CN101025272A - Multi-stage efficient enzironment-protection turbine gas-fuel staged burning method and system - Google Patents
Multi-stage efficient enzironment-protection turbine gas-fuel staged burning method and system Download PDFInfo
- Publication number
- CN101025272A CN101025272A CN 200710017424 CN200710017424A CN101025272A CN 101025272 A CN101025272 A CN 101025272A CN 200710017424 CN200710017424 CN 200710017424 CN 200710017424 A CN200710017424 A CN 200710017424A CN 101025272 A CN101025272 A CN 101025272A
- Authority
- CN
- China
- Prior art keywords
- gas
- stage
- fuel
- combustion chamber
- burning
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention discloses a gas fuel classifying burning method and the device of the multilevel highly active combustion turbine which divides the gas fuel burning into many grades. All of the high pressure fuel gas is transformed into the first burning room and passed the every next combustion turbines and the burning room. The oxidant is transformed into all the burning room before last grade. The oxidant reacts with the part fuel to emit the thermal to keep the temperature under some special temperature; in the last burning room, the oxidant burns with the fuel fully and then it is transformed into the last combustion turbine to do power. So it has the high generating efficiency and good environment protecting, especially for the multiple production system based on the coal gas, the gas steam compound circle system and the using system of the natural gas, the coke-oven gas, the blast furnace gas, the converter gas and the coal layer gas.
Description
Technical field
Content of the present invention belongs to the power-equipment field, relates to the gas turbine generating set that comprises gas fuel combustion, in particular for improving the device of heavy duty gas turbine power generation efficient and the pollutant emission of reduction heavy duty gas turbine power generation.Specifically, the present invention relates to a kind of like this multi-stage efficient enzironment-protection turbine gas-fuel staged burning method and system, in this gas turbine cycle system, combustion chambers at different levels are sent in oxidant (air, oxygen-enriched air or oxygen) classification, fuel gas is oxidation or burning step by step, enters gas turbine actings at different levels respectively.To afterbody, combustable gas concentration and pressure reduce step by step from the first order.
Background technology
A gas-turbine installation the simplest comprises a compressor, a combustion chamber and a turbine.With a fuel mix, this mixture burns in the combustion chamber after the compression of compressor of inhaled air process, and the flue gas that is generated flows into turbine, by turbine the portion of energy in the flue gas is converted into mechanical energy.
The delivery temperature of simple cycle gas turbine engine up to 450 ℃～600 ℃, if in gas turbine, install regenerator additional, utilize this high-temperature exhaust air to heat the air of blower outlet, improve the temperature that it enters the combustion chamber, can reduce the fuel quantity that adds in the combustion chamber, thereby improved the thermal efficiency, backheat that Here it is circulation.Because the volume and the size of regenerator are bigger, equipment investment and operating cost are higher, and along with combustion gas-Steam Combined Cycle technology rapid development, the circulation of practical application backheat is actually rare in large-scale gas turbine at present.
In gas compression processes, gas can heat up and cause the compressor power consumption to increase.Therefore in compression process, working medium caused the cooler cooling after, return continue in the compressor compression in the middle of cooling, the process that gradually reduces, cold circulation between this is called.In theory, a cold number of times is for a long time infinite, and compression process just becomes isotherm compression, and the compression wasted work is reduced to minimum, and the recycle ratio merit increases at most.
In the middle of expansion process, working medium led in the reheat combustion chamber heating after, return and continue in the combustion gas turbine to expand to finish expansion process, this is called thermal cycle again.In theory, hot again number of times is for a long time infinite, and the expansion process in the gas turbine just becomes isothermal expansion, and it is maximum that expansion work reaches, and the recycle ratio merit increases at most.In fact, infinite repeatedly between cold circulation and infinite repeatedly again thermal cycle do not accomplish.
The requirement of law and environment aspect has been taked strict restriction to nitrogen oxide (NOx) discharge capacity of TRT.Usually, in gas turbine, require the combustion chamber lower ignition temperature to be arranged to reduce nitrogen oxide (NOx) discharge capacity.Prior art adopts quite extreme measure to reduce the discharging of nitrogen oxide.For example, conventional way is to adding excessive air, water or steam in the gas-turbine combustion chamber to reduce reaction temperature wherein.Though this method is being that part is effective aspect the reduction ignition temperature at least, but the use of too much air, water or steam has increased the complexity of the suitable quantity delivered in metering combustion chamber and has reduced efficiency of combustion, and increased available loss of energy, thereby the generating efficiency that has limited whole gas turbine cycle improves.
Another kind of possible method is the way of catalytic combustion, uses a kind of catalyst can carry out under than the lower concentration of conventional possibility situation to impel burning.But generally speaking, catalyst is very expensive, and the technology that relies on them to obtain effective complete reaction is very complicated.The final discharging that scr reactor reduces NOx is installed in waste heat boiler besides.
