| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | Fuel injection system for a gas turbine | US10281188 | 2002-10-28 | US20040079071A1 | 2004-04-29 | Johnny Rehn; Jan Magnusson; Alf Andersson |
| A gas turbine has a fuel injection system for supplying pressurized fuel gas to a combustion chamber of a gas turbine. The fuel injection system has at least one electrically controllable magnetic valve working with pulse-width modulation, i.e., controlling the gas flow by varying the length of its opening time pulses in relation to its closing time, in a gas supply conduit. The fuel injection system has at least one electrically controllable magnetic main valve arranged in the supply conduit. Moreover, at least one pilot valve is connected to the supply conduit with its upstream end after the main valve and with its downstream end connected to a conduit leading into a pilot flame chamber inside the combustion chamber. | ||||||
| 42 | Fluidic control of fuel flow | US10348730 | 2003-01-22 | US20040020208A1 | 2004-02-05 | Peter Howard Knight |
| A fluidic apparatus for modulating the rate of fuel flow into the combustor of a gas turbine engine. The apparatus includes a fluidic oscillator device (preferably an astable fluidic oscillator, or nullflip-flopnull) having a supply inlet connected to a fluid fuel source and a pair of outlets one of which is connected to the combustor. The fluidic device operates to output fluid fuel from the outlets alternately, so modulating fuel flow into the combustor. | ||||||
| 43 | Method and device for modulation of a flame | US10308985 | 2002-12-03 | US06601393B2 | 2003-08-05 | Kenneth J. Wilson; Kenneth H. Yu; Timothy Parr; Klaus C. Schadow |
| This invention relates to air breathing engines, such as ramjets, scramjets and internal combustion, and more particularly to an active combustion control device for a combustor. In more particularity, the present invention relates to a method and apparatus that applies active combustion control technology to advanced propulsion devices and closed-loop fuel injection at sub-harmonic frequencies of the instability frequency of the combustor. The problem of limited actuator frequency response is addressed by injecting fuel pulses at sub-harmonic frequencies of the instability. The fuel may be liquid, solid or gas. To achieve this desired result, a closed loop controller is designed to determine sub-harmonic frequencies using a divider to divide the instability frequency of a combustor, yielding a fraction of the harmonic frequency. Also, this invention also combines open loop injection control with closed loop injection control to obtain enhanced engine performance, which includes extension of the stable combustion zone. | ||||||
| 44 | Process and apparatus of combustion for reduction of nitrogen oxide emissions | US10310197 | 2002-12-03 | US20030134241A1 | 2003-07-17 | Ovidiu Marin; Erwin Penfornis; Yves Bourhis; Benjamin Bugeat |
| A combustion control system allows the dramatic reduction of NOx emission levels from industrial combustion processes without having recourse to expensive flue gas clean up methods. The system combines the technique of oscillating combustion with an adapted system for post combustion burn out of the excess of CO resulting from the low-NOx combustion zone. A process for fuel combustion includes generating an oscillating combustion zone by oscillating at least one of the fuel flow and the oxidant flow to achieve a reduced nitrogen oxide emission, selecting oscillating parameters and furnace operating parameters to maximize nitrogen oxide reduction efficiency to the detriment of carbon monoxide production, and combusting carbon monoxide downstream of the oscillating combustion zone by injecting a post combustion oxidant. | ||||||
| 45 | Method and device for modulation of a flame | US09853930 | 2001-05-07 | US06530228B2 | 2003-03-11 | Kenneth J. Wilson; Kenneth H. Yu; Timothy Parr; Klaus C. Schadow |
| This invention relates to air breathing engines, such as ramjets, scramjets and internal combustion, and more particularly to an active combustion control device for a combustor. In more particularity, the present invention relates to a method and apparatus that applies active combustion control technology to advanced propulsion devices and closed-loop fuel injection at sub-harmonic frequencies of the instability frequency of the combustor. The problem of limited actuator frequency response is addressed by injecting fuel pulses at sub-harmonic frequencies of the instability. The fuel may be liquid, solid or gas. To achieve this desired result, a closed loop controller is designed to determine sub-harmonic frequencies using a divider to divide the instability frequency of a combustor, yielding a fraction of the harmonic frequency. Also, this invention also combines open loop injection control with closed loop injection control to obtain enhanced engine performance, which includes extension of the stable combustion zone. | ||||||
