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WO/2019/224463A1 |
Angular sector of a fixed blading ring of a turbomachine (10), in particular of a stator or distributor, said sector extending through a given angle about an axis A of said ring and comprising, with respect to said axis A, a radially out...
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WO/2019/220042A1 |
Turbomachine stator element (50), extending around a longitudinal axis, the element comprising at least one first stator vane (1) and at least one second stator vane (1') circumferentially adjacent to the first stator vane (1), each firs...
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WO/2019/215913A1 |
This shroud assembly for a gas turbine comprises a folder having a through-hole, a plate-shaped shroud body made of a ceramic-matrix composition material covering the folder from the diametrically inward side, and a plate-shaped insertio...
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WO/2019/208030A1 |
In a combined cycle plant and a method for operating the same, the combined cycle plant is provided with a gas turbine (11), a waste heat recovery boiler (12), and a steam turbine (13), and is also provided with a low-pressure gland stea...
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WO/2019/202234A1 |
A turbine ring assembly comprises a plurality of adjacent ring sectors (10) forming a turbine ring (1), each ring sector (10) having a platform (12) with an inner face defining the inner face of the turbine ring (1) and an outer face fro...
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WO/2019/197750A1 |
The invention concerns an aircraft turbomachine, comprising at least one tubular element (12), such as a rotor shaft, and at least one rotor wheel extending around said tubular element (12) and comprising a disk (8b) carrying, at the out...
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WO/2019/197743A1 |
The invention relates to a cooling device (21) extending circumferentially around a turbine engine casing (1), such as, for example, a turbine casing (7), comprising a support (24) extending axially and intended to be attached to the cas...
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WO/2019/193267A1 |
Cooling device (21) extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support (24) extending axially and designed to be secured to the casing, at least one cooling tube extending circumferen...
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WO/2019/185713A1 |
The invention relates to a turbine rotor blade (10) for a gas turbine, comprising a metal blade airfoil (16), which has a leading edge (18), against which a hot gas (S) can flow and from which a side wall (22) on the suction side and a s...
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WO/2019/190541A1 |
A shroud (6, 7, 10) assembly for a turbine engine includes a seal (50) for sealing a gap (30) between a first mate face (22) of a first shroud segment (20a) and a second mate face (24) of a circumferentially adjacent second shroud segmen...
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WO/2019/187435A1 |
This gas turbine for an aircraft comprises: a moving blade (24) having a moving blade body (41) extending diametrally outward from a rotor that rotates about an axis, and a fin (43) protruding from an outer peripheral surface (42a) of a ...
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WO/2019/185526A1 |
The invention relates to a turbine blade (10) for a gas turbine having a blade leaf (16) comprising a front edge (18) around which a hot gas (S) can flow, from which a suction side wall (22) and a pressure side wall (24) extend to a rear...
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WO/2019/190477A1 |
A sealing arrangement (10) in a gas turbine engine to seal a gap between first and second turbine components (12, 14) is provided. The sealing arrangement includes a first arcuate feather seal (16) connected to an anchoring assembly (18)...
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WO/2019/180366A1 |
The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23)...
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WO/2019/178469A1 |
Power recovery turbines can be used debottlenecking of an existing plant, as well as recover electric power when revamping a plant. A process for recovering energy in a petroleum, petrochemical, or chemical plant is described. A fluid st...
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WO/2019/174788A1 |
A sealing system is described for effecting a seal of a gap (G1; G2) in a turbomachine (1) between a first structural member (21; 23) and a second structural member (31). The sealing system includes a sealing apparatus comprising a seali...
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WO/2019/177600A1 |
A cooling assembly comprises a coolant source chamber inside an airfoil that directs coolant inside the airfoil that extends between a hub end and a tip end that includes a tip body and tip rail along a radial length. A first body coolin...
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WO/2019/175091A1 |
The invention relates to a method for controlling a gap minimization for an adjustable gap between a rotor and a housing of a gas turbine. This is carried out on the basis of a correlation extracted from simulation data. If the actual va...
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WO/2019/177599A1 |
A turbine engine (32) includes at least one blade (10) that includes an airfoil (12) extending span-wise along a radial direction (Ra). The turbine engine includes a shroud (26) positioned along a tip end (22) of the airfoil (12) extendi...
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WO/2019/171495A1 |
This shroud mounting structure for a gas turbine is provided with: a support (11) provided radially inside the casing of the gas turbine around the axis of the gas turbine; and a shroud assembly (12) which is mounted to the support (11) ...
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WO/2019/168590A1 |
A gas turbine engine includes a first passage 19 formed by an exterior wall 18 of a combustor and an inner wall 17 within the gas turbine engine and a second passage 20 formed by the inner wall 17 and a rotating arm 16. A pre-swirl cavit...
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WO/2019/166734A1 |
Method for controlling a play between apexes of vanes of a high-pressure turbine of a gas turbine aircraft engine and a turbine shroud, comprising the control of a valve which supplies an air flow to the turbine shroud, this method furth...
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WO/2019/160013A1 |
A seal segment (11) comprises: a seal body (13) having a plurality of thin-plate seal pieces (20) that extend at an incline relative to forward in a rotational direction (Bc) of a rotating shaft as the pieces draw farther inward in the d...
