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| Number | Title | Issue Date |
| 8087228 | Segmented combustor cap A combustor cap is cooperable with an impingement plate in a turbine fuel nozzle and includes a plurality of cap segments independently securable to the impingement plate. The plurality of cap segments are radially and tangentially movable relative to the impingemen... | 01/03/2012 |
| 8082724 | Combusting system, remodeling method for combusting system, and fuel injection method for combusting system The present invention improves the reliability of a combusting system including multiple combustors and improves an environmental performance thereof. The invention includes a device that delays the start time of fuel injection from a fuel nozzle of a combustor incl... | 12/27/2011 |
| 7950215 | Sequential combustion firing system for a fuel system of a gas turbine engine A gas turbine combustion system for a turbine engine is disclosed. The gas turbine combustion system may include a plurality of combustor baskets positioned circumferentially about a longitudinal axis of the turbine engine, at least one firing nozzle extending into ... | 05/31/2011 |
| 7886517 | Impingement jets coupled to cooling channels for transition cooling Embodiments of a transition (400) of the present invention comprise a cooling channel (20, 30, 410) defined in part by an outer wall (23) and an inner wall (24). The cooling channel (20, 30, 410) also comprises lateral side walls (... | 02/15/2011 |
| 7874138 | Segmented annular combustor A combustor for use in a turbine engine including a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. An inner annulus wall extends from a burner end of the combustor to an ... | 01/25/2011 |
| 7836677 | At least one combustion apparatus and duct structure for a gas turbine engine A combustion apparatus and duct structure for a gas turbine engine are provided. The combustion apparatus comprises a combustion system to receive fuel and air, ignite at least a portion of the fuel and air and output a stream of first combustion products and any re... | 11/23/2010 |
| 7827777 | Combustor with reduced carbon monoxide emissions A combustor arrangement for a gas turbine engine (31) has a split line (42) and a plurality of burners (20,37) arranged in an annular ring (40). The burners (46) of the combustor on either side of the split line (42) have a ... | 11/09/2010 |
| 7784264 | Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine One embodiment of a transition-to-turbine seal (300) comprises a first, flattened section (302) adapted to be received in a peripheral axial slot (320) of a transition (325), and a second, generally C-shaped section (301). The gene... | 08/31/2010 |
| 7726114 | Integrated combustor-heat exchanger and systems for power generation using the same A combustor-heat exchanger system comprising a plurality of cans. Each can includes an inner cylinder and an outer cylinder forming an annular space in between, wherein the inner cylinder is configured to receive and combust a fuel and compressed oxidant to generate... | 06/01/2010 |
| 7600370 | Fluid flow distributor apparatus for gas turbine engine mid-frame section A plenum (210) in a gas turbine engine mid-frame section (200) comprises one or more annular flow splitters (240) spaced from an inboard annular wall (232) that partition air flow flowing from a compressor into two or more portions of flo... | 10/13/2009 |
| 7481037 | Cooling structure of gas turbine tail pipe A plate spring 6 having a hook-shaped cross section from the lower part is installed in the neighborhood of one end “b” of an impingement-cooling plate 4. One end “c” on the lower side is fixed to a rib 1d by welding, while the ot... | 01/27/2009 |
| 7373772 | 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 an... | 05/20/2008 |
| 7340881 | Gas turbine combustor The invention provides a gas turbine combustor in which the size of a combustor outer casing can be reduced. A transition inner duct and a transition outer duct are disposed in a main housing, inlet openings for a fluid to cool the transition inner duct are formed a... | 03/11/2008 |
| 7340880 | Compressed air bypass valve and gas turbine It is the objective of the present invention to enable smooth rotation of the grid plate and normal operation of the bypass valve, regardless of the operational state of the gas turbine. The bypass valve according to the present invention is provided with a frame, w... | 03/11/2008 |
| 7329084 | Turbomachine Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow whi... | 02/12/2008 |
| 7310938 | 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... | 12/25/2007 |
| 7305817 | Sinuous chevron exhaust nozzle A gas turbine engine exhaust nozzle includes a row of laterally sinuous chevrons extending from an aft end of an exhaust duct. The chevrons have radially outer and inner surfaces bound by a laterally sinuous trailing edge extending between a base of the chevrons adj... | 12/11/2007 |
| 7299617 | Combustion chamber intermediate part for a gas turbine This invention relates to a gas turbine having a combustion chamber arrangement and a turbine chamber connected downstream of said combustion chamber arrangement, wherein the combustion chamber arrangement includes a plurality of individual combustion chambers forme... | 11/27/2007 |
| 7299618 | Gas turbine combustion apparatus A gas turbine combustion apparatus has a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each combustor comprising a combustor inner tube and a combustor transition pipe, but lacks a turbine bypass ... | 11/27/2007 |
