Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 1 - 50 out of 34,180

Document Document Title
WO/2018/225923A1
A combined power generation apparatus, according to the present invention, comprises: an engine (110); a first flow line (120); a power turbine (113); a turbo charger (115); a second flow line (125); a third flow line (126); a compressor...  
WO/2018/226269A1
A flight vehicle has a propulsion system that includes an air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes an obstruction that protrudes inwardly from an ...  
WO/2018/224809A1
A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a closure for closing the inlet so as to prevent ingress of debris; and a fastening attachable to an aircraft-mounted launcher and configured...  
WO/2018/225706A1
A sound-absorbing panel to be used affixed to a jet engine of an aircraft, provided with: a resin core layer 20 having a first surface, a second surface disposed on the side opposite from the first surface, and multiple partitions extend...  
WO/2018/225922A1
A combined power generation apparatus, according to the present invention, comprises: an engine (110); a first flow line (121); a turbo charger (130); a second flow line (122); a third flow line (123); a compressor (211); a first medium ...  
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/2018/219555A1
By applying material (10, 13) on only one side (7) in the case of a revision, seal rings (1) can be easily rebuilt and reused.  
WO/2018/219856A1
The invention relates to a method and a device for increasing the efficiency of jet propulsions by recuperating effective power from the propulsion flow. A ducted fan (4), driven by a drive motor (9) via a driveshaft (1) and located in t...  
WO/2018/218526A1
An ignition nozzle device (10) comprises a nozzle wall cylinder (12), a nozzle tube (14), and an igniter (16). A mixing chamber (22) is formed in the nozzle wall cylinder. The nozzle wall cylinder comprises a front end (18) and a rear en...  
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/2018/215712A1
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/2018/211224A1
The main subject of the invention is a device (10) for centring and rotationally guiding a turbomachine shaft (12), comprising: a rolling bearing comprising an outer ring (18), a bearing mount (20), a band (28) interposed between the out...  
WO/2018/212073A1
This gas turbine has: a plurality of first cooling channels (61) that have a plurality of blade rings (50) disposed radially outward thereof where a rotational shaft serves as the center, and that extend in the axial direction and are di...  
WO/2018/212001A1
Provided is a gas turbine combustor (3) equipped with a fuel injection device (15) that has a plurality of annular fuel injection parts (25), each having numerous fuel injection ports (25a) formed therein, the gas turbine combustor being...  
WO/2018/205889A1
In a combustor (10) for a gas turbine, a head end turning scoop (12) is provided associated with at least one premix nozzle (22,24), each scoop (12) being U-shaped and having a first leg (58), a second leg (60), and a curved base portion...  
WO/2018/207913A1
In the present invention, a securing tool (4) for a heat retention block (3) covering a turbine casing main body (2) has: a securing rod (41), one end of which has an engaging part (431) that includes a protrusion (412); and a socket (42...  
WO/2018/206157A1
The invention relates to a bearing arrangement (1) for mounting a turbine rotor (2) of a turbo machine (3). The bearing arrangement comprises at least one axial bearing (4) and at least one radial bearing (5). The axial bearing is design...  
WO/2018/207754A1
This turbine housing (10) is provided with: an inner cylinder (20) forming a discharge gas flow passage (K) between a discharge gas inlet-side flange (12) and a discharge gas outlet-side flange (13); and an outer cylinder (40) covering t...  
WO/2018/208513A1
An inlet duct (106) for a gas turbine wherein the inlet duct (106) may include a gas turbine inlet interface assembly (124) and a plurality of walls (126a-d) defining a first portion (128a) of an inlet flow channel (128a, 128b). The gas ...  
WO/2018/202993A1
The invention relates to an air intake duct (10) for a compressor (12) of a gas-fuelled or diesel-fuelled turbine, comprising: – two transition sections (S3, S4) in fluidic communication with one another for the circulation of an air s...  
WO/2018/202962A1
A turbomachine comprising a ducted fan, a low-pressure turbine shaft and a reduction gearbox housed in a casing between the fan and the low-pressure turbine shaft, the fan rotor supplying airflow to a primary stream and a secondary strea...  
WO/2018/201812A1
A ducted fan (100) comprises: a duct (10), having a central axis; a duct support (20), disposed inside of the duct, and a central axis thereof being coincident to that of the duct; a fan (30), disposed adjacent to an air intake of the du...  
WO/2018/197232A1
The invention relates to an aircraft propulsion assembly (10), comprising a turbine engine surrounded by a nacelle (26) comprising an annular air-intake lip (30) extending around the turbine engine by two annular walls, inner (34) and ou...  
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...  
WO/2018/199237A1
The thermal barrier coating is provided with a ceramic layer (120) formed on a heat-resistant alloy substrate and containing ceramic substance. The ceramic layer (120) has: a first dense layer (121); an intermediate porous layer (122) la...  
WO/2018/199076A1
Provided is a clearance measurement device, which is a device for measuring the clearance between the inner peripheral surface of a casing and the outer peripheral surface of a rotary body. The device emits light having a first wavelengt...  
