Did You Know...
...that two musicians were responsible for the invention of color print film? Fascinated by photography, Leopold Godowsky and Leopold Mannes worked together to produce an easy-to-use, practical color film. They worked full time as music teachers and gave concerts while experimenting during their off hours in Mannes' kitchen. Their success earned them full-time, well-paying jobs at Kodak and their efforts resulted in Kodachrome film, which was introduced in 1935.
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| Number | Title | Issue Date |
| 8186946 | Abrasive thermal coating A protective coating for a surface exposed to hot gas flow comprises a thermal layer, a conducting layer and an abrasive layer. The thermal layer comprises stabilized zirconia, and overlies the surface. The conducting layer overlies the thermal layer. The abrasive l... | 05/29/2012 |
| 8177493 | Airtight external shroud for a turbomachine turbine wheel External shroud for a turbomachine turbine wheel, this shroud being formed of ring sectors (120) positioned circumferentially end to end, and each comprising a circumferentially directed plate (136) bearing a block (138) of abradable material, t... | 05/15/2012 |
| 8177494 | Buried casing treatment strip for a gas turbine engine A multiple of circumferential grooves within said arcuate engine casing and an abradable material located radial inboard of the multiple of circumferential grooves. ... | 05/15/2012 |
| 8172518 | Methods and apparatus for fabricating a rotor assembly A method for assembling a rotor assembly and a rotor assembly are provided. The method comprises providing a rotor blade including a first sidewall, a second sidewall, where the first and second sidewalls are connected at a leading edge and a trailing edge and exten... | 05/08/2012 |
| 8128352 | Thermomechanical part constituting a body of revolution about a longitudinal axis and including at least one abradable ring for a sealing labyrinth The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that pres... | 03/06/2012 |
| 8100640 | Blade outer air seal with improved thermomechanical fatigue life A blade outer air seal for a gas turbine has an abradable coating with a substantially uniform thickness during service use. Prior to being placed in service, the abradable coating has a central portion with a greater thickness than leading and trailing portions. Wh... | 01/24/2012 |
| 7955049 | Seal between relatively moveable members A seal (48) between first and second relatively rotatable members (26,28). The seal comprises an abradable material on at least one of the relatively rotatable members (26,28). The abradable material comprises an open cell metallic foam (60 | 06/07/2011 |
| 7871244 | Ring seal for a turbine engine A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed... | 01/18/2011 |
| 7775766 | Gas turbine component A static gas turbine component, especially for an aircraft engine, is formed at least partially region-wise of metal foam. An abradable shroud lining of metal foam and a carrier allow a radial through-flow of gas. ... | 08/17/2010 |
| 7726936 | Turbine engine ring seal Aspects of the invention relate to a ring seal for a turbine engine. The ring seal can be made up of a plurality of circumferentially abutted ring seal segments. Each ring seal segment can comprise a plurality of individual channels. The channels can be generally U-... | 06/01/2010 |
| 7625177 | Simple axial retention feature for abradable members An abradable member, such as gas turbine engine seal for rotary components, is restrained against axial movement relative to an adjacent component via a lip retention engagement. ... | 12/01/2009 |
| 7614847 | Pattern for the surface of a turbine shroud A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first p... | 11/10/2009 |
| 7600968 | Pattern for the surface of a turbine shroud An article of manufacture pattern for improving aerodynamic performance of a turbine including an abradable material capable of abradable contact. The abradable material is disposed in a pattern. The pattern includes a first plurality of ridges disposed at a base su... | 10/13/2009 |
| 7510370 | Turbine blade tip and shroud clearance control coating system A turbine blade tip and shroud clearance control coating system comprising an abrasive blade tip coating and an abradable shroud coating are provided. The abrasive layer may comprise abrasive particles of cubic zirconia, cubic hafnia or mixtures thereof, and the abr... | 03/31/2009 |
| 7500824 | Angel wing abradable seal and sealing method An abradable seal is provided to improve turbine performance by physically reducing the clearance between a flange portion of the nozzle and an opposed angel wing/seal plate member of the bucket. The provision of an abradable seal also mitigates angel wing/seal plat... | 03/10/2009 |
| 7473072 | Turbine blade tip and shroud clearance control coating system A turbine blade tip and shroud clearance control coating system comprising a dense abrasive blade tip layer and an abradable shroud layer are provided. The dense abrasive coating may comprise cubic zirconia, hafnia or mixtures thereof and the abradable layer may be ... | 01/06/2009 |
| 7425115 | Thermal turbomachine A thermal turbomachine is disclosed having at least one row of rotor blades. At least one first rotor blade has a greater radial length than the others and at the blade tip is equipped with a first abrasive layer. At least one rotor blade which has a shorter radial ... | 09/16/2008 |
| 7387488 | Cooled turbine shroud A cooled turbine shroud includes an arcuate flow path surface adapted to surround a row of rotating turbine blades, and an opposed interior surface; a forward overhang defining an axially-facing leading edge, an outwardly-extending forward wall and an outwardly-exte... | 06/17/2008 |
| 7371043 | CMC turbine shroud ring segment and fabrication method Fabricating a refractory component for a gas turbine engine, such as a turbine shroud ring segment, by arranging refractory fiber tows (24) in a flaired tubular geometry (20) comprising a stem portion (21) and a funnel-shaped portion (22)... | 05/13/2008 |