| 46 | Heating device | US09424228 | 1999-11-26 | US06364212B1 | 2002-04-02 | Fritz Widemann |
| The invention relates to a heating device, especially for a motor vehicle, with a burner, to which fuel is supplied from a tank via a fuel line by means of a pump, especially a piston pump, and with an electronically controllable valve means which is inserted into the fuel line and which can be controlled by a control means. To ensure problem-free feed of fuel to the burner independently of the pump pressure, a pressure reservoir is assigned to the valve means, fuel being delivered by means of the pump controlled in a clocked manner by the control unit, to the pressure reservoir and from the latter to the burner, without the action of the pump. | ||||||
| 47 | 개선된 유동 레귤레이터를 갖는 트랩 | KR1020057022568 | 2004-05-12 | KR1020060027798A | 2006-03-28 | 듀랜드엠마에이; 팔롬보마이클제이 |
| The present application discloses a flying insect trapping device (10) configured to be used with a fuel supply (12) containing combustible fuel. One aspect of the invention provides a fuel regulator (110) for controlling fuel flow in intermittent pulses and another aspect provides a valve (8) for enabling flushing of the combustion device. | ||||||
| 48 | 폐기물을 고온에서 가스화시키기 위한 산소 랜스, 및이것의 작동 방법 | KR1020030071355 | 2003-10-14 | KR1020040034444A | 2004-04-28 | 키스,귄터하. |
| PURPOSE: An oxygen lens and an operating method thereof are provided to effectively prevent the diffusion of hot synthetic gas into an oxygen supply line by selecting the oxygen pressure over a partial pressure inside a high temperature reactor when operating only by burner flames. CONSTITUTION: A channel for carrying reaction oxygen is same as a channel for supplying combustion gas(II). A controller controls the supplied oxygen amount in a different inflow status. The controller contains valves to be connected with an oxygen flow in parallel. A changeable burner tip(1) is installed in the side of a reactant outlet. The burner tip is fixed by a plug-in or screw connections(31,32). Channels(I,II) are extended concentrically while locating one channel inside the other channel. Coolant channels(4,5) are installed additionally. Thereby, the diffusion of hot synthetic gas into the oxygen channel is prevented. Moreover, the explosion when the oxygen supply is restarted into a gasification layer of a reactor and the condensation of the hot synthetic gas inside the reaction oxygen supply channel are prevented. | ||||||
| 49 | System and method for attenuating combustion oscillations in a gas turbine engine | US11506328 | 2006-08-18 | US08024934B2 | 2011-09-27 | Mario E. Abreu; Gwenn A. Peters; Terry R. Tarver; Chris Z. Twardochleb; James W. Blust |
| A system and method for modifying the supply of fuel to injectors to attenuate combustion oscillations in a gas turbine engine. The gas turbine engine may comprise a combustor, a plurality of injectors and a manifold. The plurality of injectors may be operable to provide fuel to the combustor. The manifold may be configured to supply fuel to all of the plurality of injectors or to only a portion of the plurality of injectors in reaction to a determination of an existence of combustion oscillations. | ||||||
| 50 | Method for Heating an Industrial Furnace, and Apparatus Suitable for Carrying Out the Method | US11813759 | 2006-01-06 | US20080292999A1 | 2008-11-27 | Horst Koder; Burkhard Muller |
| In a known method for heating an industrial furnace by pulsating combustion, gaseous or liquid reactants, comprising an oxidizing agent and fuel, are fed to a burner (3), with the volumetric flow of at least one of the reactants which emerges from the burner mouth (7) being changed over the course of time. On this basis, to provide a method which allows a simple and flexible change to the flow during pulsating combustion, according to the invention it is proposed that the change in the volumetric flow of the reactant over the course of time is generated by electrical actuation imparting deflections to at least one membrane (14) in a membrane space (13) which is connected upstream of the burner mouth (3) and is accessible to the reactant, which deflections cause changes to the volume of the membrane space. A low maintenance apparatus of simple design which is suitable for carrying out the method is distinguished by the fact that the device for varying the volumetric flow over the course of time comprises at least one membrane (14), which is arranged in a membrane space (13) that is connected upstream of the burner (3) and is accessible to the reactant, and on which deflections can be imposed by means of an electrical actuation, which deflections cause a change in the volume of the membrane space (13). | ||||||