WO/2018/199289A1
A fuel injector (1) comprises: a fuel supply tube (8); a plurality of premixing tubes (2); a support plate (3) that supports the fuel supply tube (8) and the plurality of premixing tubes (2); a board (4) that supports downstream-side end...  
WO/2018/196198A1
Disclosed is an impeller tube-type nozzle (101) for a gas turbine, comprising an inlet section (108), a retraction section (107) and an outlet section (106). The inlet section (108) is a section of annular channel, the retraction section...  
WO/2018/198624A1
The purpose of the present invention is to monitor an industrial system to be managed with greater precision. Provided is a management monitoring system (18), comprising: realtime sensing devices (28, 34) for detecting the state of a sub...  
WO/2018/200636A1
A variable turbine geometry (VTG) turbocharger is disclosed. The VTG turbocharger may comprise a turbine section having a turbine wheel and plurality of guide vanes configured to regulate a flow of exhaust gases to the turbine wheel. The...  
WO/2018/195414A1
An engine mount device includes a housing, a carrier within a cavity in the housing, and a flexure flexibly connecting the carrier to the housing, with a pin disposed in a hole in the carrier to support an engine. A method of providing i...  
WO/2018/195122A1
This disclosure relates to various seals for sealing around exhaust pipes, such as the exhaust pipe of an aircraft auxiliary power unit. The seal can include a collar portion bounding an opening that is configured to receive the exhaust ...  
WO/2018/193049A1
The invention particularly relates to a method for determining damage, wear and/or imbalance in a transmission designed as a gear wheel transmission, particularly an epicyclic transmission (100), by means of at least one electronic senso...  
WO/2018/191214A1
A variable turbine geometry (VTG) turbocharger is disclosed. The VTG turbocharger may comprise a turbine section, a bearing section, and an actuation pivot shaft (APS) having a bearing side in the bearing section and a pressure side in t...  
WO/2018/190231A1
This gas turbine combined cycle plant is provided with: a fuel gas heating unit (30) which heats fuel gas using heating water that has been heated by a waste heat recovery boiler (12); a return valve (32) provided in a heating water retu...  
WO/2018/191170A1
The present disclosure is directed to a fuel manifold assembly for a gas turbine engine. The fuel manifold assembly defines a walled conduit through which a fuel flows in a fuel passage. The walled conduit defines a first end and a secon...  
WO/2018/189944A1
A regenerative cooler (2) is provided with a flow passage forming structure (10) having formed therein a fuel flow passage (11) to which liquid fuel is supplied. A coating (12, 12A) at least partially covering a wall surface of the fuel ...  
WO/2018/186921A2
A component for a turbine engine comprises a wall with a surface along which a hot airflow passes, a second surface along which a cooling airflow passes, and an insert mounted to the wall wherein the material used for the insert can have...  
WO/2018/186925A3
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine...  
WO/2018/186921A3
A component for a turbine engine comprises a wall with a surface along which a hot airflow passes, a second surface along which a cooling airflow passes, and an insert mounted to the wall wherein the material used for the insert can have...  
WO/2018/185087A1
Electric energy generating device (1) for installation to an exhaust conduit (2) in which an exhaust gas (9) is flowing, comprising: - a thermoelectric generator (3) comprising a hot side (4) and a cold side (5), - at least one hot side ...  
WO/2018/186925A2
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine...  
WO/2018/178538A1
Accessory relay (100) suitable for driving accessory equipment for a gas turbine engine, such as an aircraft engine, comprising a housing (101) and a plurality of gear wheels (110) inside the housing, the wheels each comprising a tubular...  
WO/2018/180773A1
Provided is a combustion device equipped with: an ammonia supply unit (6) that, by supplying primary reduction ammonia as a nitrogen oxide reducing agent to within a combustor (2) and mixing secondary reduction ammonia with combustion ex...  
WO/2018/181063A1
This combustion device (C) causes the combustion of fuel ammonia and combustion air within a combustion chamber (N), and is equipped with a combustor liner (3a) which forms the combustion chamber, a burner (3c) which is attached to one e...  
WO/2018/180781A1
Provided is a gas turbine (A) using a denitration catalyst and ammonia as a reducing agent for the denitration of combustion gas, wherein the ammonia is supplied, along with cooling air supplied from a compressor (1), to turbine vanes (3...  
WO/2018/180996A1
This combustion device uses compressed combustion air to cause the combustion of fuel ammonia within a combustion chamber, and is equipped with a combustion air cooling unit (6) that cools the combustion air by means of heat exchange wit...  
WO/2018/181030A1
This combustion device (C) is equipped with a compressor (2a) for compressing combustion air, a combustor (2b) for causing the combustion of fuel ammonia and the compressed combustion air, and an ammonia injection unit (3) for injecting ...  
WO/2018/182807A1
An additively manufactured fastener and a method of manufacturing the same are provided. The fastener includes a shank defining an internal passageway and a head defining a distribution plenum in fluid communication with the internal pas...  
WO/2018/181002A1
This combustion device (C) is provided with a combustor (3) for causing the combustion of fuel ammonia and combustion air within a combustion chamber (N), and the combustor is equipped with a cooling ammonia supply unit (3g) for mixing t...  

Matches 1 - 50 out of 34,180