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Power Plants > Combustion Products Used As Motive Fluid > Combustion Products Generator > Combustor Liner Combustor LinerCombustor Liner patent applications listed are from June 2005 to current and include Date, Patent Application Number, Patent Title, Patent Abstract summary and are linked to the corresponding patent application page.01/17/08 - 20080010989 - 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 the gas turbine ... 11/08/07 - 20070256418 - Method and apparatus for assembling a gas turbine engine A method for assembling a gas turbine engine combustor is provided. The method includes providing a heat shield defined by a perimeter. The perimeter includes a radially inner edge, a radially outer edge, an axially inner edge, an axially outer edge, and an opening that extends from an upstream side ... 10/25/07 - 20070245741 - Methods and system for reducing pressure losses in gas turbine engines A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion chamber therein, and coupling an annular flowsleeve radially outward from the combustor liner such that an annular flow path is defined substantially circumferentially between the ... 10/18/07 - 20070240422 - Gas turbine transition duct 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 coordinate values X, Y, and Z as set forth ... 10/11/07 - 20070234726 - Combustor liner v-band design A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening ... 10/04/07 - 20070227148 - Air flow conditioner for a combustor can of a gas turbine engine A burner (27) of a gas turbine engine (10) includes a cylindrical basket (60) comprising an air flow reversal region (86). The flow reversal region ends at an air inlet plane (84) of the basket. The burner also includes a flow conditioner (90) disposed in the flow reversal region transecting ... 08/23/07 - 20070193273 - Method and apparatus for gas turbine engines A method for fabricating a gas turbine engine combustor that includes a domeplate and at least one fuel injector extending through an opening in the domeplate. The method includes fabricating a heatshield that includes a threaded collar extending upstream from the heatshield, positioning the heatshield on a downstream side of ... 08/09/07 - 20070180828 - Combustor liners A combustor liner for use in a gas turbine engine includes a first liner section and a second liner section. They are joined together by welding or a mechanical fixing along a common join line or weld. A heat shield extends along the join line to protect it from the ... 08/09/07 - 20070180827 - Gas turbine engine transitions comprising closed cooled transition cooling channels A transition (200) for a gas turbine engine (100) comprises a transition wall (201) comprising cooling channels (213L, 213R, 223L, 223R) that are adapted to pass a cooling fluid, such as compressed air from a compressor (102) during operation of the gas turbine engine (100) so as to cool combusted ... 07/12/07 - 20070157618 - Methods and apparatus for assembling gas turbine engines A method for assembling a gas turbine engine is provided. The method includes providing a combustor liner support including a first portion formed with a plurality of circumferentially-spaced recessed areas, and a second portion extending from the first portion. The method also includes coupling the combustor liner support within a ... 07/05/07 - 20070151249 - Heat shield A heat shield according to the invention on a support structure comprises a number of heat shield elements, which are configured and arranged on the support structure such that they abut each other leaving gaps. The support structure of the heat shield according to the invention has a peripheral direction ... 06/28/07 - 20070144177 - 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 into the first fixed vane portion. ... 06/14/07 - 20070130951 - Combustor Provided is a combustor comprising an entrance through which the fuel flows thereinto; a combustion chamber, connected to the entrance, having a larger cross-section area than that of the entrance; and a plurality of protrusions installed along the interface of the entrance and the combustion chamber. Thus, the combustor according ... 05/24/07 - 20070113558 - Combustion liner for gas turbine formed of cast nickel-based superalloy and method A combustion liner for a gas turbine combustion system is provided. The combustion liner comprises a combustion zone between an inlet end and an exhaust end. The combustion liner comprises a one-piece casting construction. The combustion liner is formed from a nickel-based superalloy having strength characteristics. ... 03/29/07 - 20070068166 - Device for guiding an element in an orifice in a wall of a turbomachine combustion chamber Device (48) for guiding an element in an orifice in a wall of a turbomachine combustion chamber (10), comprising a ring (50) and a bush (52), the ring being traversed axially by the element and comprising an external annular rim (60) guided transversely in an internal annular channel (52) of ... 