Quotables
"The man with a new idea is a crank until the idea succeeds."
Samuel Clemens
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 8157509 | Method, system and apparatus for turbine diffuser sealing A turbine diffuser is disclosed. The turbine diffuser includes a diffuser segment having a forward end and an aft end with a flange disposed at the aft end of the diffuser segment. The diffuser segment is joinable to an adjacent diffuser segment via the flange, whic... | 04/17/2012 |
| 7771160 | Ceramic shroud assembly A ceramic shroud assembly suitable for use in a gas turbine engine comprises a metal clamp ring shrink fitted around a ceramic shroud ring and an insulating and compliant interlayer. The interlayer is positioned between the metal clamp ring and the ceramic shroud ri... | 08/10/2010 |
| 7766609 | Turbine vane endwall with float wall heat shield A float wall heat shield for use on an endwall of a stator vane used in a gas turbine engine. The heat shield includes an attachment extending from a center of the heat shield to secure the shield to the vane. A plurality of ribs formed on the inside surface of the ... | 08/03/2010 |
| 7722317 | CMC to metal attachment mechanism A CMC wall (20F) may be attached to a metal wall (22F) by a plurality of bolts (28A, 28B, 28C) passing through respective holes (24A, 24B, 24C) in the CMC wall (20F) and holes in the metal wall (22 | 05/25/2010 |
| 7597536 | Turbine airfoil with de-coupled platform An airfoil used in a gas turbine engine, such as a turbine blade, includes a thin slot formed between a platform section and an airfoil section of the blade, with a metering hole providing for a cooling air passage between a dead rim cavity and the thin slot, such t... | 10/06/2009 |
| 7588414 | Arrangement for internal passive turbine blade tip clearance control in a high pressure turbine A passive internal control system for rotor blade tip clearance of a high-pressure turbine is based on inner rings that expand in a radial direction under the influence of heat and radially adjust the clearance delimited by liner segments (9) on the casing si... | 09/15/2009 |
| 7422413 | Shroud tip clearance control ring The present invention is a shroud tip clearance control ring for use in a gas turbine engine in which a rotary blade and a shroud ring form a gap that forms a blade outer air seal, and where the shroud ring is formed of two shroud segment halves, each shroud segment... | 09/09/2008 |
| 7360989 | Device for axially holding a ring spacer sector of a high-pressure turbine of a turbomachine A device for axially holding a ring spacer sector of a high-pressure turbine of a turbomachine, said spacer sector comprising an upstream radial wall provided with an outer upstream tongue for being engaged in a corresponding upstream groove of a casing of the turbi... | 04/22/2008 |
| 7329088 | Pilot relief to reduce strut effects at pilot interface A turbine section of an engine that includes a shaft, a plurality of blades extending radially relative to the shaft, a bearing assembly, a flowpath housing, and a shroud is provided. The bearing assembly is mounted to the shaft adjacent to the plurality of blades. ... | 02/12/2008 |
| 7326030 | Support system for a composite airfoil in a turbine engine A turbine airfoil support system for coupling together a turbine airfoil formed from two or more components, wherein the support system is particularly suited for use with a composite airfoil. In at least one embodiment, the turbine airfoil support system may be con... | 02/05/2008 |
| 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 |
| 7290769 | Sealing device with a brush gasket and flexible washer for a high-pressure turbine of a turbomachine A sealing device for sealing between two static portions of a turbomachine includes a brush gasket formed by a plurality of resilient bristles which are, at least in part, held in a housing. Each bristle has a main portion and a secondary portion interconnected by a... | 11/06/2007 |
| 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 |
| 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 |
| 7186074 | Axial flow stream turbines A drum-type rotor carries an annular row of moving blades having root portions held within a slot in the periphery of the rotor. A turbine casing surrounds the rotor and carries a static blade assembly with an annular row of static blades which, together with the an... | 03/06/2007 |
| 7181914 | Diffuser for gas turbine engine A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member ... | 02/27/2007 |
| 7178340 | Transition duct honeycomb seal A sealing device for use between a gas turbine combustor transition duct aft frame and a turbine inlet having improved durability, reduced wear on the mating turbine vane, and reduced manufacturing costs, is disclosed. The sealing device has a circumferential length... | 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 |
| 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 |
| 7152864 | Seal assembly It is disclosed a seal assembly (5) which comprises a layered structure. It consists of a first layer (9, 12) of a base material, a second layer (10) of thermal insulating material on top of the base material and a third layer (11, 12) of... | 12/26/2006 |
| 7128323 | Seal device Primary objective of the present invention is to provide a seal device wherein the seal surfaces of the device are always brought into close contact against the side walls of the mounting slot regardless of fluid conditions. The seal device has two seal portions loc... | 10/31/2006 |
