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WO/2016/133583A1 |
Turbine and compressor ring segment abradable component embodiments for turbine engines vary localized porosity or abradability through use of holes (328A-C) of desired profiles that are formed into monolithic abradable rib structures (3...
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WO/2016/133486A1 |
A ring segment system (100) for a gas turbine engine (10) is disclosed. The ring segment system (100) may be formed from ring segments (50) that circumferentially surround a rotor assembly (40). The ring segments (50) may each include a ...
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WO/2016/133982A1 |
Delamination of thermal barrier coatings ("TBC's") (276) from superalloy substrates (262) of components (260) for turbine engines (80), such as engine blades (92), vanes (104, 106), or castings in transitions (85), is inhibited during su...
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WO/2016/133582A1 |
Turbine and compressor casing ring segment components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an arra...
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WO/2016/133987A2 |
Cooling passages (99, 105) are formed in components for combustion turbine engines, such as blades (92), vanes (104, 106), ring segments (110) or castings in transitions (85), during investment casting, through use of ceramic shell inser...
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WO/2016/133579A1 |
Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have furcated engineered groove features (EGFs) (403, 404, 418, 509, 511, 512) that cut into the outer s...
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WO/2016/128663A1 |
The invention relates to a turbomachine nut (118), particularly for axially locking a bearing (110) ring (114), the nut comprising a thread (146) for screwing onto a part of the turbomachine, and locking means (152) for locking the nut a...
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WO/2016/124262A1 |
The invention relates to a brush seal arrangement (1) for sealing a gap (2) between a rotor (3) and a stator (4). The brush seal arrangement (1) comprises at least one brush seal (5) which has a brush housing (6) and a multiplicity of br...
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WO/2016/121259A1 |
This turbine is provided with a sealing device (40). The sealing device comprises: at least one step face (42) which is provided in a region of an outer circumferential surface of a rotor (5) facing a shroud (35) of a stator vane (20)in ...
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WO/2016/121740A1 |
Provided is a brush seal capable of reliably fixing a low-pressure-side plate and a high-pressure-side plate in stable positions. In an annular brush seal (1) in which a brush body (4) having a plurality of wires is held between a low-pr...
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WO/2015/102953A9 |
A device and methods are provided for controlling blade outer air seal of a gas turbine engine. In one embodiment, a method includes receiving blade outer air seal clearance from an integrated sensor actuator, determining blade outer sea...
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WO/2016/121207A1 |
A rotary machine is provided with a seal device capable of limiting fluid flow through the gap between at least one stationary member and at least one rotating member. The seal device is provided with: a pressure loss body mounted to the...
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WO/2016/118138A1 |
A gas turbine engine (10) with a seal system (12) for a turbine ring segment assembly is disclosed. The seal system (12) may include a seal plate retention device (16) that retains a seal plate (18) between adjacent ring segments positio...
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WO/2016/117246A1 |
A seal device (100) for a turbine having: at least one step surface (102A) provided to the diametrically outer surface of a vane facing a first diametrical gap (30) or to the outer peripheral surface of a rotor facing a second diametrica...
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WO/2016/012715A9 |
The main subject matter of the invention is a system (1) for supplying pressurised air installed in an aircraft turbine engine, configured to supply pressurisation air to a portion of the aircraft for using compressed air from pressurisa...
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WO/2016/103340A1 |
A nozzle structure (3) is provided between a rotor (2) which rotates about an axis (O) and a casing (1) which surrounds the rotor (2) from the outer peripheral side. The nozzle structure (3) comprises: an outer ring (20) which is dispose...
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WO/2016/102100A1 |
The invention relates to an expansion machine (20), comprising an output shaft (24) and a shaft sealing ring (25) that interacts with the output shaft. The expansion machine (20) has an inflow region (21) and an outflow region (22). Duri...
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WO/2016/102128A1 |
The invention relates to a radial compressor for a turbocharger, in particular of an internal combustion engine, and to a turbocharger comprising such a radial compressor. The invention further relates to a method for operating such a ra...
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WO/2016/097632A1 |
The present invention relates to a turbine assembly (10) of a turbine engine (1), comprising at least: a first bladed rotor (12), a bladed stator (13) and a second bladed rotor (14) arranged in series, the rotors (12, 14) being mounted o...
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WO/2016/096231A1 |
The invention relates to a shaft seal arrangement, comprising a first seal (1), a second seal (2) and a third seal (3) which are arranged in series between a product side (15) which is to be sealed and an atmosphere side (16), wherein th...
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WO/2016/098755A1 |
The purpose of the present invention is to provide a shaft seal mechanism that, even if pressing force is applied to thin-plate seal pieces, can suppress deformation due to the pressing force and prevent abrasion due to contact with a ro...
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WO/2016/098753A1 |
Provided is a shaft sealing mechanism that, by making the pressure of fluid that flows between thin-plate seal pieces uniform, can eliminate the fluid pressure difference that acts on an upper surface and a lower surface of the thin-plat...
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WO/2016/098752A1 |
Provided is a shaft sealing mechanism wherein the flexibility of thin-plate seal pieces can be maintained and vibration of the thin-plate seal pieces can be suppressed by partially thickening the thin-plate seal pieces. A shaft sealing m...
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WO/2016/100636A1 |
A radial seal and radial seal assembly (10) are disclosed. An embodiment of seal assembly may include an inner rotating shaft (20) with inner rotating shaft fluid feed holes (22); a primary segmented seal (30); a secondary segmented seal...
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WO/2016/096420A1 |
The invention relates to a diversion guide device (26) in the labyrinth seal (25) in the large intermediate base (19) for diverting the leakage steam in the circumferential direction (28) in order to thereby obtain a cooling effect in th...