03/22/07 - 20070062198 - 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 heat shield elements. ... 03/15/07 - 20070056289 - Annular combustion chamber for a turbomachine An annular turbine engine combustion chamber configured so that in an axial half-section, values of first acute angles formed between a line that is effectively the median of the half-section located between an external axial wall and an internal axial wall, and the principal directions, in this half-section, of the ... 02/15/07 - 20070033941 - Transition piece for gas turbine As used to connect a combustor of a gas turbine to a stage of the gas turbine, a transition piece has a generally tubular body, an inlet to receive hot gases from the combustor, and an outlet to discharge the gases. The transition piece has a frame, which surrounds the ... 01/25/07 - 20070017225 - Combustion transition duct providing stage 1 tangential turning for turbine engines 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 that is offset from the inlet in the longitudinal, radial and tangential directions. The offset outlet ... 01/18/07 - 20070012043 - Turbine spring clip seal An improved turbine spring clip seal for directing gases to be mixed with fuel in a combustor basket. The turbine spring clip seal may include an inner housing and an outer housing. The inner housing or the outer housing, or both, may be shortened relative to conventional clips and may ... 01/11/07 - 20070006588 - Gas turbine engine combustor with improved cooling A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide improved cooling efficiency in regions of the combustor dome corresponding to predetermined hotspots. ... 01/04/07 - 20070000252 - Heat shield block for lining a combustion chamber wall, combustion chamber and gas turbine The invention relates to a heat shield block, particularly for lining a combustion chamber wall, with a hot side that can be subjected to the action of hot medium and with a wall side situated opposite the hot side. A core area, which has a core material, extends inside the ... 08/10/06 - 20060174626 - Shroud for a turbomachine combustion chamber A shroud for a combustion chamber bottom designed to cover fuel injectors is provided with drillings (21) on at least one of its sides to open up the cavity within the shroud and reduce noise that it produces and combustion instabilities. The drillings also have the effect of reducing instabilities ... 08/03/06 - 20060168965 - Combustion liner with enhanced heat transfer A combustion liner having enhanced heat transfer over at least a portion of the liner is disclosed. The combustion liner comprises, amongst other features, an outer surface wherein at least a region of the outer surface is textured in a substantially uniform pattern such that the surface area exposed to ... 06/29/06 - 20060137351 - Wall structure for limiting a hot gas path A wall structure for restricting a hot-gas path in a gas turbine or in a combustion chamber includes a first wall segment having a first face and a second wall segment having a second face and disposed adjacent to each other in a connection area. A first face is disposed ... 06/22/06 - 20060130486 - Method and apparatus for assembling gas turbine engine combustors A method enables the operation of a gas turbine engine. The method comprises channeling airflow into a cooling passageway defined between the combustor casing and an inner liner of the combustor, wherein the inner liner is fabricated from a plurality of panels coupled together, channeling airflow into a cooling passageway ... 06/22/06 - 20060130485 - Method and apparatus for assembling gas turbine engine combustors A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled together, and coupling an outer support ... 06/22/06 - 20060130484 - Cooled gas turbine transition duct A transition duct (40) for a gas turbine engine (10) incorporating a combination of cooling structures that provide active cooling in selected regions of the duct while avoiding cooling of highly stressed regions of the duct. In one embodiment, a panel (74) formed as part of the transition duct includes ... 06/08/06 - 20060117755 - Wall elements for gas turbine engine combustors A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member ... 03/23/06 - 20060059916 - Cooled turbine engine components A combustor heat shield panel has interior and exterior surfaces with a number of circuitous non-interconnected cooling gas passageways having inlets on the exterior surface and outlets on the interior surface. ... 03/02/06 - 20060042255 - Combustor cooling with angled segmented surfaces A combustor liner for a gas turbine includes a body having a plurality of angled strips on an outside surface of the combustor liner. The plurality of angled strips are arranged in an array about the outside surface. A space is disposed between each of said plurality of angled strips ... 