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Matches 1 - 50 out of 33,810

Document Document Title
WO/2018/164786A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction. The gas turbine engine defines an upstream end and a downstream end ...  
WO/2018/164149A1
This cooling structure for a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) that is curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a second blade w...  
WO/2018/163877A1
A first turbulator 41R which is at least one of a plurality of turbulators comprises: a first section 411 which has a constant projection height from an inner surface 40S; and a second section 412 which is connected at one end to the fir...  
WO/2018/164150A1
This cooling structure for a turbine blade (1) is provided with: a cooling passage (17) formed between a first blade wall (3) that is curved in a concave shape with respect to a high-temperature gas flow passage (GP) and a second blade w...  
WO/2018/163419A1
The purpose of the present invention is to provide an intake/exhaust device capable of cooling intake air of a gas turbine by using exhaust gas of the gas turbine and having a simple configuration. [Problem] Provided is an intake/exhaust...  
WO/2018/164148A1
This cooling structure for a turbine blade (1) is provided with a lattice structure (23) formed by a first rib pair (33A) and a second rib pair (33B) which are disposed in a cooling passage (17) and overlap each other in a lattice shape,...  
WO/2018/160275A1
An additively manufactured heat exchanger and a method of manufacturing the same are provided. The heat exchanger includes a plurality of wails spaced apart to define a plurality of fluid passageways and a plurality of flow turbulators e...  
WO/2018/158537A1
A mechanical decoupler (15) at the inlet to a turbomachine is positioned on the outside of an intake casing, where radiating arms (27) meet an external casing (13) so as to partially unload a low-pressure shaft when a significant out-of-...  
WO/2018/159681A1
A turbine is provided with a turbine rotor (21), a turbine casing, turbine moving blades (24), turbine fixed blades, and a diffuser (4A). The diffuser (4A) is provided with an inner cylinder (41) which extends along the axial line, and a...  
WO/2018/157957A1
The invention relates to a turbine casing (1) for a turbine, in particular a steam turbine, having a front casing segment (3), which is formed around a turbine longitudinal axis (2) and has a first front casing part-segment (3a) and a se...  
WO/2018/159686A1
In a rotating machine (1) a tip shroud (51A) of a moving blade (50) includes: a plurality of shroud outer peripheral surfaces (53A, 53B, 53C) provided in such a way that the radial direction positions thereof are positioned further towar...  
WO/2018/156302A1
An acoustic liner can comprise a support layer including a set of partitioned cavities defining a set of cells with open faces, as well as a first and second facing sheet operably coupled to the support layer that overlie and close the o...  
WO/2018/155640A1
An axial flow rotating machine (100) comprises a rotating shaft (1), a rotor blade (4), a casing (2), and a stator blade (7). A stator blade body (70A) comprises: a stator blade first shape part (73A) in which a stator blade intermediate...  
WO/2018/156623A1
An inlet cooling system unit that is fluidly coupled to a gas turbine can include a filter module configured to filter inlet air, a chiller module configured to cool inlet air, and a framework. The framework is sized and shaped to define...  
WO/2018/155652A1
In an axial flow rotary machine according to the present invention, a structure comprises a casing-side fin (42). An upstream-side inclined surface (45) that is inclined from the upstream side toward the downstream side is provided to a ...  
WO/2018/156263A1
The present disclosure is directed to an aircraft including a fuselage to which a pair or more of wings attaches. The aircraft defines a transverse direction, a longitudinal direction, and a latitudinal direction. The aircraft includes a...  
WO/2018/155189A1
The purpose of the invention is to reduce the region in which peeling occurs in a flow channel and to increase the efficiency of pressure recovery in an expanded-diameter flow channel. A radial turbine (10A) comprises: a rotor (12) provi...  
WO/2018/155015A1
Provided are a fuel gas heater, a support structure for the fuel gas heater, and a method for cleaning the fuel gas heater, which are provided with: a hollow-shaped container (11); a gas inflow chamber (12) defined at one end of the cont...  
WO/2018/156265A1
A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the...  
WO/2018/155635A1
A turbine moving blade comprises a diametrically extending blade body (50) in which a negative pressure surface (51) that faces one way in a circumferential direction and a pressure surface (52) that faces the other way in the circumfere...  
WO/2018/155636A1
In an axial flow rotary machine according to the present invention, a moving blade (4) comprises a moving blade shroud (41) and a shroud-side fin (44), and a small gap is formed between said shroud-side fin (44) and a casing (2). The cas...  
WO/2018/150121A1
Propulsion system (8) for a single-engine helicopter (1), comprising: • a main engine (9) connected to a front drive shaft (5) and a rear drive shaft (7), respectively, suitable for driving a main gearbox (4) referred to as MGB (4) and...  
WO/2018/151784A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and an upstream end and a downstream end along the longitudinal dire...  
