Did You Know...
...that the Band-Aid Bandage was invented by a Johnson & Johnson employee whose wife had cut herself? Earl Dickson's wife was rather accident prone, so he set out to develop a bandage that she could apply without help. He placed a small piece of gauze in the center of a small piece of surgical tape, and what we know today as the Band Aid bandage was born!
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| Number | Title | Issue Date |
| 8443610 | Low emission gas turbine combustor An annular combustor for a gas turbine has a combustion chamber having an interior volume that, in longitudinal section, includes a forward volume, an intermediate volume and an aft volume. The forward volume represents from about 30% to about 40% of the combustor i... | 05/21/2013 |
| 8438856 | Effusion cooled one-piece can combustor A combustor for an industrial turbine includes a single transition piece transitioning directly from a combustor head-end to a turbine inlet. The transition piece includes an inner surface and an outer surface. The inner surface bounds an interior space for combuste... | 05/14/2013 |
| 8429916 | Dual walled combustors with improved liner seals A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines... | 04/30/2013 |
| 8397511 | System and method for cooling a wall of a gas turbine combustor A system, in one embodiment, includes an engine wall. The engine wall includes a cold-side and a hot-side. The engine wall includes one or more dilution holes, wherein each of the one or more dilution holes includes a first opening on the cold-side, a second opening... | 03/19/2013 |
| 8387395 | Annular combustion chamber for a turbomachine An annular combustion chamber for a turbomachine is disclosed. The chamber includes an inner wall, an outer wall, and a chamber end wall disposed between the inner and outer walls in the upstream region of the chamber. The chamber end wall presents an outer fastener... | 03/05/2013 |
| 8381527 | Combustor having an acoustically enhanced ejector system The present specification generally relates to improvements to combustors such as burners and engines. In one aspect, the specification presents an acoustically enhanced ejector system which can be used as part of an intake system for a combustor. In another aspect,... | 02/26/2013 |
| 8381526 | Systems and methods of providing high pressure air to a head end of a combustor A combustor includes a first flow path and a second flow path. The first flow path places a diffuser in indirect fluid communication with a combustor cap assembly by way of an intervening lower combustor annular passageway. The second flow path places the diffuser i... | 02/26/2013 |
| 8375722 | Flow modulation method and apparatus An apparatus and method for inducing waves within a container arranged to permit a through-flow of fluid flowing generally from an inlet of the container to an exit of the container, wherein the container has wave inducing means located at the exit of the container,... | 02/19/2013 |
| 8359866 | Combustor liner segment seal member A combustor liner segment seal member is provided that includes a center section, a forward flange, and an aft flange. The center section includes a base surface, a gas path surface, a forward side surface, and an aft side surface. The forward flange extends outward... | 01/29/2013 |
| 8359865 | Combustor liner segment seal member A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and exterior surface, and a plurality of impingement apertures disposed withi... | 01/29/2013 |
| 8359867 | Combustor having a flow sleeve A combustor is provided and includes a liner through which fluid fed from at least two injection points flows from a head end to an interior of a transition piece, a first one of the at least two injection points being axially proximate to a fluid impenetrable coupl... | 01/29/2013 |
| 8347632 | Open-cooled component for a gas turbine, combustion chamber, and gas turbine An open-cooled component for a gas turbine is provided. The component includes an outer wall that is subjected to a hot gas and at least partially defines a first cavity for a first means. The outer wall is provided with through-openings which open up into the cavit... | 01/08/2013 |
| 8307654 | Transition duct with spiral finned cooling passage A transition duct for a gas turbine engine of the kind with can combustors, the transition duct is formed from an inner section and an outer section that form a spiral shaped cooling channel from an inlet end to an outlet end. The spiral channel includes a number of... | 11/13/2012 |
| 8276389 | Assembly for directing combustion gas An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) section... | 10/02/2012 |
| 8272220 | Impingement cooling plate for a hot gas duct of a thermal machine A thermal machine including a wall defining a hot gas duct for transferring a hot gas stream and a cooling jacket disposed at a distance from the wall on an outside of the hot gas duct so as to define a cooling duct with an inlet and an outlet. The cooling duct is c... | 09/25/2012 |
| 8245514 | Combustion liner for a gas turbine engine including heat transfer columns to increase cooling of a hula seal at the transition duct region A combustion duct assembly has a transition duct and a combustion liner having a hula seal at a downstream end that is forced within an inner wall of the transition duct. The combustion liner is held within the transition duct by the hula seal, but allowed to move r... | 08/21/2012 |
| 8245513 | Combustion chamber The invention relates to a combustion chamber of a gas turbine, inside of which a supplied fuel is reacted with supplied combustion air in order to produce a working medium. The inside of the combustion chamber wall is provided with a lining formed from a number of ... | 08/21/2012 |
| 8245515 | Transition duct aft end frame cooling and related method A transition duct for a gas turbine includes a tubular body having a forward end and an aft end, the aft end surrounded by a frame component; an interior closure band within the aft end, covering interior top, bottom and side wall surfaces of the frame; and a plural... | 08/21/2012 |
| 8230688 | Modular transvane assembly An arrangement for delivering gasses from can combustors of a can annular gas turbine combustion engine to a turbine first stage section including a first row of turbine blades, the arrangement including a flow-directing structure for each combustor, wherein each fl... | 07/31/2012 |
