Did You Know...
...that in the early 1940s GE engineer James Wright was charged with a task of utmost importance to the war effort: develop a cheap substitute for rubber that could be used to produce tires, gas masks and a whole host of military gear. Wright tackled the task diligently -- and wound up inventing Silly Putty.
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| Number | Title | Issue Date |
| 8182208 | Gas turbine systems involving feather seals Systems involving feather seals are provided. A representative vane assembly for a gas turbine engine includes: a first mounting platform having a first slot; a first airfoil extending from the first mounting platform; and a feather seal having opposing faces, a fir... | 05/22/2012 |
| 8043050 | Gap seal in blades of a turbomachine A gap seal (9) radially seals a gap (8) which extends axially and radially between two blades (1, 2) of a turbomachine which are adjacent in the circumferential direction (3). The two blades (1, 2) have, in each case, an axially ex... | 10/25/2011 |
| 7922444 | Chamfer rail pockets for turbine vane shrouds A shroud rail for retaining a feather seal in a vane shroud of a gas turbine engine comprises a slot for, receiving the feather seal, and a chamfer rail pocket for lightening the shroud rail. The slot traverses the vane shroud and includes a slot base extending from... | 04/12/2011 |
| 7686577 | Stacked laminate fiber wrapped segment A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a stren... | 03/30/2010 |
| 7527472 | Thermally sprayed conformal seal A conformal seal (20) for sealing air flow between a cooling airflow path and a hot gas flow path within a combustion turbine engine. The conformal seal (20) may be fitted within cooperating side slots of adjacent vane segments (10) within the c... | 05/05/2009 |
| 7357618 | Flow splitter for steam turbines A flow splitter directs inlet steam in axially opposite directions in a double flow steam turbine. The flow splitter includes a main ring having a radially outer apex with annular concave surfaces extending inwardly from and in opposite axial directions on opposite ... | 04/15/2008 |
| 7338253 | Resilient seal on trailing edge of turbine inner shroud and method for shroud post impingement cavity sealing A sealing arrangement for the post impingement cavity of a stator shroud segment is provided that includes a resilient seal to reduce air leakage and improve turbine energy efficiency. The stator shroud segment includes an outer shroud having a leading edge groove a... | 03/04/2008 |
| 7331755 | Method for coating gas turbine engine components A method for assembling a vane sector for a gas turbine engine, the vane sector including an airfoil vane and a platform includes depositing a wear coating material onto a selected area of the platform, positioning the platform adjacent to the airfoil vane, and exec... | 02/19/2008 |
| 7293957 | Vane platform rail configuration for reduced airfoil stress A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing its resis... | 11/13/2007 |
| 7291946 | Damper for stator assembly A damper for a stator assembly, the stator assembly comprising a stator segment and a seal mounted to the stator segment. The damper locates between the stator segment and the seal, and comprises: a medial section; and opposed arms extending from the medial section.... | 11/06/2007 |
| 7284954 | Shroud block with enhanced cooling A shroud for surrounding a portion of a turbine flow path having improved cooling and durability is disclosed. The shroud includes a plurality of generally axial cooling holes spaced a substantially equal distance apart and a plurality of generally circumferential c... | 10/23/2007 |
| 7278820 | Ring seal system with reduced cooling requirements Aspects of the invention are directed to systems for reducing the cooling requirements of a ring seal in a turbine engine. In one embodiment, the ring seal can be made of a ceramic material, such as a ceramic matrix composite. The ceramic ring seal can be connected ... | 10/09/2007 |
| 7261514 | Sealing arrangement, in particular for the blade segments of gas turbines A sealing arrangement has two bodies with two end faces which extend along a longitudinal axis, adjoin one another while forming a gap, the width of which can vary between zero and a maximum width. The gap is covered by a sealing strip which lies transversely to the... | 08/28/2007 |
| 7238003 | Vane attachment arrangement A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing. ... | 07/03/2007 |
| 7229245 | Vane platform rail configuration for reduced airfoil stress A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their res... | 06/12/2007 |
| 7217081 | Cooling system for a seal for turbine vane shrouds A seal for sealing a seal groove in a shroud of a turbine vane. The seal may include a cooling system configured to pass cooling fluids through a cooling fluid supply port in a shroud, through a cooling system in which the cooling fluids contact the shroud and the s... | 05/15/2007 |
| 7201559 | Stationary ring assembly for a gas turbine A stationary ring assembly forming a rotor shroud for a gas turbine including a plurality of segments having adjacent side faces that are placed end to end with sealing means interposed therebetween. The sealing means include at least one axial sealing strip and at ... | 04/10/2007 |
| 7198454 | Variable stator vane arrangement for a compressor An axial flow compressor (16) comprises a plurality of variable stator vanes (32) circumferentially spaced apart and extending radially. Each variable stator vane (32) is rotatably mounted on a compressor casing (28). A control ring (3... | 04/03/2007 |
| 7195453 | Compressor stator floating tip shroud and related method A stator blade segment for a compressor includes an inner ring segment and an outer ring segment and a plurality of stator blades extending radially between the inner and outer ring segments, the stator blade secured to the outer ring at a shank portion of the blade... | 03/27/2007 |
| 7192246 | Seal arrangement in a machine A seal arrangement, for example a brush seal 8′ in a gas turbine engine, includes thermal matching means for matching the rates of response of a supporting ring 14′, 16′ of the seal, and of a rotatable component 4 with which the seal coope... | 03/20/2007 |
