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WO/2015/152381A1 |
Vane arrays define a flow path (R) through which a working fluid (G) flows and are formed in an annular shape by including a plurality of vane dividers (10) in a circumferential direction, each vane divider including a vane body (11). Th...
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WO/2015/147821A1 |
A stator vane segment (10) including a connection system (12) that enables stator vane (14) alignment while enabling an individual stator vane (14) to be replaced is disclosed. The stator vane connection system (12) may include a radiall...
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WO/2015/146854A1 |
Provided is a split ring cooling mechanism that can efficiently supply cooled air and that can efficiently cool a split ring. Also provided is a gas turbine equipped with the split ring cooling mechanism. A split ring cooling mechanism t...
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WO/2015/147967A1 |
The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least one beam. An anti-vibration seal is disposed in contact with beam and operative to mitigate an externally induced vib...
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WO/2015/138027A2 |
One exemplary embodiment according to this disclosure relates to a system includes a blade outer air seal (BOAS), and a meter plate. A portion of the meter plate is provided radially outward of a radially outermost surface of the BOAS.
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WO/2015/136522A1 |
A fluid flow system comprising a supply line, a fluid control unit and at least one end user; wherein fluid flow through the system is facilitated only upon a certified verification signal generated by the end-user and certifying said ve...
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WO/2015/132012A1 |
The invention relates to a turbine housing having a seal arrangement (11) for sealing off a gap between two components (13, 15) which bear areally against one another at the gap side, which components can be assembled only by means of a ...
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WO/2015/132013A1 |
The invention relates to a sealing arrangement (11) for sealing a gap between two components (13, 15) which bear flat against one another on the gap side and which can be assembled only by means of a transverse movement, wherein each com...
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WO/2015/133313A1 |
A seal structure (2) for sealing a gap between the outer circumferential surface (54) of a rotor (51) rotating around an axial line and the inner circumferential surface (13) of a stator (10) arranged so as to surround the rotor (51) fro...
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WO/2015/133421A1 |
A support device (5) supports an inner member of a secure body including an inner member arranged in the periphery of a rotating body and divided vertically, and an outer member arranged in at least part of the periphery of the inner mem...
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WO/2015/130328A1 |
A turbine abradable component (160), comprising: a support surface for coupling to a turbine casing; an abradable substrate coupled to the support surface, having a blade facing substrate surface with a pattern of respective interfacing ...
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WO/2015/130497A1 |
A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing sur...
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WO/2015/130355A2 |
A blade tip clearance system includes first and second control rings. The first control ring has a first coefficient of thermal expansion (CTE) and a first thermal response rate. The second control ring is located radially outward of and...
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WO/2015/130522A1 |
Turbine casing abradable component having an abradable surface with ridges (1322) projecting from the abradable surface, separated by grooves (1328). The ridges have one or both sidewalls (1325, 1326) inclined against the opposing turbin...
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WO/2015/130524A1 |
Turbine casing abradable component having an abradable surface (1300) with a compound angle planform pattern of grooves and ridges (1302) defined by a pair of forward and aft linear segment portions (1302A, 1302B) that are conjoined by a...
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WO/2015/130528A1 |
Thermal barrier coatings (TBCs) for turbine engine components are applied over engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC. The ESF...
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WO/2015/130523A1 |
Turbine and compressor casing abradable component embodiments for turbine engines, with nested loop pattern abradable surface ridges and grooves. The nested loops comprise nested fully closed loops or a spiraling maze pattern loop. Some ...
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WO/2015/128724A1 |
A turbocharger includes a compressor housing, a bearing housing, a liquid gasket, and a recessed portion. The bearing housing is fixedly fastened to the compressor housing. The liquid gasket is configured to seal fastening surfaces of th...
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WO/2015/130538A1 |
Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section ridges that reduce, redirect and/or block blad...
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WO/2015/128193A1 |
The invention relates to a method for operating a stationary gas turbine (1) at partial load, comprising at least one compressor (11), at least one expansion turbine (14) and a combustion chamber (12) provided with at least one burner (1...
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WO/2015/130520A1 |
Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting alternating rows of first and second height ridges in planform patterns, to reduce, redirect and/or block...
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WO/2015/130519A1 |
A turbine abradable component includes a support surface and a thermally sprayed ceramic/metallic abradable substrate coupled to the support surface for orientation proximal a rotating turbine blade tip circumferential swept path. An elo...
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WO/2015/130536A1 |
Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of first ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage dow...
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WO/2015/130535A1 |
Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of stepped first ridges in planform patterns, to reduce, redirect and/or block blade tip airflow lea...
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WO/2015/130525A1 |
Turbine and compressor casing abradable component embodiments for turbine engines, with composite, non inflected, bi angle, "hockey stick" like pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstr...
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WO/2015/130371A2 |
A directional solidification apparatus includes a mold heating chamber, a solidification chamber, and a gas source. The solidification chamber is adjacent the mold heating chamber for solidifying molten metal formed from an air melt allo...
