Patent application number | Description | Published |
20120125006 | GAS TURBINE COMBUSTOR AND GAS TURBINE - In a gas turbine combustor and a gas turbine, an air passage ( | 05-24-2012 |
20120167569 | GAS TURBINE COMBUSTION BURNER - Provided is a gas turbine combustion burner capable of uniformly ejecting fuel from ejection holes for reduced NO | 07-05-2012 |
20130008167 | GAS TURBINE COMBUSTOR - A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket. | 01-10-2013 |
20130160453 | COMBUSTOR AND GAS TURBINE - A combustor includes a combustion chamber and an acoustic liner, wherein through-holes through are formed in a wall of the combustion chamber, a plurality of rows of the through-holes is arranged in a lengthwise direction of the combustor, the through-holes of a first through-hole row are shifted with respect to the through-holes of a second through-hole row so that centers of the through-holes of the first and second through-hole rows adjacent each other are staggered in the circumferential direction, cooling grooves are formed so as to avoid the through-holes inside that is sandwiched between the outer peripheral surface and the inner peripheral surface of the combustion chamber, and the cooling grooves include transverse cooling grooves extending in the circumferential direction between rows of the through-holes, and longitudinal cooling grooves extending in the lengthwise direction between the through-holes and connecting the transverse cooling grooves adjacent to each other. | 06-27-2013 |
20140041389 | NOZZLE, GAS TURBINE COMBUSTOR AND GAS TURBINE - A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage. | 02-13-2014 |
20140311151 | GAS TURBINE COMBUSTOR - Provided is a gas turbine combustor having improved maintainability obtained by facilitating the mounting and removal of a base plate for supporting main burners and a pilot burner. A gas turbine combustor is provided with: a pilot burner disposed at the center of a combustor inner tube; main burners provided on the outside of the pilot burner in the radial direction so as to be arranged in the circumferential direction of the inner peripheral surface of the combustor inner tube; a circular disc-shaped base plate disposed within the combustor inner tube and supporting both the pilot burner and the main burners; and an engagement section protruding from the inner peripheral surface toward the inside thereof in the radial direction and engaging with the base plate. The base plate, and the engagement section or the inner peripheral surfaces are affixed by bolts. | 10-23-2014 |
20150101343 | GAS TURBINE COMBUSTOR - A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket. | 04-16-2015 |
20150300648 | GAS TURBINE COMBUSTOR AND GAS TURBINE - A gas turbine combustor forms a combustion region R | 10-22-2015 |