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| Number | Title | Issue Date |
| 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 |
| 8091364 | Combustion chamber wall, gas turbine installation and process for starting or shutting down a gas turbine installation In a combustion chamber wall for a combustion chamber having a combustion chamber outlet through which a hot combustion exhaust gas can exit the combustion chamber, the combustion chamber wall comprises an outlet end which surrounds the combustion chamber outlet, an... | 01/10/2012 |
| 8091367 | Combustor with improved cooling holes arrangement A gas turbine engine combustor liner with at least one of the inner and outer liners that is effusion cooled and has a row of groups of circumferentially spaced apart dilution holes defined therethrough. Each group is located within a respective zone of the combusto... | 01/10/2012 |
| 8091365 | Canted outlet for transition 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 has an internal passage from an inlet to an outlet. The outlet may include canted sides that reduce formation of damaging vibration in do... | 01/10/2012 |
| 8079219 | Impingement cooled combustor seal Disclosed is a combustor seal including a seal support locatable at a first combustor component and having a plurality of through impingement holes. A wave-shaped seal located at the seal support and defining at least one seal cavity between the wave-shaped seal and... | 12/20/2011 |
| 8069669 | Separator for feeding cooling air to a turbine A combustion chamber which is fitted with a separator disposed between the radially inner wall of the chamber and the inner flange of the chamber is disclosed. The separator includes a tubular portion and a fastener portion. The tubular portion is centered on the ma... | 12/06/2011 |
| 8065881 | Transition with a linear flow path with exhaust mouths 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... | 11/29/2011 |
| 8056342 | Hole pattern for gas turbine combustor A combustor for a turbine engine includes an outer liner having a row of circumferentially distributed outer combustion air holes and an inner liner circumscribed by the outer liner and having a row of circumferentially distributed inner combustion air holes. The in... | 11/15/2011 |
| 8056343 | Off center combustor liner The present application provides a liner for a combustor. The combustor liner may include a mouth, a passage for a flow of fuel, a passage for a flow of air, a first zone for mixing the flow of fuel and the flow of air, and the first zone having a constant diameter.... | 11/15/2011 |
| 8051662 | Transition duct assemblies and gas turbine engine systems involving such assemblies Transition duct assemblies and gas turbine engine systems involving such assemblies are provided. In this regard, a representative a transition duct assembly for a gas turbine engine includes: an impingement sheet having cooling holes formed therethrough, an inlet e... | 11/08/2011 |
| 8028528 | Annular gas turbine combustor A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a di... | 10/04/2011 |
| 8028529 | Low emissions gas turbine combustor A gas turbine combustor including: a primary combustion chamber; a secondary combustion chamber downstream of the primary combustion chamber; a venturi having a venturi throat; a transition piece; a cap assembly attached to the primary combustion chamber, and an ext... | 10/04/2011 |
| 8020385 | Centerbody cap for a turbomachine combustor and method A turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a centerbody within the cap assembly, a wall of the centerbody having a first end, a second end and an intermediate portion, and an external turbulator member in operabl... | 09/20/2011 |
| 8015817 | Cooling structure for gas turbine transition duct A transition duct for conveying hot combustion gas from a combustor to a turbine in a gas turbine engine. The transition duct includes a panel including a middle subpanel, an inner subpanel spaced from an inner side of the middle subpanel to form an inner plenum, an... | 09/13/2011 |
| 8001787 | Transition support system for combustion transition ducts for turbine engines A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition ... | 08/23/2011 |
| 7975487 | Combustor assembly for gas turbine engine A combustor liner assembly includes a liner assembly, including a hot dome, a hot wall, and an impingement shield. The liner assembly further includes a convector assembly. The combustor liner assembly further includes an impingement dome assembly, including a ring-... | 07/12/2011 |
| 7954326 | Systems and methods for cooling gas turbine engine transition liners A gas turbine engine assembly includes a combustor configured to combust an air-fuel mixture to produce combustion gases in a first direction; a transition liner coupled to the combustor and adapted to receive the combustion gases from the combustor and to redirect ... | 06/07/2011 |
| 7954325 | Gas turbine combustor A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner ... | 06/07/2011 |
| 7950233 | Combustor A combustor is provided having one or more apertures adapted to asymmetrically introduce air adjacent the fuel nozzles to reduce smoke resulting from unburned hydrocarbons in a gas turbine engine combustion system by impeding escape of unburned hydrocarbons. ... | 05/31/2011 |
| 7942005 | Combustion chamber in a turbomachine A turbomachine combustion chamber has primary and dilution air inlet orifices formed by die stamping to have edges that project into the inside of the combustion chamber, and stress relaxation and/or reduction means in the edges or in the vicinity of the edges of sa... | 05/17/2011 |
| 7942004 | Tile and exo-skeleton tile structure It is known to assist cooling of a combustion chamber in a gas turbine by fixing an exo-skeleton tile structure to an inner annular combustion liner shell. To improve structural integrity of the exo-skeleton tile structure, each tile is formed with at least one rib ... | 05/17/2011 |
| 7934382 | Combustor turbine interface A combustor assembly for a turbine engine includes an aft open end that communicates gas flow to a turbine assembly. The combustor assembly includes a liner assembly that terminates at a first fixed vane. A portion of the liner assembly extends an axial distance int... | 05/03/2011 |
| 7926283 | Gas turbine combustion system cooling arrangement Cooling is provided for a gas turbine combustion system that includes a first member, such as a liner, having exterior and interior surfaces that define a wall therebetween and a central area. A second member, such as a cap, is located adjacent that interior surface... | 04/19/2011 |
| 7908866 | Gas turbine combustor An object of the present invention is to provide a gas turbine combustor with improved fatigue resistance of a combustor. It is possible to intentionally reduce a stiffness of each of flanges of upper and lower walls of an end portion (outlet) of the tail pipe of th... | 03/22/2011 |
| 7905094 | Combustor systems with liners having improved cooling hole patterns A combustor liner assembly includes a liner and a first group of cooling holes formed in the liner and having an increasing density in a downstream direction. The first group of cooling holes include a generally circumferential first row of cooling holes, a generall... | 03/15/2011 |
| 7900457 | Method and apparatus to facilitate reducing NOemissions in turbine engines A method for fabricating a combustor liner for a gas turbine engine is provided. The method includes providing an annular shell including a plurality of circumferentially extending panels, wherein the plurality of circumferentially extending panels includes a first ... | 03/08/2011 |