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WO/2015/130537A1 |
Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of ridges in planform patterns, establishing upper and lower wear zones. The lower wear zone reduces...
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WO/2015/130380A2 |
A gas turbine engine component includes a structure including a first wall and a second wall that provide a cooling passage. The cooling passage extends a length from a first end to a second end. A cluster of impingement inlet holes is p...
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WO/2015/121592A1 |
The invention relates to a clamping system (1) comprising a clamping jaw (7) mounted on the shaft of a pneumatic or hydraulic cylinder (4), wherein said cylinder has a structure which drives the clamping jaw towards its clamping position...
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WO/2015/121407A1 |
The invention relates to a component (10) which can be subjected to hot gas for a gas turbine, said component having at least one wall, which comprises a first surface (26) as far as an edge (28), the first surface (26) being intended fo...
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WO/2015/120997A1 |
The present invention relates to a housing device (100) for a steam turbine and a manufacturing method therefor. The housing device (100) comprises a housing body (101) which extends along an axial direction of a turbine shaft of the ste...
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WO/2015/121008A1 |
The invention relates to a component (1) for a turbomachine, the component (1) comprising a coating for minimizing thermal gradients within the component (1), the coating comprising a first coating (2) on at least a portion of a surface ...
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WO/2015/119687A2 |
One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the sec...
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WO/2015/119699A2 |
A seal component for a turbomachine includes a stator platform configured to be disposed on an end of a stator airfoil and a scoop disposed on a first edge of the stator platform configured to be oriented obliquely with respect the stato...
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WO/2015/116399A1 |
A seal assembly, comprising a first segment, a second segment, and a seal incorporated between the first segment and the second segment, the seal comprising a mesh. The first segment may comprise a blade outer air seal and the second seg...
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WO/2015/115400A1 |
A rotary machine (100) comprises: a rotor (5) rotating about an axis; a seal housing (30) disposed facing the outer peripheral surface of the rotor (5); and a seal body (10) having circumferentially laminated thin plates (20) extending i...
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WO/2015/115558A1 |
Provided is a seal structure (2) for sealing a gap between a first structural body (10) and a second structural body (51) facing the first structural body (10) in a radial direction,wherein the seal structure (2) is provided with: a peri...
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WO/2015/110744A1 |
The invention concerns a turbomachine bearing housing (E) comprising a fixed wall (9), a rotating shaft (5), first and second seals (10, 20) between the wall and the shaft, and a chamber (Cam) between the fixed wall (9) and a stator elem...
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WO/2015/112239A1 |
A seal for sealing a space defined by first and second components, the seal including at least one first seal and at least one second seal wherein at least a portion of the at least one first seal is disposed in the at least one second s...
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WO/2015/112414A1 |
A platform seal assembly (438) for a gas turbine engine (100) with a turbine disk (422) and a plurality of turbine blades (460) is disclosed. The platform seal assembly (438) includes a platform seal (430) and a validation tab (401). The...
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WO/2015/110190A1 |
Mechanical fastening system (10) for rotating or stationary components (1) such as turbine or compressor blades on a rotor or a shaft or a casing, respectively comprising a circumferential mounting groove adapted for receiving root secti...
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WO/2015/112354A1 |
The present disclosure relates generally to blade outer air seal section mount including a resilient spring element that acts to provide re-centering forces to the blade outer air seal section when non-uniform forces applied to the blade...
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WO/2015/112662A1 |
A turbine engine system comprising a turbine engine air seal having at least one contact portion. The turbine engine air seal having a MAXMET composite bonded to at least one contact portion.
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WO/2015/112219A2 |
A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond stren...
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WO/2015/112238A1 |
A toggle seal, for use with a rim seal, including: a seal body, a proximal end and a distal end, a first end seal extending in a first axial direction from the proximal end of the seal body, a second end seal extending in the first axial...
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WO/2015/111688A1 |
A fluid seal structure of a heat engine including a steam turbine is provided with: an inner case for rotatably accommodating a turbine rotor within the interior thereof; an outer case for accommodating the inner case and forming a space...
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WO/2015/109292A1 |
One exemplary embodiment of this disclosure relates to a system having a static segment with a circumferentially extending slot. The system further includes a retention clip partially received in the slot, and partially contacting a circ...
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WO/2015/105623A1 |
A turbine stage (415) for a gas turbine engine (100) is disclosed. The turbine stage (415) includes a turbine disk (435) and a turbine diaphragm (460), forming a cavity (466) there between. The turbine stage (415) also includes an exit f...
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WO/2015/104695A1 |
A blade for a gas turbine (2) is provided with an elongated main body (18) and a cooling circuit (28) supplied with a cooling fluid and comprising a first channel (29) and at least one second channel (30) arranged, at least partly, insid...
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WO/2015/105574A1 |
A spring guide for use in a seal housing including a first body portion, a second body portion, and a flange portion, including a flange width, extending circumferentially between the first body portion and the second body portion. The f...
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