| 51 | Adiabatic power generating system | US11105130 | 2005-04-12 | US07134285B2 | 2006-11-14 | Indru J. Primlani |
| An adiabatic power generation method and apparatus includes at least one combusting device to combust any suitable fuel and an oxygen-containing gas to produce hot high pressure combustion gases. Also includes modified present art combustors, wind and solar energy sources. A portion of the expanded gases, or ambient air is mixed with the combustion gases to form a mixture of gases as working fluid that is fed to a work-producing device. | ||||||
| 52 | Fluidic control of fuel flow | US10348730 | 2003-01-22 | US06895758B2 | 2005-05-24 | Peter Howard Knight |
| A fluidic apparatus for modulating the rate of fuel flow into the combustor of a gas turbine engine. The apparatus includes a fluidic oscillator device (preferably an astable fluidic oscillator, or “flip-flop”) having a supply inlet connected to a fluid fuel source and a pair of outlets one of which is connected to the combustor. The fluidic device operates to output fluid fuel from the outlets alternately, so modulating fuel flow into the combustor. | ||||||
| 53 | Method and device for affecting thermoacoustic oscillations in combustion systems | US10725562 | 2003-12-03 | US20050019713A1 | 2005-01-27 | Ephraim Gutmark; Christian Paschereit |
| The present invention relates to a method and a device for affecting thermoacoustic oscillations in a combustion system (1) comprising at least one burner (2) and at least one combustor (3), modulated injection of fuel being carried out. In order to improve the action of affecting the thermoacoustic oscillations, the modulated injection of the fuel is carried out into a recirculation zone (7) which forms in the combustor (3). | ||||||
| 54 | Evaporative burner | US10775035 | 2004-02-09 | US20040177611A1 | 2004-09-16 | Christopher C. Langenfeld; Ryan Keith LaRocque; Angus A. MacEachern; Michael G. Norris |
| An evaporative burner that includes an igniter assembly, a swirler, an evaporation chamber, and a reverse throat. The reverse throat has raised ends that protrude into the evaporation chamber. The reverse throat in combination with the evaporation chamber and the swirler, facilitate the recirculation of air in the evaporation chamber such that a flame is stabilized near the evaporation chamber walls. This flame gradually evaporates the fuel in the lining of the evaporation chamber. The fuel-air mixture results in a steady and uniformly distributed flame in the combustion chamber. This flame can heat uniformly the walls of the combustion chamber, and thus be applicable for high efficiency and low emissions applications. Furthermore, this burner can start and reach full burner power rapidly. | ||||||
| 55 | Metering fuel pump | US10643147 | 2003-08-18 | US20040033140A1 | 2004-02-19 | Eric R. Jensen; Christopher C. Langenfeld; Scott W. Newell; Michael Norris; Jeffrey D. Renk; Andrew Schnellinger |
| A device and method for controlling the flow of a gaseous fuel from a fuel supply to a pressurized combustion chamber. A fuel pump is included in the gas train from supply to chamber. The fuel pump increases the pressure of the gas to allow efficient injection into the chamber. The pump is modulated to control the fuel flow. Both alternating current and pulse-width-modulated direct current signals may be used to control the flow. The pump may be a piston pump or a diaphragm pump. Feedback may be provided from sensors that determine operating parameters of the engine and such sensor signals may be used by the controller to maintain a parameter, such as temperature, at a specified value. An acoustic filter can be included in the gas train to significantly reduce gas flow pulsations generated by the pump. This filter improves the uniformity of the combustion process. | ||||||
| 56 | Method and device for the control of thermoacoustic instabilities or oscillations in a combustion system | US10397216 | 2003-03-27 | US20030211432A1 | 2003-11-13 | Ephraim J. Gutmark; Christian Oliver Paschereit |
