Patent application number | Description | Published |
20080216461 | Micro Gas Turbine System - A micro gas turbine system is provided which increases power generation efficiency and output of power generation by means of water spray and which can exercise effective water spray control with simple control. The micro gas turbine system, according to the present invention, including a compressor, a combustor, a regenerative heat exchanger, a generator and a power transducer is provided with a plurality of spray water supply lines which include spray water nozzles and shutoff valves and which supply a prescribed amount of spray water by opening and closing the shutoff valves. | 09-11-2008 |
20090173075 | BURNER AND GAS TURBINE COMBUSTOR - A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet. | 07-09-2009 |
20100050648 | COMBUSTOR AND THE METHOD OF FUEL SUPPLY AND CONVERTING FUEL NOZZLE - An object of this invention is to accelerate further mixing of a fuel and air independently of a flow rate of the fuel. | 03-04-2010 |
20100064694 | COMBUSTOR, METHOD OF SUPPLYING FUEL TO SAME, AND METHOD OF MODIFYING SAME - An object of this invention is to suppress adhesion of a flame to periphery of air hole outlets arranged on an air hole plate. | 03-18-2010 |
20100251725 | Combustor and Method for Modifying the Same - This invention is intended to maintain combustor reliability. | 10-07-2010 |
20110076628 | COMBUSTOR - This invention is directed to supply a combustor having a structure that reduces NOx emissions while maintaining combustion stability. The combustor has a chamber into which fuel and air are supplied. An air hole plate having a plurality of air holes upstream of the chamber is also disclosed, and fuel nozzles supplying fuel to the air holes of the air hole plate are further disclosed. In the combustor, a center of a chamber-side of the air hole plate is closer to the chamber than exits of outermost peripheral air holes. | 03-31-2011 |
20110094239 | Low NOx Combustor for Hydrogen-Containing Fuel and its Operation - An object of the present invention is to provide a gas turbine combustor that supports hydrogen-containing gas having a high burning velocity and is capable of performing low NOx combustion without reducing reliability of a burner. A first fuel nozzle is provided upstream of a combustion chamber and supplies fuel for activation and hydrogen-containing gas. The combustor has a primary combustion zone, a reduction zone and a secondary combustion zone. In the primary combustion zone, the fuel supplied from the first fuel nozzle is combusted under a fuel rich condition to form a burned gas containing a low concentration of oxygen. In the reduction zone, a hydrogen-containing gas is injected into the combustion chamber through a second fuel injection hole from a second fuel nozzle so that NOx generated in the primary combustion zone is reduced by an oxygen reaction of the hydrogen. In the secondary combustion zone, air for lean combustion is supplied into the combustion chamber so that unburned part of fuel is combusted under a fuel lean condition. | 04-28-2011 |
20110185703 | Gas Turbine Combustor - A gas turbine combustor includes plural multi-coaxial-injection-hole burners in which plural fuel nozzles and plural air holes provided in an air plate to correspond to the respective fuel nozzles are coaxially arranged. Each of the multi-coaxial-injection-hole burners includes a first coaxial injection burner disposed on an inner circumferential side, and a second coaxial injection burner disposed on an outer circumferential side, and a diameter of the air holes of the first coaxial injection burner is smaller than a diameter of the air holes of the second coaxial injection burner. Combustion for carrying out flame holding of a gas turbine combustor is performed by the first coaxial injection burner, and low NOx combustion of the gas turbine combustor is performed by the second coaxial injection burner. | 08-04-2011 |
20120137694 | BURNER AND GAS TURBINE COMBUSTOR - A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet. | 06-07-2012 |
20120192568 | Gas Turbine Combustor - A combustor of the prior art that defines the outlet position and direction of an air hole and suppresses adhesion of flame to an air hole outlet can reduce a discharge amount of NOx by increasing a distance over which fuel and air are mixed with each other. However, such a combustor is not sufficiently discussed for measures to suppress the occurrence of combustion oscillation resulting from the variation of a flame surface. | 08-02-2012 |
20130029277 | Combustor, Burner, and Gas Turbine - A combustor is provided that can ensure combustion stability even when operated on low BTU gas without needing any equipment for preventing back-flow of fuel gas during operation on pilot fuel. The combustor includes a first perforated plate disposed upstream of a combustion chamber, the first plate having a plurality of nozzle holes and air holes; a second perforated plate disposed on the upstream side of the first plate; and a plurality of gas nozzles each of which is inserted into corresponding nozzle holes. The gas nozzle has a leading end located inside the corresponding one of the nozzle holes. Each of the gas nozzles includes a jet hole portion having a diameter smaller than that of a gas jet hole of the gas nozzle; and a passage portion designed to form an air passage on the outer circumference of the leading end portion of the gas nozzle. | 01-31-2013 |
20130219903 | Gas Turbine Combustor and Method for Operating Same - Disclosed is a gas turbine combustor for stably burning low-BTU gases, such as blast furnace gases, that are heavily laden with CO | 08-29-2013 |