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 |
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 |
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 |
20130139517 | Solar Assisted Gas Turbine System - This invention is intended to provide a solar assisted gas turbine system significantly reduced in the number of heat collectors and downsized in heat collector installation site area requirement. | 06-06-2013 |
20130174549 | Gas Turbine System, Control Device for Gas Turbine System, and Control Method for Gas Turbine System - Provided is a gas turbine system capable of dealing with a request for output increase even when high-pressure hot water generated using solar thermal energy cannot be used according to the operating state of the gas turbine system. A gas turbine system which sucks in intake air from an air intake duct by a compressor and drives a gas turbine by combustion gas obtained by burning air and fuel by a combustor, said gas turbine system being provided with pipes for generating high-pressure hot water by providing a solar collecting tube that utilizes solar heat and spraying the high-pressure hot water into the intake air sucked in by the compressor, and pipes for spraying normal temperature water into the intake air sucked in by the compressor. | 07-11-2013 |
20140033720 | Controller for Gas Turbine Power Plant - A controller for use in a gas turbine power plant includes a compressor that compresses combustion air; a water-atomization cooling apparatus that sprays water drops of atomized water supplied via a water-atomization flow-rate regulating valve over a flow of air drawn in the compressor; a combustor that mixes the compressed combustion air with fuel to thereby burn a fuel-air mixture and generate combustion gas at high temperature and performs combustion switching during operation; a turbine that uses the combustion gas to drive the compressor and a generator; the water-atomization flow-rate regulating valve that controls a flow rate of the atomized water; and a compressor inlet inner blade that controls a flow rate of air drawn in the compressor. The controller includes control means that calculates a fuel-air ratio correction command signal for compensating for reduction in a fuel-air ratio in the combustor occurring during the combustion switching. | 02-06-2014 |
20140034752 | Atomizer - In an atomizer constructed to cool inlet air for a gas turbine by spraying fine droplets of water into the inlet air, a spray nozzle is disposed to spray the finely atomized droplets of water from an outer edge of an atomized airstream into a high-speed zone thereof, towards a central region of the airstream. The atomized airstream meets an airstream of a low-speed zone formed at a downstream side, and after the two kinds of airstreams have been mixed and unified, this mixture is supplied to an axisymmetric compressor. Devices such as a feed water pipe and spray nozzle are placed in the low-speed zone so as not to obstruct the airstream. | 02-06-2014 |