| 7341426 | Gas turbine engine blade tip clearance apparatus and method A gas turbine engine is provided that includes one or more rotor assemblies, one or more shroud segments, and an actuator. The rotor assemblies are rotatable around an axially extending rotational axis, and each rotor assembly has a plurality of blades. Each blade h... | 03/11/2008 |
| 7334984 | Turbine shroud assembly with enhanced blade containment capabilities A low pressure turbine shroud assembly includes a backsheet with enhanced blade containment capabilities that is sized to be retrofitted into a conventional low pressure turbine assembly. The backsheet has first and second mounting rails at axially opposite ends the... | 02/26/2008 |
| 7311940 | Layered paint coating for turbine blade environmental protection The present invention is a gas turbine engine turbine blade comprising an airfoil section having at least an exterior surface, a platform section having an exterior surface, an under platform section having an exterior surface, and a dovetail section having an exter... | 12/25/2007 |
| 7290982 | Arrangement for the attachment of distributor sectors supporting vanes around an arc of a circle The distributor sectors (25) of a turbomachine are secured adjacent to a casing (31) with sealing sectors (32) alternating with them in the axial direction. The distributor sectors (25) are provided with force resistant faces (37; 39 | 11/06/2007 |
| 7291403 | Thermal barrier coating system A TBC system suitable for protecting the surface of a substrate subjected to a hostile thermal environment. The TBC system comprises a bond coat on the substrate surface, an alumina scale on the bond coat, and a multilayer TBC comprising a thermal-sprayed first cera... | 11/06/2007 |
| 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 |
| 7287956 | Removable abradable seal carriers for sealing between rotary and stationary turbine components The turbine includes a diaphragm having a seal carrier mounted in opposition to seal teeth carried by the rotary component. The seal carrier includes a seal face having a coating of abradable material enabling the rotary component to abrade the material from the sea... | 10/30/2007 |
| 7282271 | Durable thermal barrier coatings A durable protective coating may be formed by applying a thin layer of metastable alumina to a bond coating on a substrate. A thermal barrier coating may then be applied to the metastable alumina and the resulting part may be heat treated to transform the metastable... | 10/16/2007 |
| 7278208 | Method of replacing an abradable portion on the casing on a turbojet fan A simple and low cost method of replacing an abradable portion on the fan casing of a turbojet includes an inside heating belt together with holding sectors therefor are put into place against the abradable portion, each holding sector including an inflatable bladde... | 10/09/2007 |
| 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 |
| 7273353 | Shroud honeycomb cutter A turbine blade for use in a gas turbine engine is provided. The turbine blade includes an airfoil portion having a tip end, a shroud attached to the tip end, which shroud has an outer surface, and a knife edge attached to an outer surface of the shroud. The knife e... | 09/25/2007 |
| 7255929 | Use of spray coatings to achieve non-uniform seal clearances in turbomachinery The invention provides spray coatings to achieve circumferentially non-uniform seal clearances in turbomachines. In steam and gas turbines it is desirable to assemble the machines with elliptical seal clearances to compensate for expected casing distortion, rotordyn... | 08/14/2007 |
| 7247002 | Lamellate CMC structure with interlock to metallic support structure A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperat... | 07/24/2007 |
| 7246990 | Composite fan containment case for turbine engines A composite fan casing for a gas turbine engine is provided includes, in an exemplary embodiment, a core having a plurality of core layers of reinforcing fiber bonded together with a thermosetting polymeric resin. Each core layer includes a plurality of braided rein... | 07/24/2007 |
| 7241108 | Cantilevered stator stage A cantilevered stator stage for the axial compressor 14 of a gas turbine engine 10 in which the stator tips 26 rub against an abrasive section 24 on the rotor drum 22 during initial running of the engine 10 to abrade the tip... | 07/10/2007 |
| 7228192 | Method for manufacturing an item According to a first aspect of the present invention, a method is provided for manufacturing an item. The method comprises the steps of creating a build schedule; creating a first portion of the item for manufacture; causing the first portion of the item to pass in ... | 06/05/2007 |
| 7223067 | Flow machine with a ceramic abradable The flow machine is furnished with an abradable (10) made of a particle composite material. This so-called composite (1) contains granular core particles (2) of a ceramic material. The surfaces (20) of the granular core particles carry fu... | 05/29/2007 |
| 7210901 | Assembly of sectors of a dispensing unit in a gas turbine The retaining hooks (32) of a flange (22) of straightening sectors (20), bearing fixed blades in a turbomachine, are advantageously placed on an end plate (30) distinct from the casing (21) but assembled on the latter. In this way,... | 05/01/2007 |
| 7210905 | Compressor having casing treatment slots A compressor (16) comprises a rotor (40) having a plurality of circumferentially spaced radially outwardly extending rotor blades (42). A casing (44) surrounds the rotor (40) and rotor blades (42). The casing (44) has... | 05/01/2007 |
| 7163370 | Gas turbine engine and method of producing the same A raw material powder having particle sizes of not more than 125 μm and preferably not more than 75 μm, such as a powder of an alloy of Co-32% Ni-21% Cr-7.5% Al-0.5% Y is thermally sprayed onto surfaces of shroud members of a shroud to form a coating. The high vel... | 01/16/2007 |
| 7160635 | Protective Ti-Al-Cr-based nitrided coatings This invention relates to coatings for the protection of substrates operating at moderately elevated temperatures, and, more particularly, for the protection of titanium-alloy aircraft and stationary gas turbine components as well as engine components for automotive... | 01/09/2007 |
