Patent application number | Description | Published |
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 |
20130139511 | GAS TURBINE COMBUSTOR AND GAS TURBINE - A gas turbine combustor includes: an external cylinder ( | 06-06-2013 |
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 |
20140013762 | COMBUSTOR AND GAS TURBINE PROVIDED WITH SAME - A combustor ( | 01-16-2014 |
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 |
20140202161 | COMBUSTOR AND ROTATING MACHINE - A combustor includes: a combustor basket configured to surround a fuel nozzle from an outer circumferential side, and a plurality of connecting members formed in a circumferential direction at intervals to connect a rear end of the combustor basket and a casing and configured to define a flow path through which compressed air introduced into the combustor basket flows. A circulation direction of the compressed air flowing through the flow path is configured to be reversed at a rear end of the combustor basket and the compressed air is introduced into the fuel nozzle. The flow path is partially or entirely inclined in the circumferential direction to blow the compressed air. | 07-24-2014 |
20150300648 | GAS TURBINE COMBUSTOR AND GAS TURBINE - A gas turbine combustor forms a combustion region R | 10-22-2015 |
20160091207 | COMBUSTOR AND GAS TURBINE HAVING THE SAME - A combustor is equipped with a burner case, and a base plate spreading from a downstream end of the burner case in a radial direction. The base plate defines a purging air space at an upstream side of the base plate. The combustor is formed with a purging air flow passage that injects purging air in the purging air space to a downstream side relative to the base plate. An outflow opening of the purging air flow passage is formed within an opening formation range. The opening formation range is made up of a range from the downstream end of the burner case to a plate thickness dimension of the base plate toward the upstream side, and a range from an inner circumferential surface of the burner case to the plate thickness dimension of the base plate in the radial direction. | 03-31-2016 |