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WO/2019/156666A1 |
A transition-to-turbine seal assembly, and method for manufacturing same are provided. The method allows forming an arcuate seal piece (110) including a first sealing flange (112) and a second sealing flange (114). Each sealing flange de...
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WO/2019/151221A1 |
This axial flow rotary machine is provided with: a rotor; a casing; a movable blade stage including a movable blade and an outer circumferential-side blade ring connected to an outer circumferential-side end of the movable blade; and a m...
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WO/2019/149474A1 |
The invention relates to a sealing element (21) and a rotor of a gas turbine having at least one rotor disc (01) and having an annular rotor component (11) arranged adjacently to the rotor disc (01) and having a plurality of sealing elem...
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WO/2019/145809A1 |
A rotating turbomachine provided with a fluid sealing device, comprising an extensible/dilatable bellows piston to make a sealing surface abut against a rotor disc, or against the head of the shaft, therefore confining the working fluid ...
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WO/2019/141671A1 |
The invention relates to a molded article, such as for example a turbine component, in particular also a guide vane or rotor blade of a gas turbine, and/or a component of an exhaust gas manifold, which is made at least in part of CMC, i....
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WO/2019/135758A1 |
An induction heater is employed with a gas turbine engine (100) in order to heat a static component (22) of the gas turbine engine (100). The heating of the static component (22) is performed such that the clearance space between the sta...
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WO/2019/131011A1 |
This aircraft gas turbine is provided with a rotor, a moving blade (24), a casing, a stationary blade (26), and a guide member (53). The moving blade (24) has fins (43) projecting from the outer peripheral surface (42a) of a moving blade...
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WO/2019/122625A1 |
Disclosed is an aircraft turbine engine having a longitudinal axis A and comprising a reduction gear, at least one turbine shaft, an upstream end of which is connected to an input shaft (8) of a reduction gear, a fan, one shaft (3) of wh...
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WO/2019/122541A1 |
The invention relates to a turbine wheel (34) comprising a plurality of blades connected to an annular platform (24) carrying annular lips (36, 38). According to the invention, either the upstream lip (38, 46) or the downstream lip (36) ...
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WO/2019/115999A1 |
Apparatus and methods for measuring clearance are disclosed. In one arrangement, a sensor is used to output a signal that is dependent on a separation between the component and the reference structure. A passage event integration compris...
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WO/2019/110210A1 |
A heat shield (60) for a gas turbine engine (10), the heat shield (10) comprising a main body (61) having a first surface (70) and a second surface (72), the first surface (70) being exposed to a hot working gas in use, a plurality of wa...
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WO/2019/110934A1 |
Coating with property gradient intended to be affixed by additive manufacturing to an inner wall of a housing (46) mounted at the periphery of mobile rotor blades of a turbomachine, the coating comprising, as superposed layers, from an o...
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WO/2019/106286A1 |
The invention relates to a method for measuring the flow rate of cooling air in a cooling air circuit (13) of a casing (121) of a high-pressure turbine (9) of a turbomachine (1). The invention is characterized in that sensors (21, 22, 24...
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WO/2019/106024A1 |
A seal segment (128) for a machine (100) includes a circumferentially extending stationary seal body (200) configured to be coupled to a casing (110) of the machine, and a support member (204) extending radially inward from the stationar...
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WO/2019/102124A1 |
An abradable structure (36) is provided, with regions (44, 45, 46) with lower resistance to wearing produced by labyrinth seal lips (4, 5), at specific points in the axial direction of the turbomachine, where lip interference could cause...
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WO/2019/097058A1 |
The invention relates to a steam turbine (100, 200), comprising: an inflow housing (109); nozzles (115) fixed in the inflow housing; a rotor (121) having a wheel disk (119) and wheel blades (117), a wheel intermediate space (143) lying b...
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WO/2019/097905A1 |
This annular seal for a gas turbine is provided with: a first part extending in the circumferential direction on one end side in the axial direction and comprising a first groove opening on the one end side in the axial direction; and a ...
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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...
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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...
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WO/2019/083475A2 |
The invention relates to the construction of a woven cloth layer (3) designed in a way that it will be placed between metal sheets (2) in order to support them in the sealing element (1) which is mounted to provide sealing around the rot...
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WO/2019/082737A1 |
This axial-flow fluid machine is provided with: a holding ring (30) holding a stationary blade train; a casing (20) supporting the holding ring (30); and an eccentric pin (80). An engagement part (23) of the casing (20) has a protruding ...
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WO/2019/081861A1 |
The invention relates to a retention device (101) for at least one cooling tube (120) of a cooling system (100) for a turbomachine case (10), the case (10) extending about an axial direction (X) of the turbomachine, the retention device ...
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WO/2019/077251A1 |
Aircraft turbomachine (100) comprising a first channel (200) enabling communication between a high pressure compressor (30) and a high pressure turbine (50), a second channel (400) enabling communication between the high pressure compres...
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WO/2019/074389A1 |
The present invention provides a micro compressor seal arrangement to minimize a working medium flow from a high pressure area to a low pressure area through a gap is presented. The micro compressor seal arrangement comprises a rotor ...
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WO/2019/075283A1 |
A thrust bearing assembly for a turbocharger includes a first thrust portion (50) disposed on a turbocharger shaft of the turbocharger, a second thrust portion ( 52) disposed on the turbocharger shaft and spaced axially from the first th...
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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...
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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...
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