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| Number | Title | Issue Date |
| 8146364 | Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber Embodiments of the present invention provide resonators (260, 460) that have lateral walls (268, 270) disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis (219) such that a film cooling of substantial portions... | 04/03/2012 |
| 8127546 | Turbine engine fuel injector with helmholtz resonators An end cap for a fuel injector of a turbine engine is disclosed. The end cap includes an annular first surface including a plurality of perforations. The annular first surface is exposed to a combustion chamber of the turbine engine. The end cap is coupled to an end... | 03/06/2012 |
| 8061141 | Combustor assembly including one or more resonator assemblies and process for forming same A combustor assembly is provided comprising a combustor casing; a liner coupled to the combustor casing; a burner assembly coupled to the combustor casing; and at least one resonator assembly. The resonator assembly comprises a resonator outer plate having at least ... | 11/22/2011 |
| 8037687 | Bypass turbomachine with reduction of jet noise In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diff... | 10/18/2011 |
| 8033111 | Damping of vibration of a combustion chamber by resonators Device for damping oscillations of a combustion chamber that includes at least one resonator connected to a pre-chamber in a vibration-damping manner. The pre-chamber is connected to a combustion chamber in a vibration-damping manner via at least one passage channel... | 10/11/2011 |
| 7926278 | Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber A gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber with a combustion chamber casing 2, 3 and several combustion chamber segments arranged in the combustion chamber casing 2, 3 and forming a combustion chamber wall | 04/19/2011 |
| 7832211 | Gas turbine combustor and a gas turbine equipped therewith In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor (3) is provided with a first box body (30), which is installed outside an object body (20) such as a combustor b... | 11/16/2010 |
| 7788926 | Resonator device at junction of combustor and combustion chamber One or more Helmholtz-type resonators (270) is/are provided at the junction (260) of a combustor (220) and a combustion chamber (240) of a gas turbine engine (100). In one embodiment, adjacent Helmholtz-type resonators (290, 291... | 09/07/2010 |
| 7661267 | System for damping thermo-acoustic instability in a combustor device for a gas turbine A system for damping thermo-acoustic instability in a combustor device for a gas turbine, the combustor device including at least one combustion chamber, in particular of an annular type, and at least one burner associated to the combustion chamber and mounted in a ... | 02/16/2010 |
| 7603862 | Combustion device A combustion device, such as an afterburner 4 for a gas turbine engine, comprises primary and secondary fuel delivery means 12, 20. Pressure fluctuations in the afterburner 4 are damped by reducing the supply of fuel through the primary fuel del... | 10/20/2009 |
| 7549290 | Acoustic damper A combustor wall of a gas turbine engine is provided with an acoustic damper component. The component has a first metering passage, a first damping chamber, a first damping passage, a second damping chamber and a second damping passage. Air flows through the damper ... | 06/23/2009 |
| 7464552 | Acoustically stiffened gas-turbine fuel nozzle Under certain conditions, the fuel delivery system can contribute to the formation of strong dynamic pressures in the combustor of a turbine engine. Embodiments of the invention provide a system for dynamically stiffening the fuel supply passage to suppress damaging... | 12/16/2008 |
| 7448215 | Combustion chamber for a gas turbine engine A combustion chamber suitable for a gas turbine engine is provided with at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the chamber interior. The resonator neck is provided with at least cooling holes extend... | 11/11/2008 |
| 7424804 | Premix burner A premix burner has a swirl generator and two perforated through flow elements are arranged at a defined distance from one another in the inflow region for the combustion air. The through flow elements are preferably arranged in such a way that substantially the ent... | 09/16/2008 |
| 7406820 | System and method for turbine engine adaptive control for mitigation of instabilities The present invention provides an adaptive combustion controller and method for a turbine engine. The adaptive combustion controller and method modulates the fuel flow to the turbine engine combustor to reduce combustion instabilities. In particular, the adaptive co... | 08/05/2008 |
| 7363756 | Method for combustion of a fuel In a method for the combustion of a fuel, a fuel or a premixed combustible mixture is introduced into a combustion space as a combustible fluid open jet. The velocity of the open jet is selected in such a way that it is impossible for a stable flame front to form, i... | 04/29/2008 |
| 7334408 | Combustion chamber for a gas turbine with at least two resonator devices A combustion chamber according to the invention, in particular for a gas turbine, includes at least one combustion chamber wall through which cooling fluid flows and at least one resonator device. The combustion chamber according to the invention is distinguished in... | 02/26/2008 |
| 7331182 | Combustion chamber for a gas turbine At least one Helmholtz damper is arranged at a combustion chamber for a gas turbine in order to damp thermoacoustic oscillations; the damping volume of this Helmholtz damper is in communication with the combustion chamber via a connecting passage. Optimum damping is... | 02/19/2008 |