| 8220273 | Cooling structure for gas turbine combustor A gas turbine combustor having an improved cooling structure effective to efficiently suppress a possible occurrence of buckling in the combustion liner while exhibiting a convection cooling effect to the combustion liner, the gas turbine combustor includes a combus... | 07/17/2012 |
| 8215115 | Combustor interface sealing arrangement A gas turbine engine sealing arrangement which includes a combustor liner establishing a combustion area and a turbine nozzle configured to receive a portion of a combustor liner. A sealing ring arrangement is configured to seal with the turbine nozzle to control fl... | 07/10/2012 |
| 8205453 | Method for assembling end to end two parts having different thermal expansion coefficients and assembly thus obtained In order to assemble together two parts (154, 162) of materials having different coefficients of expansion via mutually engaged edge portions (154a, 162a), tongues (170) are formed in the thinned edge of one of the parts, th... | 06/26/2012 |
| 8201412 | Apparatus and method for cooling a combustor A combustor includes a combustion chamber and an interior wall circumferentially surrounding at least a portion of the combustion chamber and defining an exterior surface. A plurality of turbulators are on the exterior surface. The combustor further includes means f... | 06/19/2012 |
| 8196412 | Gas turbine transition duct profile A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with... | 06/12/2012 |
| 8191373 | Interlocking retention strip An impingement shield assembly for a turbine includes a first impingement shield portion and a second impingement shield joined to the first impingement shield portion. The assembly also includes a first connection portion formed on the first impingement shield port... | 06/05/2012 |
| 8186167 | Combustor transition piece aft end cooling and related method A transition duct for a gas turbine includes a tubular body having a forward end and an aft end; a plurality of cooling channels formed on an exterior surface of the tubular body at the aft end; a closure band surrounding the aft end, covering at least a portion of ... | 05/29/2012 |
| 8176740 | Method of refurbishing a seal land on a turbomachine transition piece and a refurbished transition piece A method of refurbishing a seal land on a transition piece of a turbomachine includes applying a wear strip to a wall surface of the seal land, and covering the wear strip with a slot protector. ... | 05/15/2012 |
| 8171736 | Combustor with chamfered dome A combustor for a gas turbine engine includes an annular combustor shell having an inner liner and an outer liner respectively with inner and outer flanges at least partly overlapping to form a dome end portion of the shell, at least the outer flange including inter... | 05/08/2012 |
| 8161752 | Combustors with inserts between dual wall liners A combustor includes a first liner; and a second liner forming a combustion chamber with the first liner. The combustion chamber is configured to receive an air-fuel mixture for combustion therein, and the first liner is a first dual wall liner having a first hot wa... | 04/24/2012 |
| 8156744 | Annular combustion chamber for a gas turbine engine An annular gas turbine engine combustion chamber including an outer wall and an inner wall connected by a wall forming the chamber bottom is disclosed. The walls delimit sources of combustion with axes inclined relative to the axis of the chamber. The chamber-bottom... | 04/17/2012 |
| 8156743 | Method and arrangement for expanding a primary and secondary flame in a combustor Disclosed is an arrangement for expanding an annular fluid flow and a center fluid flow, comprising a combustor including a venturi and a centerbody, the centerbody including an upstream end and a downstream end, and a venturi throat defined by the venturi and dispo... | 04/17/2012 |
| 8127553 | Zero-cross-flow impingement via an array of differing length, extended ports A jet impingement array design and method are disclosed for efficiently cooling the liner of a gas turbine combustion chamber, while eliminating almost all effects of coolant gas crossflow. The design includes an array of extended jet ports for which the distance be... | 03/06/2012 |
| 8127552 | Transition scrolls for use in turbine engine assemblies An engine assembly includes a combustor having a combustion chamber in which an air and fuel mixture is combusted to produce combustion gases. The engine assembly further includes a transition scroll coupled to the combustor for receiving the combustion gases. The t... | 03/06/2012 |
| 8113004 | Wall element for use in combustion apparatus A tile for use as part of an inner wall of a gas turbine engine combustor, the tile being provided with deformable cooling pedestals extending into a space between the tile and the outer wall. The pedestals are deformed in contact with the outer wall of the combusto... | 02/14/2012 |
| 8113003 | Transition with a linear flow path for use in a gas turbine engine A transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have an internal passage extending between an inlet to an outlet. An axis of the transition duct bo... | 02/14/2012 |
| 8109098 | Combustor liner for gas turbine engine A combustor liner (230) for a gas turbine engine combustor (200) comprises an inner wall (232), an outer wall (238), a cooling air flow channel (244) formed there between, and a flow control ring (246). The flow control ring... | 02/07/2012 |
| 8104287 | Retaining element and heat shield element for a heat shield and combustion chamber provided with a heat shield A retaining element for retaining a heat shield element on a support structure comprises at least one fixing section adapted to fix the retaining element to the support structure and at least one retaining section adapted to engage with an engaging groove present on... | 01/31/2012 |
| 8099961 | Gas-turbine combustion chamber wall A gas-turbine combustion chamber wall for a gas-turbine has a combustion chamber wall 9, on the inner side of which several tiles 10 are arranged, with an interspace 14 being formed between the tiles 10 and the combustion chamber wall ... | 01/24/2012 |
| 8096133 | Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface A combustor liner includes a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween. A plurality of cooling and dilution ai... | 01/17/2012 |
| 8091366 | Armor-plated machine components and gas turbines A machine component with a base body made of a base material, a part of the surface of which has been equipped with cladding material having a hardness greater in comparison to the base material. The cladding material is segmented and made up of a number of cladding... | 01/10/2012 |