| 7114917 | Vane assembly for a gas turbine engine An exhaust diffuser unit for a gas turbine engine includes an outer ring, a diffuser cone and vanes, all made from a ceramic matrix composite material. Each vane has end components which have apertures through which a metallic support strut extends. The support stru... | 10/03/2006 |
| 7108479 | Methods and apparatus for supplying cooling fluid to turbine nozzles A method enables a gas turbine engine to be operated. The method comprises supplying cooling fluid into a manifold ring that includes a plurality of distribution ports defined by a sidewall connected by a radially inner wall, channeling the cooling fluid circumferen... | 09/19/2006 |
| 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 |
| 7094025 | Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction Nozzle segments are secured to a retention ring against circumferential rotation by anti-rotation pins extending generally axially between the outer bands of the nozzle segments and the retention ring. Retention plate segments overlie the ends of the pins, preventin... | 08/22/2006 |
| 7090224 | Seal device Primary objective of the present invention is to effect a seal against assembly clearances formed between components which admit flows of high temperature fluids or are subjected to vibrations. The seal device is comprised of a supporting member which has a first se... | 08/15/2006 |
| 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 |
| 7032904 | Inner air seal anti-rotation device An anti-rotation device for preventing rotation of a damper spring and an inner air seal in a stator assembly is provided. The anti-rotation device is formed by a lug positioned within a slot at a center of an inner air seal arc segment. The lug engages a slot in th... | 04/25/2006 |
| 7029391 | Blower unit and air conditioning unit including the same and method of controlling the same A blower unit of an air conditioning unit including a scroll casing including a first engaging portion, a fan casing including a first engaging portion, and a controller for controlling an electric motor to move at least one of the scroll casing and the fan casing s... | 04/18/2006 |
| 6945046 | Turbine casing for an exhaust turbocharger made by casting The invention concerns a casing aggregate for the turbine of an exhaust turbocharger. The invention is identified by the following characteristics: a spiral casing adapted for surround the running wheel of the turbine; ... | 09/20/2005 |
| 6942453 | Turbine nozzle segment A turbine nozzle segment 1 of a turbine nozzle assembly comprises a plurality of stator vanes 7, an arc-like inner band 9 integrally molded at the inner end of a plurality of the stator vanes 7, an arc-like outer band 11 integrally... | 09/13/2005 |
| 6939106 | Sealing of steam turbine nozzle hook leakages using a braided rope seal A steam turbine includes a stator supporting a plurality of turbine nozzles. The stator has shaped grooves for receiving a complementary-shaped nozzle hook formed on an end of each of the turbine nozzles. A rope seal is disposed in each interface between the nozzle ... | 09/06/2005 |
| 6932566 | Gas turbine shroud structure There is disclosed a gas turbine shroud structure comprising: a shroud support component 12 attached to an inner surface of a gas turbine casing 3; a shroud segment 14 divided in a peripheral direction and supported by the inner surface of the s... | 08/23/2005 |
| 6918594 | Face seal assembly with composite stator A composite face seal has an annular seal rotor and an annular seal stator, both having a metal base portion and a radially extending flange. The flange has first and second axially facing surfaces. A first ceramic ring may be mounted to the first surface of the fla... | 07/19/2005 |
| 6896483 | Blade track assembly The clearances between an array of turbine blades and its surrounding blade track may be controlled by an expansion control material system supporting the blade tracks. The blade track support hoop is placed in tension by the expansion control material placed therei... | 05/24/2005 |
| 6893214 | Shroud segment and assembly with surface recessed seal bridging adjacent members A turbine engine shroud segment is provided with a radially outer surface including a pair of spaced apart, opposed first and second edge portion surface depressions, for example spaced circumferentially, having a seal surface shaped to receive, in a surface depress... | 05/17/2005 |
| 6857848 | Gap seal in a gas turbine A gap seal in a gas turbine for sealing off a cooling space, formed between a heat shield and a heat shield carrier, from a hot gas space of the gas turbine. A sealing body is retained in a movable manner on the heat shield, on the one hand, and on a blade carrier, ... | 02/22/2005 |
| 6808363 | Shroud segment and assembly with circumferential seal at a planar segment surface A turbine engine shroud segment having a body including a circumferentially arcuate radially inner surface defining a circumferential arc and a radially outer surface is provided, at least at one axially spaced apart outer surface edge portion surface, with a surfac... | 10/26/2004 |
| 6752591 | Suspension A suspension of an annular secondary structure on a primary structure, in the form of a spoke-type centering device, has at least three sliding guides distributed uniformly over the structure circumference. Each sliding guide allows at least a linear relative moveme... | 06/22/2004 |
| 6733234 | Biased wear resistant turbine seal assembly A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim ... | 05/11/2004 |