02/23/06 - 20060037322 - Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. In longitudinal section, a first portion of the combustor interior volume converges from fore to aft and a second portion, aft of the first ... 01/26/06 - 20060016190 - Methods and apparatus for cooling turbine engine combustor ignition devices An ignition device assembly for a gas turbine engine combustor includes a body and a shroud. The body extends from an inlet end to an outlet end, and the shroud extends circumferentially around at least a portion of the body, and axially from a first end to a tip end. ... 01/19/06 - 20060010874 - Cooling aft end of a combustion liner A liner (18) installed in a transition region (16) between a combustion section (12) of a gas turbine engine (10) and an air discharge section (14) of the turbine. The liner has an air inlet (26) for admitting air into the liner, and an air outlet (28) by which air ... 01/19/06 - 20060010873 - Gas turbine combustor end cover An end cover for a gas turbine combustor that eliminates the use of braze joints within the plate portion of the end cover is disclosed. The end cover comprises a plate and a plurality of fluid inlets with the fluid inlets directing fluids to first and second manifolds machined into ... 01/12/06 - 20060005543 - Heatshielded article A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated cold side 32. A projection projects from an origin 36 ... 12/22/05 - 20050279099 - Multi-zone tubing assembly for a transition piece of a gas turbine A replaceable section (25) of force-cooling tubing assembly (21, 22) for attachment to a transition piece (5) of a gas turbine is comprised of two ends (54, 70) fashioned for attachment by removable unions (52) to adjoining parts of a force-cooling tubing assembly. When assembled thereto to complete the assembly, ... 12/01/05 - 20050262846 - Combustion apparatus A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not ... 12/01/05 - 20050262845 - Combustion liner having improved cooling and sealing A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness along the aft end of the combustion liner is improved, resulting in extended component life, while utilizing a simpler combustion liner geometry. The region of the combustion liner ... 12/01/05 - 20050262844 - Combustion liner seal with heat transfer augmentation A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end ... 11/10/05 - 20050247062 - Gas turbine The invention relates to a gas turbine comprising a combustion chamber, into which fuel and combustion air are fed and caused to react, in order to produce a working fluid. The aim of the invention is to provide a particularly simple construction, which achieves a relatively high degree of efficiency ... 11/03/05 - 20050241314 - Cooling structure of gas turbine tail pipe A plate spring 6 having a hook-shaped cross section from the lower part is installed in a neighborhood of one end “b” of an impingement-cooling plate 4. One end “c” on the lower side is fixed to a rib Id by welding, while the other end “b” on the upper ... 09/22/05 - 20050204741 - Turbine combustor transition piece having dilution holes A transition piece body, having an inlet end for receiving combustion products from a turbine combustor and an outlet end for flowing the gaseous products into a first stage nozzle, has dilution holes in zones respectively adjacent the transition piece body inlet and outlet ends. The volume of dilution air ... 09/15/05 - 20050198966 - Burner for a gas turbine engine To meet emissions standards, many gas turbine engines use some form of lean, pre-mixed combustion systems. These systems may lead to combustion oscillations or other instabilities. Jet combustion techniques provide a stable alternative lean, pre-mixed combustion system. The present invention presents a jet combustion system that includes a first cylinder ... 07/07/05 - 20050144954 - Apparatus and methods for minimizing and/or eliminating dilution air leakage in a combustion liner assembly Variations in dilution air leakage paths in a gas turbine combustion liner assembly are minimized or eliminated to reduce emissions and variations in emissions from combustor to combustor. Leakage paths between the liner sleeve and venturi outer liner are minimized by using additional rivets at that joint. The leakage paths ... 07/07/05 - 20050144953 - Flow sleeve for a law nox combustor A gas turbine combustor structure having improved cooling effectiveness and increased life as well as a method for improving the cooling effectiveness is disclosed. The gas turbine combustor incorporates a unique flow sleeve configuration for directing air to more effectively cool a combustion liner. The flow sleeve geometry is configured ... 06/23/05 - 20050132708 - Cooling and sealing design for a gas turbine combustion system An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received within the transition duct such that a combustion ... ### FreshPatents.com Support |