Did You Know...
...that the x-ray was discovered purely by accident? When German physicist Wilhelm Konrad von Roentgen was experimenting with cathode rays in 1895, he put an activated Crookes tube in a book and went out to lunch. When he returned, he discovered that a key that had also been placed in the book showed up as an image on the developed film!
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| Number | Title | Issue Date |
| 8182210 | Heat shield segment for a stator of a gas turbine A gas turbine includes a turbine housing; a rotatable turbine rotor with turbine blades; and at least one heat shield segment for a stator. The heat shield segment is disposed radially between the rotor and the housing and attached to the housing and has a profile w... | 05/22/2012 |
| 8177492 | Passage obstruction for improved inlet coolant filling A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or mor... | 05/15/2012 |
| 8167546 | Ceramic turbine shroud support A turbine shroud includes a ceramic shroud ring configured to surround a plurality of turbine rotor blades, a plurality of slots circumferentially distributed around the ceramic shroud ring, a forward metallic support ring, a plurality of tabs attached to a forward ... | 05/01/2012 |
| 8157511 | Turbine shroud gas path duct interface An arrangement for sealing a turbine shroud gas path duct interface of a turbine engine comprises a static shroud surrounding a rotatable airfoil array and an annular duct downstream of the shroud with respect to a gas flow passing through the gas path. The shroud a... | 04/17/2012 |
| 8152456 | Turbojet compressor The invention relates to a turbojet compressor comprising a shroud and a plurality of blades, each fixed via its root to the shroud. Level with each blade root, the shroud presents a suction-side ramp and a pressure-side ramp extending from the trailing edge of the ... | 04/10/2012 |
| 8152455 | Suspension arrangement for the casing shroud segments A suspension arrangement for the casing shroud segments of the high-pressure turbine of a jet engine with inclination or graduation of the rotor blade tips (4) includes spaced apart attaching hooks (11) formed onto the casing shroud segments (2)... | 04/10/2012 |
| 8133013 | Stage of a turbine or compressor, particularly for a turbomachine A stage of a turbine or compressor for a turbomachine including at least a vane disk surrounded with a sectorized ring supported by a casing and including a circumferential flange radially clamped on a rail of the casing by substantially C-shaped cross-section locks... | 03/13/2012 |
| 8128351 | Seals in steam turbine A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portio... | 03/06/2012 |
| 8128350 | Stacked lamellae ceramic gas turbine ring segment component A gas turbine ring segment (10) for use in gas turbine engines made from a ceramic matrix composite (CMC) material is disclosed. The ring segment includes a stacked multiplicity of CMC thin-sheet lamellae (25a, 25b) each comprising... | 03/06/2012 |
| 8128348 | Segmented cooling air cavity for turbine component A component for a gas turbine engine has an airfoil with internal cooling channels for delivering air from a radially outer end of the airfoil toward a radially inner end of the airfoil. The cooling channels are separated from adjacent cooling channels by sets of at... | 03/06/2012 |
| 8128349 | Gas turbine engines and related systems involving blade outer air seals Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments defining an inner diameter surfa... | 03/06/2012 |
| 8123473 | Shroud hanger with diffused cooling passage A shroud hanger for a gas turbine engine has an arcuate body with opposed inner and outer faces and opposed forward and aft ends, the channel having at least one cooling passage therein which includes: (a) a generally axially-aligned channel extending through the bo... | 02/28/2012 |
| 8118547 | Turbine inter-stage gap cooling arrangement A turbine inter-stage gap cooling and sealing arrangement for a turbine in which the blade outer air seal that forms a seal with a stage of rotor blades includes a row of cooling air holes on the back side of the blade outer air seal to discharge cooling air toward ... | 02/21/2012 |
| 8118546 | Grid ceramic matrix composite structure for gas turbine shroud ring segment A ceramic matrix composite (CMC) component such as a ring seal segment (50, 50A, 50B, 50C, 50D) for a gas turbine engine (10), the component formed with a base plate (52) and a frame portion (54) that extends substant... | 02/21/2012 |
| 8096755 | Crowned rails for supporting arcuate components A flange for supporting arcuate shrouds and shroud hangers comprising at least one arcuate rail, each arcuate rail having an inner radius, a first taper location, a first taper region, a second taper location, a second taper region, wherein the thickness of at least... | 01/17/2012 |
| 8092160 | Turbine shroud thermal distortion control A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth. ... | 01/10/2012 |
| 8092159 | Feeding film cooling holes from seal slots A cooling arrangement for a first stage nozzle of a turbine includes a slot formed in a forward face of the first stage nozzle, the slot opening in a direction facing a combustor transition piece and adapted to receive a flange portion of a seal extending between th... | 01/10/2012 |
| 8079807 | Mounting apparatus for low-ductility turbine shroud A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material ... | 12/20/2011 |
| 8075255 | Reducing inter-seal gap in gas turbine A device for reducing inter-seal gap in gas turbines. Embodiments of a gas turbine with a first arcuate component adjacent to a second arcuate component; a first slot and a connected second slot on an end of the first arcuate component; a first seal disposed into th... | 12/13/2011 |
| 8061978 | Systems and methods involving abradable air seals Systems and methods involving air seals are provided. In this regard, a representative air seal for a gas turbine engine comprises a layer of ceramic exhibiting patterned surface features, wherein a substrate supporting the layer of ceramic lacks the patterned surfa... | 11/22/2011 |
