum upper limits.  
WO/2019/054685A1
The present invention relates to a large and curved thick plate support structure for a blade and, more specifically, to a large and curved thick plate support structure for a blade, the structure holding a thick plate so as to easily mo...  
WO/2019/054590A1
The present invention relates to a gas turbine blade comprising an outer structure, an inner structure, a plurality of porous slots and a cooling medium channel, wherein the outer structure is formed in an airfoil shape of which the insi...  
WO/2019/054103A1
This application jig 100 is used to apply an erosion shield member 80 to a rotor blade member 70 and is provided with: a body 10 disposed on the back side of the rotor blade member 70; a first pressing section 20 provided to the body 10 ...  

Matches 1 - 50 out of 22,640