| Document |
Document Title |
|
WO/2019/111108A1 |
The invention relates to a method for repairing a composite substrate (1) and a protection layer (2) comprising at least one thermoplastic polymer and having at least one area of damage (5), the method comprising defining at least one ar...
|
|
WO/2019/105496A1 |
The invention relates to a component of a flow machine and to a method for producing a component of a flow machine, in particular a gas turbine or an aircraft engine, wherein the component is formed from a fibre-reinforced material, in p...
|
|
WO/2019/108421A1 |
A torque converter includes a turbine including a plurality of turbine blades and an inner radial extension radially inward from the turbine blades. The torque converter also includes a stator including a plurality of stator blades and a...
|
|
WO/2019/105742A1 |
An internally-cooled turbomachine component, comprising a main body (200) comprising a first end wall (210), a second end wall (212) spaced apart from the first end wall (210), and a sidewall (220) which extends between the first end wal...
|
|
WO/2019/105672A1 |
The invention relates to a rotor blade (10) of a turbomachine, comprising a blade root (11), a blade airfoil (12) which has a flow leading edge (13), a flow trailing edge (14), and flow-guiding surfaces (15) extending between the flow le...
|
|
WO/2019/105743A1 |
An internally-cooled turbomachine component, comprising: a main body (200) comprising; a first end wall (210), a second end wall (212) spaced apart from the first end wall (210), and a sidewall (220) which extends between the first end w...
|
|
WO/2019/108203A1 |
There is provided a component that includes a core (14) that includes a first material (16) of a metal material (24) or a ceramic matrix composite material (22). A shell (18) surrounds the core (14). The shell (18) is of a second materia...
|
|
WO/2019/108220A1 |
There is provided a ceramic matrix composite component (10) having a body (12) comprising a ceramic matrix composite material (14) and a plurality of grooves (24, 25, 26) extending from a top surface (16) of the body (12) and into the bo...
|
|
WO/2019/108216A1 |
A cooled turbine component in a turbine engine is provided. The cooled turbine component includes a brazed in heat transfer feature, the brazed in heat transfer feature including a thin film including a heat transfer feature incorporated...
|
|
WO/2019/102556A1 |
Provided are a turbine blade (34) and a turbine, wherein the turbine blade (34) is effectively cooled to increase the efficiency of an electric power generation system. According to an embodiment, the turbine blade (34) has an inlet-side...
|
|
WO/2019/101919A1 |
The present invention relates to a method for producing a multilayer film comprising aluminum, chromium, oxygen and nitrogen, in a vacuum coating chamber, the multilayer film comprising layers of type A and layers of type B deposited alt...
|
|
WO/2019/102137A1 |
The invention relates to a method for producing a part of a turbomachine coated with a thermal barrier, characterised in that it comprises the following steps: (E1) producing the part by means of additive manufacturing; (E2) electrophore...
|
|
WO/2019/101439A1 |
The invention relates to a measuring system (1) for sensing the spatial position of a straight securing pin (26) provided with a centering recess (29) at each end-face free end of said securing pin, in particular a securing pin (26) of t...
|
|
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/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/2019/099009A1 |
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...
|