| In a method for the control of thermoacoustic instabilities or oscillations in a combustion system (15), pressure oscillations and/or heat release oscillations in the combustion system (15), which are linked to the thermoacoustic instabilities, are measured, the resulting measurement signal is filtered, time-delayed and amplified, and, according to the filtered, delayed and amplified measurement signal, the fuel stream to or the combustion air for the combustion system (15) is modulated. In such a method, the use of more cost-effective modulation devices is achieved in that modulation takes place at a subharmonic of a dominant instability frequency in the combustion system (15). | ||||||
| 57 | Fuel injection control system for a turbine engine | US10059501 | 2002-01-29 | US20030140614A1 | 2003-07-31 | Charles F. Nearhoof SR.; Charles F. Nearhoof JR.; Kevin P. Pearce |
| This invention is a fuel injection control system for a turbine engine. The invention uses at least one fuel injector, having means for injecting fuel in pulses to the combustion chamber of a turbine engine, and an electronic control unit to receive and interpret input sensor signals from selected operating functions of the engine and to generate and direct fuel injection signals to modify the pulse duration and/or frequency of fuel injection in response to a deviation from a selected operating function, such as the desired operating speed, caused by variable operating loads encountered by the turbine engine. This configuration provides significantly greater fuel efficiency, better operational control and response time, and a lighter weight than is currently available in turbine engines. The invention may be used in many applications such as commercial, private, experimental and military aviation, power plant turbines, and other industrial, military and mining applications. | ||||||
| 58 | Method and device for modulation of a flame | US09853930 | 2001-05-07 | US20020162334A1 | 2002-11-07 | Kenneth J. Wilson; Kenneth H. Yu; Timothy Parr; Klaus C. Schadow |
| This invention relates to air breathing engines, such as ramjets, scramjets and internal combustion, and more particularly to an active combustion control device for a combustor. In more particularity, the present invention relates to a method and apparatus that applies active combustion control technology to advanced propulsion devices and closed-loop fuel injection at sub-harmonic frequencies of the instability frequency of the combustor. The problem of limited actuator frequency response is addressed by injecting fuel pulses at sub-harmonic frequencies of the instability. The fuel may be liquid, solid or gas. To achieve this desired result, a closed loop controller is designed to determine sub-harmonic frequencies using a divider to divide the instability frequency of a combustor, yielding a fraction of the harmonic frequency. Also, this invention also combines open loop injection control with closed loop injection control to obtain enhanced engine performance, which includes extension of the stable combustion zone. | ||||||
| 59 | Combustion device | US09506035 | 2000-02-17 | US06402505B1 | 2002-06-11 | Hiroshi Okada; Kiyoshi Kawaguchi |
| In a combustion unit, a fuel collision member is disposed between a fuel injection valve and a combustion chamber. The fuel collision member is positioned so that, a part of fuel injected from said fuel injection valve is introduced into the combustion chamber while colliding with the fuel collision member, and the other part of fuel is directly introduced into the combustion chamber without colliding with the fuel collision member. Thus, fuel introduced into the combustion chamber is atomized while being introduced into the combustion chamber in a wide range. | ||||||
| 60 | Proportional combustion control device | US774534 | 1991-10-08 | US5158261A | 1992-10-27 | Yukuo Morohoshi |
| A proportional combustion control device for supplying fuel to a combustor for a boiler, a hot water maker, etc., comprising an opening and closing valve for controlling a supply of fuel provided in the midst of a fuel supply pipe, and a control valve having a spindle whose needle portion at the extreme end is moved in and out of a nozzle and an exciting coil to generate a drive force for intermittently and axially moving said spindle against the restoring force by being supplied with a drive pulse, wherein even if fuel is either oil or gas, proportional control of combustion can be made, and the spindle is intermittently moved in the range capable of continuously carrying out combustion to open and close the nozzle whereby jetting of fuel is subjected to proportional control at the turndown ratio of 1/5 to 1/10 to always render the stabilized combustion possible. | ||||||
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