| 7322195 | Acoustic dampers An acoustic resonator for use in an engine is provided. The acoustic resonator includes a cavity having a volume, an aperture, and a passage connecting the aperture and the cavity. The aperture has a profiled surface for delaying separation of fluid entering the pas... | 01/29/2008 |
| 7320222 | Burner, method for operating a burner and gas turbine This invention relates to a burner, especially a gas turbine burner, wherein a Helmholtz resonator downstream of a fuel inlet position in directly linked with a burner channel. In this manner, combustion oscillations do not arrive at the fuel inlet position, thereby... | 01/22/2008 |
| 7311175 | Acoustic liner with bypass cooling An acoustic liner 20 includes a remote panel 26, a proximate panel 28 transversely spaced from the remote panel and a resonator chamber 34b residing between the panels. Perforations 38 penetrate the proximate panel in regist... | 12/25/2007 |
| 7302802 | Aerodynamic trip for a combustion system A apparatus and method for improving combustion by improving at least one of temperature distribution in the combustor, pressure distribution around the combustor and combustion noise level in the combustor, by redistributing air around the combustor to modify the s... | 12/04/2007 |
| 7278256 | Pulsed combustion engine A pulsed combustion apparatus includes a conduit having an outer wall and an inner wall. The inner wall has a number of apertures. An interior space is separated from the outer wall by the inner wall. An induction system is positioned to cyclicly admit charges to th... | 10/09/2007 |
| 7272931 | Method and apparatus to decrease combustor acoustics A method for operating a gas turbine engine includes coupling an anti-resonant frequency system to a combustor including a premixer assembly and a plurality of damper tubes, and adjusting the anti-resonant frequency system until the anti-resonant frequency of the da... | 09/25/2007 |
| 7267297 | Integrated axially varying engine muffler, and associated methods and systems Integrated axially varying engine mufflers, and associated methods and systems. An arrangement in accordance with one embodiment of the invention includes a tailcone having a tapering external surface, a cavity disposed within the surface, and an engine muffler disp... | 09/11/2007 |
| 7246493 | Gas turbine The invention relates to a gas turbine comprising a combustor that extends into a combustion chamber. The port of the combustor is surrounded in a ring-shaped manner by a Helmholtz resonator, whereby combustion oscillations are effectively suppressed due to close co... | 07/24/2007 |
| 7234304 | Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor ... | 06/26/2007 |
| 7232308 | Method and device for affecting thermoacoustic oscillations in combustion systems The present invention relates to a method and a device (1) for affecting thermoacoustic oscillations in a combustion system (6) comprising at least one burner (7) and at least one combustor (8). In order to improve the action of af... | 06/19/2007 |
| 7219498 | Waffled impingement effusion method A combined impingement effusion method comprises brazing or welding a waffled impingement plate to the cold back-side surface of component having effusion holes there through. The impingement plate comprises a plurality of small baffle cells to relieve the thermal s... | 05/22/2007 |
| 7204089 | Arrangement for the cooling of thermally highly loaded components An inexpensively manufacturable arrangement for the cooling of thermally highly loaded components, for example the combustion chamber of a gas turbine, comprises cavities (4) provided on the thermally loaded inner surface/air exit side (3) of the wall ... | 04/17/2007 |
| 7194862 | Resonator adopting counter-bored holes and method of suppressing combustion instabilities A resonator for damping pressure waves or instabilities in a system supported by acoustic energy wherein the resonator adopts the use of counter-bored openings on the downstream side of the resonator within the flow path of the system. The resonator includes a first... | 03/27/2007 |
| 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 |
| 7124856 | Acoustic liner for gas turbine engine A passive acoustic liner system (50) for attenuating a sound field comprising, in acoustic series, a mode-scattering segment (48) and a sound-absorbing segment (40), wherein the mode scattering segment (48) provides a reactance between âˆ... | 10/24/2006 |
| 7117675 | Cooling of liquid fuel components to eliminate coking A system for cooling at least one gas turbine liquid fuel component located in a high temperature environment to eliminate coking in the component is disclosed. The system includes a sleeve surrounding the liquid fuel component, a device for providing a current of c... | 10/10/2006 |
| 7114323 | Jet exhaust noise reduction system and method A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft en... | 10/03/2006 |
| 7104068 | Turbine component with enhanced stagnation prevention and corner heat distribution Aspects of the invention relate to a system for reducing stagnation between substantially adjacent components while providing enhanced heat distribution properties in the corners and edges of the components. Each component is generally hollow and has two walls dispo... | 09/12/2006 |
| 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 |
| 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 |
| 7080514 | High frequency dynamics resonator assembly Aspects of the invention relate to resonator assemblies for use in non-uniform flow environments. The resonator assemblies include one or more features, such as a box or a scoop, for substantially equalizing the pressure on the resonator. In the box configuration, a... | 07/25/2006 |
| 7080515 | Gas turbine can annular combustor A gas turbine engine (120) includes a cylindrical basket (146) having an axis (14) and a single main burner assembly (12) disposed within the basket. A burner insert (34) is disposed in an annular space between the burner assembly ... | 07/25/2006 |
