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WO/2013/069775 |
This seal assembly is disposed on each of a plurality of gas burners, and inserted into a space which is demarcated by a pair of depression parts which are disposed on the lateral faces of tailpipe exhaust port flanges that are adjacent ...
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WO/2013/062040 |
This shaft sealing device is provided in an annular space between a rotor and a stator surrounding the outer periphery of the rotor, and divides the annular space in the axial direction of the rotor into a high-pressure region and a low-...
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WO/2013/062668 |
A hydrodynamic sealing system for use in an oxidizing environment includes a rotor and a sealing stator. The stator includes a solid lubricant or a surface treatment and the rotor is hardened or the stator is hardened and the rotor inclu...
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WO/2013/058112 |
A seal device comprises: three ring-shaped first vertical walls (21) which extend to the rotating body (12) side from a stationary body (11) and which are arranged at predetermined intervals in the axial direction (A) of the rotating bod...
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WO/2013/059038 |
An expander-generator is disclosed having an expansion device and a generator disposed within a hermetically-sealed housing. The expansion device may be overhung and supported on or otherwise rotate a hollow expansion rotor having a thru...
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WO/2013/054043 |
The present invention relates to a turbomachine assembly in which a foil (30) is able to cover mainly one of the bulbs (11) of the disc (10) and be held, radially with respect to the disc (10), by said bulb (11) of the disc (10) and the ...
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WO/2013/048072 |
The present invention relates to a reactive turbine apparatus that is easy to assemble. To this end, the reactive turbine apparatus includes: a rotation shaft formed of a certain length; a housing defining an inner space so as to be rota...
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WO/2013/049456 |
An apparatus and a method for repairing a component of a gas turbine engine is provided. The method includes locating a damaged area of the component, preparing a portion of the component that includes the damaged area leaving a remainin...
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WO/2013/042660 |
In this turbine (1), with regards to the distal-end portion of a blade (50) or a portion of the partition plate outer ring (11) corresponding to the distal-end portion of the blade (50), a step portion (52) having a step surface (53) is ...
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WO/2013/037849 |
A labyrinth seal (25,...,27), for sealing the annular interspace (11) between the rotor (12) and the stator (10) of a steam turbine or gas turbine, comprises a multiplicity of sealing strips (13) which are arranged in series in the axial...
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WO/2013/034385 |
The invention relates to a guide device (1) for a turbine comprising a guide vane carrier (2) and a plurality of guide vanes (3) arranged over the circumference of the guide vane carrier (2). The guide vanes 3 are fastened/clamped in the...
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WO/2013/034655 |
A rotary machine includes a machine rotor, a machine stator, a labyrinth seal disposed between the machine rotor and the machine stator, a dry gas seal disposed between the machine rotor and the machine stator, the dry gas seal being dis...
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WO/2013/035638 |
Provided is a steam turbine facility capable of recovering energy held by discharged steam and keeping the interior of a gland seal steam receiver within a predetermined pressure range. A steam turbine facility is provided with: a spill ...
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WO/2013/034837 |
The invention relates to a turbine nozzle or compressor stator vane that includes sectors (12) made of a CMC material, each of which has an inner platform (14), an outer platform (16), and blades (18). A support ring (50) made of an abra...
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WO/2013/026870 |
The invention relates to a rotor blade for a turbomachine, comprising an abradable blade tip coating (8) which has a material consisting of zirconium(IV) oxide stabilized with 2 to 12 mass percent of yttrium(III) oxide. The housing (12) ...
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WO/2013/025385 |
Polymer-based materials and processes suitable for producing panels (10), for example, panels for use in a fan shroud abradable seal (12) of a turbofan engine. Such a process includes introducing constituents of an expandable foam materi...
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WO/2013/025454 |
Processes for producing near net-shape panels and panels formed thereby. The processes include forming a preform (28) to comprise a stack of multiple plies (30) that contain an uncured expandable foam material. The preform has regions th...
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WO/2013/025384 |
A method of repairing a seal wire groove is disclosed, the groove forming an annular structure having an outer surface and an inner surface and defining an original profile when new, comprising the steps of: removing a less-than-annular ...
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WO/2013/014106 |
A centrifugal turbomachine (1) comprises a casing (2); a rotor assembly (3) including at least one centrifugal impeller (10) for a fluid flowing from an inlet side (11) to an outlet side (12) of the impeller (10 and an eye seal (20) exte...
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WO/2013/013975 |
Airfoil arrangement comprising a sealing element made of metal foam An airfoil arrangement (100) for a gas turbine comprises a first airfoil device (110), a second airfoil device (120) and a sealing element (210). The first airfoil devic...
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WO/2013/011126 |
The invention relates to a heat shield element (HS) for a gas turbine (GT) comprising an areal wall section (WS), which extends with regard to a central axis (CA) in an axial direction and a circumferential direction (CD), said wall sect...
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WO/2013/007937 |
The invention relates to a method for manufacturing a turbine-engine fan casing having, on the inner surface thereof, an abradable coating and an acoustic coating arranged downstream and/or upstream from the abradable coating. The casing...
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WO/2013/001091 |
An abradable seal system for a gas turbine comprises a rotor blade tip (7) with an abrasive coating system (9, 11) and a stationary heat shield ring (1) facing opposite to the blade tip (7) and coated with an abradable coating. The abras...
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WO/2013/001246 |
The invention relates to an arrangement for connecting at least one duct (12) to a casing (10) for distributing air towards said at least one duct (12), which comprises two sidewalls (14) opposite one another, and which comprises a perip...
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WO/2013/001240 |
The invention relates to a turbine (10) of a gas turbine engine comprising at least one turbine nozzle assembly (25) and a turbine rotor (11), said turbine nozzle assembly (25) comprising at least one internal annular platform (26), said...