| 7189057 | Turbine shroud segment attachment A turbine shroud segment attachment with a casing (1) and several shroud segments (2) arranged in the casing (1), wherein the individual shroud segments (2) are located in the casing (1) with a circumferential clearance (3) ... | 03/13/2007 |
| 7179049 | Gas turbine gas path contour Gas flow is redirected by a feature disposed on a trailing edge of at least one segment of a peripheral gas path defining surface to improve alignment with a downstream portion of the gas path. ... | 02/20/2007 |
| 7175387 | Seal arrangement for reducing the seal gaps within a rotary flow machine A seal arrangement for reducing the seal gaps within a rotary flow machine, preferably an axial turbomachine, has rotor blades and guide vanes, which are respectively arranged in at least one rotor blade row and guide vane row and have respective blade/vane roots ( | 02/13/2007 |
| 7172388 | Multi-point seal A spring seal for sealing a gap defined between first and second gas turbine engine components. The spring seal has a grasping portion for graspingly receiving a portion of the first component, and a spring loading portion adapted to extend between the first and sec... | 02/06/2007 |
| 7168914 | Gas turbine stationary blade The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of... | 01/30/2007 |
| 7160078 | Mechanical solution for rail retention of turbine nozzles A mechanical arrangement for protection against catastrophic nozzle failures includes a turbine nozzle segment including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with the rail on one side, an inner retainer segment se... | 01/09/2007 |
| 7134287 | Turbine combustor endcover assembly The endcover assembly for a combustor includes an endcover having an aperture, an insert disposed in the stepped bore opening through an internal face of the endcover, a fuel cartridge extending through the insert and aperture and a seal cover on the external face o... | 11/14/2006 |
| 7128522 | Leakage control in a gas turbine engine A gas turbine engine expansion joint comprises first and second members having confronting faces defining a gap therebetween. At room temperature, the gap varies in accordance with the temperature distribution profile of the first and second members during normal en... | 10/31/2006 |
| 7114920 | Shroud and vane segments having edge notches Random air flow leakage between a shroud assembly and a stator vane assembly into the gas path of a gas turbine engine due to manufacturing tolerance stack-up is reduced by providing notches to inhibit interference caused by misalignment and/or mismatch of adjacent ... | 10/03/2006 |
| 7101147 | Sealing arrangement A sealing arrangement that can be employed to maintain a seal in any suitable pressure vessel including but not limited to a gas turbine engine. The sealing arrangement is forg sealing a leakage gap between at least two relatively moveable parts that are adjacent to... | 09/05/2006 |
| 7080513 | Seal element for sealing a gap and combustion turbine having a seal element The invention pertains to a seal element for sealing a gap, in particular within a turbo-machinery, between a first component and a second components spaced apart from each other, said first component having a first surface and said second component having an opposi... | 07/25/2006 |
| 7063503 | Turbine shroud cooling system A cooled turbine shroud assembly includes a first cooling path and a second cooling path adapted to provide shroud impingement air at different pressures to enhance efficiency. The cooling air is preferably acquired from a common source of secondary air. In one aspe... | 06/20/2006 |
| 7033138 | Ring segment of gas turbine An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidation is prevented, and high temperature deformation is prevented. In order to achieve the object, the pre... | 04/25/2006 |
| 7029228 | Method and apparatus for convective cooling of side-walls of turbine nozzle segments A turbine nozzle includes, in an exemplary embodiment, an outer band portion, an inner band portion at least one nozzle vane extending between the inner band portion and the outer band portion, and at least one cooling channel extending axially at least partially th... | 04/18/2006 |
| 7025563 | Stator vane assembly for a gas turbine engine A low-pressure compressor exit stator assembly for a gas turbine includes a multiple of vanes mounted between a full hoop outer shroud and an inner shroud. The outer shroud and inner shroud are mounted to the intermediate case structure. A seal is located between th... | 04/11/2006 |
| 6997673 | Gas turbine high temperature turbine blade outer air seal assembly A turbine shroud assembly includes forward and aft hangers, an axisymmetric plenum assembly, ceramic shroud segments, ceramic spacers, and forward and aft rope seals. The plenum assembly supplies impingement cooling to the shroud and the hangers. The impingement coo... | 02/14/2006 |
| 6971844 | Horizontal joint sealing system for steam turbine diaphragm assemblies Spline seals are provided in registering end faces of upper and lower diaphragm segments in a steam turbine at each of the horizontal joints. The diaphragm segments each include inner and outer semi-annular rings with circumferentially spaced partitions extending th... | 12/06/2005 |
| 6969239 | Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine A stator vane assembly for a compressor of a gas turbine engine, including a stator vane having an inner portion and an outer portion, a platform attached to the outer portion of the stator vane, a casing for the gas turbine engine, wherein the outer platform of the... | 11/29/2005 |
| 6918743 | Sheet metal turbine or compressor static shroud A static shroud for ducting an axial gas flow past an array of blades rotating about an axis, made of a sheet of metal bent to form a contiguous shroud body having a substantially uniform sheet thickness and a uniform axial profile, initiating with an upstream flang... | 07/19/2005 |
| 6910854 | Leak resistant vane cluster A vane cluster for a turbine engine compressor or turbine includes a shroud 12 with a nonlinear slot 26 extending therethrough to divide the shroud into thermally independent shroud segments 24. The slot is bordered by matching nonlinear surface... | 06/28/2005 |