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WO/2016/095940A1 |
The invention relates to a turbocharger having a swing vane nozzle assembly - VGT - (120). The turbocharger (100) comprises a turbine housing (102) and a bearing housing (104). The swing vane nozzle assembly (120) comprises a front nozzl...
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WO/2016/093811A1 |
A compressor is provided including a compressor end-wall having a casing and a hub. The compressor further includes at least one set of rotor blades, one set of stator blades, and a plurality of end-wall treatments spaced apart from each...
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WO/2016/082956A1 |
The invention relates to a turbine housing assembly, comprising a first tube-like housing part (12), in particular an outer housing of a steam turbine, and a tube-like second housing part (14), in particular an exhaust-steam housing of t...
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WO/2016/078980A1 |
The invention relates to an exhaust-gas section (12) for a gas turbine (1), comprising a surrounding shroud (42, 44) having a first opening (48), which is arranged in a region of the exhaust-gas section (12) that has a pressure lower tha...
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WO/2016/080136A1 |
This turbine rotor blade (26) used for a turbine is provided with: an airfoil section (30) which has an airfoil shape formed by a ventral surface (31) and a dorsal surface (32); and one or more squealer ribs (40, 42, 44) which are dispos...
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WO/2016/071620A1 |
The invention relates to a turbine blade (1) of a turbine engine including an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14), and a squealer tip (2) at the top thereof, wherein said squealer tip (2) i...
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WO/2016/071224A1 |
A sector (2) for the assembly of a stage (1) of a turbine comprises a central (2a) and a peripheral portion (2b); a plurality of blades (6) attached between the central (2b) and the peripheral portions (2a); a first (16) and a second sid...
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WO/2016/072734A1 |
An impulse turbine system of an independent type wing is disclosed. The impulse turbine system according to an embodiment of the present invention is characterized by an inlet through which a working fluid flows, and in that working flui...
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WO/2016/068857A1 |
A seal assembly (12) between a transition seal structure (14) associated with a downstream end (16) of a transition duct (10) and a vane seal structure (18) associated with an upstream end (20) of a vane structure (22) in a first row van...
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WO/2016/068859A1 |
An airfoil attachment system (10) for a modular turbine vane (12) of a gas turbine engine (14) including an outer attachment system (10) with forward and aft radially extending axial hooks (20, 22) configured to be coupled directly to a ...
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WO/2016/066932A1 |
The invention relates to a rotor vane for a turbine engine, comprising a body (170) locally defining a blade provided at the radially outer end with a root (33), characterised in that the rotor vane also comprises at least one sealing el...
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WO/2016/068855A1 |
An active turbine blade tip clearance control system (10) for increasing efficiency of a turbine engine (12) by reducing the clearance between a tip (14) of a turbine airfoil (16) and a radially adjacent component of the turbine engine (...
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WO/2016/068159A1 |
The present invention is provided with: a plurality of arc-shaped grooves (23) that are formed side by side in the axial direction with respect to an inner circumferential surface of a housing (22) of a turbine; and abradable seal rings ...
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WO/2016/063604A1 |
This axial flow turbine is provided with: a rotor having a plurality of rotor blades on an outer periphery thereof; and a stationary member provided on the outer periphery side of the rotor and having an annular wall face facing the tip ...
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WO/2016/064393A1 |
A gas turbine engine (10) having a turbine blade tip clearance control system (12) for increasing the efficiency of the engine (10) by reducing the gap (14) between turbine blade tips (16) and radially outward ring segments (18) is discl...
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WO/2016/064389A1 |
A clearance control system includes an electrically powered radiant heater (62a, 62b, 62c, 62d) supported to a radially inner surface of an outer casing (53) for a turbine engine (10), and an absorption surface (28s, 50s) on a radially o...
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WO/2016/061075A1 |
A process of forming a turbine engine seal includes the steps of: providing a flat strip of material; roll forming the flat strip of material forming an asymmetric profile in the flat strip of material; coiling the formed asymmetric prof...
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WO/2016/059348A1 |
The invention relates to a rotary assembly for a turbine engine, comprising a rotor with two consecutive rotor stages (10a, 10b) equipped with a plurality of movable vanes (20), and an annular rotor collar (50) connecting the two consecu...
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WO/2016/055606A1 |
The invention relates to a device (10) for influencing the flow in a turbomachine (1), which device comprises a housing (1a) and at least one blade ring (9), which has a plurality of blades (15) and rotates within the housing (1a). There...
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WO/2016/054084A1 |
A porous media ventless thrust bearing seal is disclosed. The porous media thrust bearing may include a primary porous media thrust bearing also serving as a seal ring including porous media positioned over a plenum and a port connected ...
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WO/2016/050642A1 |
The invention relates to a connection arrangement (1) of a compressor guide disk (2) of a compressor, said compressor guide disk being equipped with a plurality of guide vanes. The connection arrangement is constituted of at least two ar...
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WO/2016/051054A1 |
The invention relates to a mobile vane (34) for a turbine engine, comprising a root (41) designed to be inserted into a receiving element (62) of a rotor disk (38) for a turbine engine, a platform (48) carried by the root (41), and a bla...
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WO/2016/050641A1 |
The invention relates to a connection arrangement (1; 101) of a compressor guide disk (2; 102) of a compressor, said compressor guide disk being equipped with a plurality of guide vanes (107). The connection arrangement is constituted of...
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WO/2016/052177A1 |
In order to improve performance and ensure safety of an appropriate clearance between a turbine casing side and a rotor blade, a gas turbine, a combined cycle plant, and an activation method of a gas turbine of the present invention are ...
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WO/2016/050640A1 |
The invention relates to a sealing arrangement (11) for sealing a gap between two components (13, 15) lying with the gap sides flat against one another, wherein each component (13, 15) has grooves in the gap side surfaces lying opposite ...
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