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WO/2012/175274 |
The invention relates to a rotor (14) for a stationary gas turbine (10), comprising at least two rotor components (40, 42) which lie axially on one another with in each case one sealing arm section (46, 48) which is directed at the oppos...
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WO/2012/177507 |
A turbocharger (10) includes a turbine section (12), a compressor section (15) and a bearing section (20, 160). A turbine wheel (14) and a compressor wheel (17) are mounted on a shaft (40, 140) and the shaft (40, 140) is rotatably mounte...
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WO/2012/163611 |
The present invention relates gas turbine (100) comprising a device (110) and a further device (120). The device (110) comprises an outer casing (111), an inner casing (112) and a seal ring (113). The outer casing (111) and the inner cas...
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WO/2012/161920 |
A seal strip (60A, 60B, 60C, 60F, 60G, 60H, 60J) with an imperforate width-spanning portion (64) first and second rounded edges (65, 66) and one or more strip-thickening elements (67, 68, 74, 76, 82, 84, 90, 91) between the rounded edges...
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WO/2012/161904 |
A seal strip (54) with a central relatively thin portion (68) and first and second thicker side portions (70, 72) that may be wedge-shaped adjacent the central portion. Each side portion may be formed of a linear array of base-in prisms ...
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WO/2012/162016 |
A wear indication system (10) for use in turbine engines to measure the rate of gap closure between a seal holder (12) and a rotor disk in a compressor blade assembly (16) includes a support system capable of supporting a wear indicator ...
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WO/2012/160586 |
Provided is a gas turbine configured so that the rotor blades have high energy conversion efficiency. A gas turbine comprises a compressor which compresses air, a combustor to which air discharged from the compressor is supplied and whic...
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WO/2012/161906 |
Respective seals (54, 78) for the upper and lower spans (48A, 48B) of an exit frame (48) of a turbine combustion system transition piece (28). Each seal has a first strip (55, 79) and a second strip (66, 88) of a sealing material. The tw...
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WO/2012/150424 |
The invention relates to a device for sealing a nozzle (25) of a turbine (10) of a turbomachine comprising a turbine (10) rotor (11), said turbine (10) nozzle (25) comprising at least one internal annular platform (26), said turbine (10)...
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WO/2012/150425 |
The invention relates to a rotor of a turbomachine, such as a multi-flow turbojet engine fan, having a disc (4) comprising, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades (6) mounted individuall...
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WO/2012/149925 |
The invention relates to a cover device (46) for an integrally bladed main rotor body (1) of a turbomachine for preventing or reducing a cooling air flow from a high pressure side to a low pressure side through channels formed between ad...
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WO/2012/144242 |
This turbine stator vane is equipped with: multiple outside shrouds (8a) provided adjacent to each other in the circumferential direction of the turbine and forming the outer wall of a main flow path, and multiple inside shrouds (8b) pro...
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WO/2012/141858 |
A low pressure cooling system (10) for a turbine engine (12) for directing cooling fluids at low pressure, such as at ambient pressure, through at least one cooling fluid supply channel (14) and into a cooling fluid mixing chamber (16) p...
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WO/2012/136493 |
The present invention relates to a turbine (100), in particular a gas turbine. The turbine (100) comprises a first inner wall (101), a second inner wall (102), an inner casing (103) and a shield element (104). The first inner wall (101) ...
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WO/2012/136917 |
The invention relates to a sealing ring (60) intended to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring being equipped with a plurality of anti-rotation pegs (66) for preventing it from rotating...
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WO/2012/131100 |
The invention relates to a method for producing a metallic component (10) configured and designed especially for a turbomachine (100), wherein a), for a precision casting process, a wax model (20) with a wax structure (21) is produced, b...
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WO/2012/132787 |
A gas turbine is provided with: a turbine rotor blade (33); a turbine stator blade (32); a dividing ring (52) surrounding the turbine rotor blade (33) in a circumferential direction; an outer shroud (51) surrounding the turbine stator bl...
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WO/2012/130935 |
Methods and systems for controlling infiltration of ambient air into, and exfiltration of process gas out of, an organic Rankine system are described. A first sealing mechanism, e.g., a double dry gas seal, can be used to prevent exfiltr...
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WO/2012/125387 |
The propensity for gas leakage around a shaft, which extends through a bore which connects volumes of differing pressures, e.g., a turbocharger turbine housing and the ambient air, is minimized with the addition of a pair of seal rings b...
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WO/2012/125387 |
The propensity for gas leakage around a shaft, which extends through a bore which connects volumes of differing pressures, e.g., a turbocharger turbine housing and the ambient air, is minimized with the addition of a pair of seal rings b...
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WO/2012/120228 |
The invention relates to an aircraft turbine casing (30), which is to support a set of ring sectors (28) that partially define a pipe for the flow of a gas stream through the turbine, comprising a means for dynamically adjusting the radi...
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WO/2012/117016 |
The invention relates to a divisible housing having a joint seal for a fluid machine, in particular for a turbo compressor, such as a single shaft compressor. The divisible housing (1) comprises at least one first housing element (2) and...
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WO/2012/116943 |
The invention relates to a turbine (1) of a power plant, preferably a steam turbine, comprising a stator (2), which has a housing (4) and in the housing (4) at least one stator blade carrier (5, 6, 7) comprising stator blades (8), a roto...
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WO/2012/113486 |
The aim of the invention is to provide an alternative method for producing a protective layer for a rotor blade (1) of a turbomachine having a wear cap wall (4) that in relation to the axis of the turbomachine protrudes radially towards ...
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WO/2012/112366 |
A measuring assembly for use in a gas turbine engine includes an indicia portion that extends radially inwardly from an inner surface of a ring seal structure to a location radially inwardly from tips of blades mounted on a rotor. The in...
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