| 8061979 | Turbine BOAS with edge cooling A cooling hole having an inlet passage forming an inward spiral flow path and an outlet passage forming an outward spiral flow path in which the two paths are counter flowing in order to improve the heat transfer coefficient. The spiral cooling hole is used in a bla... | 11/22/2011 |
| 8061977 | Ceramic matrix composite attachment apparatus and method An attachment method and flange for connecting a ceramic matrix composite (CMC) component, such as a gas turbine shroud ring (36, 68), to a metal support structure. A CMC flange (20A) may be formed by attaching a wedge-shaped block (26) of a cer... | 11/22/2011 |
| 7988410 | Blade tip shroud with circular grooves A blade tip shroud segment for a gas turbine engine in which the shroud segment is cooled and sealed using a combination of vortex cooling air flow and cooling air discharge film cooling. The shroud segment includes a row of vortex chambers formed within the shroud ... | 08/02/2011 |
| 7972109 | Methods and apparatus for fabricating a fan assembly for use with turbine engines A method for fabricating a fan assembly is provided, wherein the method includes providing a rotor having a plurality of rotor blades. At least one rotor blade is fabricated from a frangible material. The method also includes coupling a casing substantially circumfe... | 07/05/2011 |
| 7967557 | Multiblade centrifugal blower A multiblade centrifugal blower includes a centrifugal fan including a hub rotated by a motor, and plural curved rectangular blades arranged at predetermined intervals in a circumferential direction of the hub forming a cylindrical basket with an opening on a front ... | 06/28/2011 |
| 7946807 | Set of insulating sheets on a casing to improve blade tip clearance A turbine stator of a gas turbine engine includes a turbine casing, a turbine shroud ring and a shroud ring support connecting the shroud ring to the casing. The stator is one wherein the support is provided with a heat shield positioned on the turbine side. This as... | 05/24/2011 |
| 7938621 | Blade tip clearance system A pressure actuated tip clearance system for a shroud structure of a gas turbine engine rotary stage includes an annular plenum chamber formed between an annular arrangement of a plurality of shroud liners on the inner circumference of the chamber and a generally cy... | 05/10/2011 |
| 7874792 | Blade outer air seals, cores, and manufacture methods A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a proximal end joining the first end portion; a main body portion; and a free distal portion. Second legs each have: a proximal... | 01/25/2011 |
| 7874793 | Blade clearance arrangement Control of blade clearance gaps between rotating turbine blades and an associated casing in a gas turbine engine is important in order to maintain operational efficiency. It is desirable to achieve accurate gap control but previous passive and scheduled thermal gap ... | 01/25/2011 |
| 7866943 | Device for attaching ring sectors to a turbine casing of a turbomachine Device for attaching ring sectors (20) to a turbine casing (16) in a turbomachine, comprising, at the upstream ends of the ring sectors (20), circumferential coupling means (70, 72) engaged on a casing rail (50) and clamped axially... | 01/11/2011 |
| 7811054 | Shroud configuration having sloped seal A stator shroud segment is provided that includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook, the leading and trailing hooks of each of the inner ... | 10/12/2010 |
| 7811053 | Fan rotor design for coincidence avoidance A fan rotor capable of avoiding coincidence will include a fan hub comprising one or more slots each designed to receive a fan blade; and one or more fan blades disposed within the slots. One or more slots will comprise an RZ′ baseline and have one or m... | 10/12/2010 |
| 7789619 | Device for attaching ring sectors around a turbine rotor of a turbomachine A device for attaching ring sectors around a turbine rotor in a turbomachine is disclosed. Each of the ring sectors includes at its upstream end a circumferential rim being able to be held on an annular casing rail by an annular locking member, and at its downstream... | 09/07/2010 |
| 7785067 | Method and system to facilitate cooling turbine engines A method of assembling a gas turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the gas turbine engine. The at least one turbine nozzle segment includes at least one airfoil vane extending between an inner band and an... | 08/31/2010 |
| 7740444 | Methods and system for cooling integral turbine shround assemblies A method for cooling a turbine shroud assembly includes providing a turbine shroud assembly including a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween. A shroud support circumferentially spans and supports the shroud segm... | 06/22/2010 |
| 7717671 | Passive air seal clearance control A seal for restricting leakage of a fluid through a gap disposed between rotating and stationary components concentrically aligned within a gas turbine engine comprises a sealing member and a land. The sealing member is positioned on either the rotating or stationar... | 05/18/2010 |
| 7699581 | Run-in coating for gas turbines and method for producing same A run-in coating is for gas turbines. The run-in coating is used for sealing a radial gap between a housing of the gas turbine and rotating rotor blades of same, the run-in coating being applied onto the housing. The run-in coating is made of an intermetallic titani... | 04/20/2010 |
| 7686578 | Conformal tip baffle airfoil A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested trans... | 03/30/2010 |
| 7670108 | Air seal unit adapted to be positioned adjacent blade structure in a gas turbine An air seal unit to be positioned adjacent blade structure in a gas turbine is provided. The air seal unit comprises a main body including a plurality of first impingement cavities and at least one first interconnecting passage extending between and communicating wi... | 03/02/2010 |
| 7665960 | Turbine shroud thermal distortion control A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth. ... | 02/23/2010 |
