Patent application number | Description | Published |
20080268387 | COMBUSTION EQUIPMENT AND BURNER COMBUSTION METHOD - Combustion equipment of a coaxial jet combustion scheme is provided that includes: a burner plate in which fuel and air are mixed with each other while the fuel and air pass through an air hole; a burner plate extension which is a portion of the burner plate and extends toward a combustion chamber side spaced apart from the air hole; and a protrusion disposed on the combustion chamber side of the burner plate extension so as to protrude in a direction where flow of the fuel moves. In the combustion equipment, a gap between opposite portions of the protrusion is greater than a diameter of the air hole and a flame source forming area is defined between the burner plate, the burner plate extension and the protrusion. The combustion equipment of a coaxial jet combustion scheme can achieve a further reduction in NOx emissions. | 10-30-2008 |
20090031728 | COMBUSTOR AND A FUEL SUPPLY METHOD FOR THE COMBUSTOR - A combustor includes a chamber mixing and burning fuel and air and an air hole plate disposed on a wall surface of the chamber. The air hole plate includes a plurality of rows disposed concentrically of a plurality of air holes jetting coaxial jets of fuel and air into the chamber. A first fuel nozzle and a second fuel nozzle are disposed near a fuel hole for jetting fuel into an air hole row on an inner peripheral side. The first fuel nozzle is structured to suppress turbulence of surrounding air flow and the second fuel nozzle is structured to promote turbulence of a surrounding air flow. | 02-05-2009 |
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 |
20090293484 | GAS TURBINE COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO THE SAME - A fuel flow path and a flow path of air for combustion are disposed coaxially to create a coaxial jet such that a fuel flow is embraced by an air flow. A large number of such fuel flow paths and air flow paths are arranged in a wall surface of a combustion chamber to create coaxial nozzle jets. Some of the flow paths of air for combustion are arranged inclinedly so as to create rotation for the stabilization of combustion and straight portions not having an inclination angle are added respectively to upstream ends of such inclined air flow paths. Fuel is jetted toward or within the straight portions. | 12-03-2009 |
20100180604 | METHOD FOR STARTING PREMIXED COMBUSTION IN COMBUSTOR FOR TWO-SHAFT GAS TURBINE - A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out. | 07-22-2010 |
20110167833 | METHOD FOR STARTING PREMIXED COMBUSTION IN COMBUSTOR FOR TWO-SHAFT GAS TURBINE - A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out. | 07-14-2011 |
20120017600 | Combustor Control Method and Combustor Controller - Provided are a combustor control method and a combustor controller capable of calculating the combustion air flow and the fuel flow in multi-shafts gas turbine with high precision and without the need of performing complicated calculations and thereby calculating a fuel-air ratio necessary for stable combustion control. The multi-shaft gas turbine is made up of a gas generator turbine and a power turbine. Combustors includes a diffusive combustion units and a plurality of premixed combustion units. An ignition/extinction control unit of the combustor control device calculates the combustion air flow supplied to the combustors based on the open position of compressor inlet guide vanes attached to the gas generator turbine, revolution speed of the gas generator turbine and compressor inlet temperature, calculates the flow of fuel supplied to the combustors based on revolution speed of the power turbine, and calculates the fuel-air ratio in real time as flame reference based on the calculated combustion air flow and fuel flow. | 01-26-2012 |
20120094239 | COMBUSTOR AND A FUEL SUPPLY METHOD FOR THE COMBUSTOR - A combustor includes a chamber mixing and burning fuel and air and an air hole plate disposed on a wall surface of the chamber. The air hole plate includes a plurality of rows disposed concentrically of a plurality of air holes jetting coaxial jets of fuel and air into the chamber. A first fuel nozzle and a second fuel nozzle are disposed near a fuel hole for jetting fuel into an air hole row on an inner peripheral side. The first fuel nozzle is structured to suppress turbulence of surrounding air flow and the second fuel nozzle is structured to promote turbulence of a surrounding air flow. In accordance with the aspect of the present invention, good flame stability can be maintained while further reducing NOx in a combustor using coaxial jets. | 04-19-2012 |
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 |