Patent application number | Description | Published |
20110027732 | BURNER OF A GAS TURBINE - The burner of a gas turbine includes two or more part cone shells arranged offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein. A lance carrying a liquid fuel nozzle arranged centrally in the cone shaped chamber is also provided. A portion of the nozzle facing the cone shaped chamber is divergent in shape. A diffuser angle (α) between the wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5°. A diverging portion of the nozzle has a diffuser length to nozzle diameter ratio comprised between 2-6. The nozzle diameter is the smaller diameter of the diverging portion. | 02-03-2011 |
20110048018 | COMBUSTION DEVICE OF A GAS TURBINE - A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper. | 03-03-2011 |
20110139541 | METHOD FOR ADJUSTING A HELMHOLTZ RESONATOR AND AN ADJUSTABLE HELMHOLTZ RESONATOR - In a method for adjusting a Helmholtz resonator ( | 06-16-2011 |
20110265484 | COMBUSTION DEVICE FOR A GAS TURBINE - A combustion device ( | 11-03-2011 |
20110308630 | HELMHOLTZ DAMPER AND METHOD FOR REGULATING THE RESONANCE FREQUENCY OF A HELMHOLTZ DAMPER - A Helmholtz damper, including an enclosure, a neck extending from the enclosure, and a pipe for inserting into the neck. The portions of the pipe inserted into the neck is adjusted to regulate a resonance frequency of the Helmholtz damper. | 12-22-2011 |
20110308654 | DAMPER ARRANGEMENT AND METHOD FOR DESIGNING SAME - A damper arrangement ( | 12-22-2011 |
20120279229 | METHOD FOR PROTECTING A GAS TURBINE ENGINE AGAINST HIGH DYNAMICAL PROCESS VALUES AND GAS TURBINE ENGINE FOR CONDUCTING THE METHOD - A method can protect a gas turbine engine ( | 11-08-2012 |
20140109591 | DAMPER ARRANGEMENT FOR REDUCING COMBUSTION-CHAMBER PULSATION - The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor. | 04-24-2014 |
20140345284 | DAMPER FOR GAS TURBINE - The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck. | 11-27-2014 |
20150047357 | DAMPER FOR COMBUSTION OSCILLATION DAMPING IN A GAS TURBINE - The invention relating to a A damper for combustion oscillation damping for a gas turbine, includes a resonator cavity with a box or cylinder shape, a neck in flow communication with the resonator cavity and a combustion chamber. The length L | 02-19-2015 |
20150059345 | SIMULTANEOUS BROADBAND DAMPING AT MULTIPLE LOCATIONS IN A COMBUSTION CHAMBER - The damper arrangement includes a plurality of interconnected volumes and a plurality of necks for connecting the damper to a combustion chamber at a plurality of contact points. The plurality of necks are connected to the plurality of volumes. | 03-05-2015 |
20150075168 | COMBUSTION CHAMBER SEAL SEGMENTS EQUIPPED WIHT DAMPING DEVICES - A strip seal arrangement for turbine components employs acoustic damping. A sealing plate having a front face adjacent a combustion chamber and a back face facing away from a combustion chamber configured to have one or more holes of a predefined cross-sectional area. Containers having predefined volumes are attached to the back face of the sealing plate such that the one or more holes are in fluidic communication with the one or more containers thereby creating at least one acoustic damper. The side edges of the sealing plate fit into a slots of burner front panels, creating a seal between the panels. | 03-19-2015 |