WO/2018/151251A1
A steam turbine is provided with: a rotating shaft (1); a moving blade (4) including a platform (43) and a moving blade main body (40); a casing (2); a stationary blade (7) including a stationary blade main body (70) and a stationary bla...  
WO/2018/146405A1
The invention relates to a turbofan (1) comprising a low-pressure compressor (3); a series of housings (9, 10) arranged downstream of said low-pressure compressor (3) for defining a primary stream, and comprising an upstream edge (19) de...  
WO/2018/146411A1
The invention relates to a turbojet (10) comprising an inlet casing (12), a low-pressure compressor (14), a high-pressure body, a low-pressure turbine (22), and an exhaust casing (24). The inlet casing and the low-pressure compressor def...  
WO/2018/146862A1
Provided is a fan blade which is made of a composite material and which will not suffer damage even if a large foreign object collides with the fan blade. A fan blade (20) is provided with a blade body (21) composed of a composite materi...  
WO/2018/147950A2
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/2018/144989A2
A filtration system for a gas turbine engine is provided. The filtration system may include a holding frame with a positioning element extending therefrom and a filter element for mounting within the holding frame. The frame of the filte...  
WO/2018/144218A1
An acoustic liner and a method of attenuating noise are provided. The acoustic liner includes a face sheet, a back sheet spaced from the face sheet, and a core layer extending between the face sheet and the back sheet. The core layer inc...  
WO/2018/140139A1
The present disclosure is directed to a gas turbine engine defining an axial centerline, a longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes one or more frames in which the frame...  
WO/2018/139131A1
A natural gas fired combined-cycle power generation system is provided with: a vaporization device, a cooling device, a circulation flow path, a pump, and a gas-turbine combined power generation device. The vaporization device includes: ...  
WO/2018/140150A1
A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the co...  
WO/2018/138154A1
The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine (10) defines an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembl...  
WO/2018/138155A1
The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more...  
WO/2018/140665A1
Vented bearing retainer and roller bearings for turbomachines, such as compressors and turbines. Axial openings in, or adjacent to, the inner circumferential surface of the bearing retainer member equalize pressure differentials on the r...  
WO/2018/140130A2
The turbine includes a first turbine rotor disc, a second turbine rotor disc, a first source of cooling fluid, and a first cooling fluid conduit. The first turbine rotor disc has a first outer circumference and a first plurality of blade...  
WO/2018/140173A1
Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turb...  
WO/2018/138296A1
The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includ...  
WO/2018/140135A1
Gas turbine engines, as well as outer walls and flow path assemblies of gas turbine engines, are provided. For example, an outer wall of a flow path comprises a combustor portion extending through a combustion section, and a turbine port...  
WO/2018/140137A1
A mounting system includes a rotatable machine, a frame circumscribing the rotatable machine, and a plurality of mounting elements. Each mounting element of the plurality of mounting elements includes a pin member and a joint member. The...  
WO/2018/139646A1
A plant provided with: a fuel supply line for supplying high-pressure fuel gas; and at least one expander which is disposed in the fuel supply line and configured to extract power from the high-pressure fuel gas by expanding the high-pre...  
WO/2018/140138A1
A gas turbine engine includes a compressor section defining a compressor exit temperature, T3. The gas turbine engine also includes a combustion section and a turbine section, with the turbine section defining a turbine inlet temperature...  
WO/2018/138730A1
A performance enhancing aspirator apparatus for improving efficiency of a gas turbine by drawing in surplus air comprises attachment members and a substantially funnel shaped casing. The attachment members are positioned radially on an e...  
WO/2018/140136A1
Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including ...  
WO/2018/138454A1
The invention relates to a system for supplying fuel to a turbomachine, comprising a fuel circuit comprising a pressurisation means (202) at the outlet (3) of said system, and a pump (1). The circuit comprises a flow rate sensor (201) ar...  
WO/2018/138428A1
The invention relates to a transmission device (6) for driving a fuel pump (1) for a turbomachine using a drive shaft of said turbomachine, said transmission comprising a planet reduction gearing (11) comprising three elements, a central...  
WO/2018/140112A1
An asymmetric inlet particle separator system (AIPS) includes a bifurcated duct system that defines an inlet for receiving inlet air. The bifurcated duct system includes a core air channel and a scavenge air channel and is configured to ...  
WO/2018/136291A1
A method of monitoring a turbomachinery is disclosed herein. The method includes measuring the pressure drop across the intake filter (66). The method further includes determining clog rate parameters for a clog rate of a filter area of ...  
WO/2018/136272A2
Methods and apparatus to control the actuation of regulators including a loading chamber are disclosed. An example apparatus includes a first pneumatic regulator including a loading chamber, the first pneumatic regulator to flow fluid to...  

Matches 1 - 50 out of 33,810