| 7278254 | Cooling system for a transition bracket of a transition in a turbine engine A heat shield for a transition of a turbine engine for coupling a transition component of a turbine engine to a turbine vane assembly to direct combustor exhaust gases from the transition into the turbine vane assembly. The heat shield may be capable of reducing the... | 10/09/2007 |
| 7277777 | Method and system for real time reporting of boiler adjustment using emission sensor data mapping A method to adjust a boiler having a flue gas duct including: sensing flue gas emissions in the gas duct with a plurality of emission sensors arranged in an array; generating a multidimensional graphical depiction of the flue gas emissions by plotting sensor data ca... | 10/02/2007 |
| 7277801 | Method for testing catalytic converter durability The present application relates in general to methods for testing the performance of an automotive catalytic converter under conditions simulating those which occur in motor vehicles over extended driving conditions. ... | 10/02/2007 |
| 7217099 | Coated forward stub shaft dovetail slot A compressor forward stub shaft comprising a plurality of axially spaced, annular rows of dovetail grooves, at least a first and a second of the plurality of rows having dovetail slots coated in part with an anti-wear coating. ... | 05/15/2007 |
| 7200987 | Off-axis pulse detonation configuration for gas turbine engine The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation ... | 04/10/2007 |
| 7181914 | Diffuser for gas turbine engine A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member ... | 02/27/2007 |
| 7174719 | Gas turbine engine with seal assembly A gas turbine engine includes an interstage seal assembly positioned in a plenum between the compressor section and turbine section. The seal assembly includes an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid... | 02/13/2007 |
| 7171813 | Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine A fuel injection nozzle has a cylindrical nozzle body having a cavity where fuel passes through. A plurality of hollow spokes, each having an aerofoil cross section, are provided around the nozzle body. Each hollow spoke has four fuel injection holes in total on bot... | 02/06/2007 |
| 7159403 | Apparatus for assembling gas turbine engine combustors A method for assembling a gas turbine engine combustor facilitates reducing costs and time required for assembly. The combustor includes a spectacle plate, a plurality of swirlers, and a plurality of deflector plates. The method includes coupling an assembly fixture... | 01/09/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7140185 | 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 co... | 11/28/2006 |
| 7137241 | Transition duct apparatus having reduced pressure loss A gas turbine transition duct having a reduced pressure loss is disclosed. The transition duct of the preferred embodiment comprises a panel assembly having a first panel fixed to a second panel and a mounting assembly for securing the transition duct to a turbine i... | 11/21/2006 |
| 7111463 | Combustion wave ignition for combustors A system, such as a turbine power production system, including a plurality of combustion chambers. The combustion chamber may be provided with an ignition system that allows for substantially simultaneous ignition of each of the plurality of the combustors. Generall... | 09/26/2006 |
| 7104065 | Damping arrangement for reducing combustion-chamber pulsation in a gas turbine system A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (1), with a combustion-chamber wall (2), which is of double-walled design and, with an outer wall-surface part (22) and an inner wall-surfac... | 09/12/2006 |
| 7096668 | 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... | 08/29/2006 |
| 7093794 | Aircraft and detonative engine incorporating pulse detonation engines An aircraft includes at least one airfoil having a leading edge and a trailing edge. A number of pulse detonation engines are distributed along one of the leading and trailing edges of the airfoil and are positioned beneath the airfoil. Each pulse detonation engine ... | 08/22/2006 |
| 7093441 | 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 ... | 08/22/2006 |
| 7089741 | Gas turbine combustor A gas turbine combustor includes a combustion liner in which a combustion region is formed; and a housing provided for a wall of the combustion liner in a predetermined circumferential region of the combustion liner to form a resonance space between the combustion l... | 08/15/2006 |
| 7082765 | Methods and apparatus for reducing gas turbine engine emissions A method enables a gas turbine engine to be assembled. The method comprises coupling a fuel nozzle within the engine to inject fuel into the engine, wherein the fuel nozzle includes three independent injection circuits arranged such that the second injection circuit... | 08/01/2006 |
| 7080513 | Seal element for sealing a gap and combustion turbine having a seal element The invention pertains to a seal element for sealing a gap, in particular within a turbo-machinery, between a first component and a second components spaced apart from each other, said first component having a first surface and said second component having an opposi... | 07/25/2006 |
| 7080516 | Gas diffusion arrangement A gas diffusion arrangement (22) for a gas turbine engine (10) is disclosed. The gas diffusion arrangement (22) has an inlet (26) and an outlet (28) for the gas, and comprises diffusion means (32) having an upstream region (... | 07/25/2006 |