Existing gas-turbine installation is typically equipped with composite chamber, but the burner level of a plurality of parallel runnings is arranged on it, and these burner levels can single operation or cooperation according to the loading condition of gas-turbine installation.Chinese patent application (application number: 200480028655.4) mentioned a kind of employing before burning fuel gas and the air premix method of getting up accurately, thereby make burning under lower temperature, carry out making the discharge capacity reduction of nitrogen oxide and carbon monoxide.Chinese patent application (application number: 97120031.9) proposed a kind of gas turbine, belonged to the thermal cycle again of a kind of routine recited above, promptly in secondary combustion chamber, sprayed into fuel with sequential combustion.The multistage combustion of above-mentioned all technology indoor burning remains to be carried out under the condition of poor fuel, does not clearly propose the said fractional combustion of the present invention but on the whole.
Above-mentioned gas turbine cycle and existing thermal cycle weak point again are: fuel (perhaps fuel is with oxidant) sprays into completing combustion under the level pressure in the reheat combustion chamber; The burning that is characterized in fuel is to carry out under the oxidizing atmosphere of oxidizing atmosphere even high excess of oxygen, therefore has to reduce the NOx discharging by reducing ignition temperature.And, must limit the raising of whole gas-turbine installation efficient because the temperature of burning reduces.
Summary of the invention
Defective or deficiency at the existence of above-mentioned background technology, the objective of the invention is to, a kind of multi-stage efficient enzironment-protection turbine gas-fuel staged burning method that can reduce the NOx discharging and realize the high efficiency generating is provided, and has produced the gas turbine cycle system of multistage combustion by this method.
In order to realize above-mentioned task, the present invention takes following technical solution:
A kind of multi-stage efficient enzironment-protection turbine gas-fuel staged burning method, it is characterized in that, the completing combustion of fuel gas is divided into some levels, being about to all high-pressure fuel gas all sends into the first-stage burning chamber and passes through subsequent stages gas turbine and combustion chamber successively, the gas turbine cycle that is suitable for all kinds of high-pressure fuel gas, especially the gas turbine cycle that is fit to the HTHP fuel gas that the gasification furnace of high pressure discharges, and can dispose compressor and regenerator in addition with its increasing temperature and pressure for other lower gaseous fuels of temperature and pressure; In the end send into a certain amount of oxidant respectively in the institute's combuster before the one-level, atmosphere in the control combustion chamber is reducing atmosphere and makes it to reach a certain specific temperature, usually may be selected to be the maximum temperature that combustion gas turbine can bear, thereby avoided the generation of NOx, and high available energy utilization ratio has been arranged; Indoor in final-stage combustion, the oxidant that replenishes enough stoichiometric proportions is sent into the acting of final stage gas turbine after finishing whole fuel gas burnings and making it to reach a certain particular temperature value.
Described oxidant is air, oxygen-enriched air or oxygen, oxidant and fuel tolerance have the stoichiometric ratio that departs from of control, guarantee that fuel and oxidant burn in each grade combustion chamber under reducing atmosphere, be fuel gas oxidation or burning step by step, every grade of gas turbine is only finished the burning of part of fuel gas, enter the gas turbine acting of this one-level then, in the final-stage combustion chamber, the oxidant that replenishes enough stoichiometric proportions is finished the burning of whole fuel gas, enters the acting of final stage gas turbine.
Realize the multi-stage efficient enzironment-protection turbine gas-fuel staged burning system of said method, it is characterized in that this system comprises:
Multistage compressor, be used for implements spatial scalable compression and classification and supply with oxidant, on the one-level compressor oxidant inlet is arranged, compressor is divided into some levels by the pressure and the flow of the required oxidant of corresponding gas turbine combustion, between compressor is at different levels inter cooler is set, also inter cooler can be set; Compressed Gas not at the same level is sent into respectively in the corresponding combustion chamber according to pressure, supplies with the required oxidant of burning of fuel gas, also can be provided with exhaust heat heated oxidant regenerator, and the waste heat of combustion turbine exhaustion is transmitted back to combustion chambers at different levels; Compressor can be driven or be driven separately by combustion gas turbine.
Multistage gas turbine, it is driven by the high-temperature high-pressure fuel gas from the combustion chamber of this grade, is used to drive generator for electricity generation, and can drives compressor work;
Composite chamber is used for fractional combustion fuel gas, so that generate high-temperature fuel gas, its first-stage burning chamber is connected between final stage compressor and the first order gas turbine; Other grade combustion chamber is arranged between the two-stage gas turbine, and the high-pressure gas import is arranged on the first-stage burning chamber, and the exhaust of previous stage gas turbine is as the fuel of next stage combustion chamber;
Air, oxygen-enriched air or pure oxygen enter the one-level compressor by oxidant inlet, after being compressed to certain pressure, a part is sent into the burning needs of final-stage combustion chamber for fuel gas, enter two-stage compressor behind the remainder process one-level inter cooler and further be compressed to more high pressure, and then telling a part, to send into the penultimate stage combustion chamber required for fuel gas burning, enter three grades of compressors behind the remainder process secondary inter cooler and further be compressed to more high pressure, after some levels, further send into of the burning of one-level combustion chamber again after the compression for fuel gas until entering the final stage compressor;
Having the high-pressure fuel gas of uniform temperature to enter the one-level combustion chamber by the high-pressure gas import mixes with the oxidant that the final stage compressor is sent here, the gas that generates HTHP after the partial combustion enters one-level gas turbine expansion acting, pressure and temperature is reduced to and enters that secondary combustion chamber is mixed with the supplemental oxidant that the penultimate stage compressor is sent here and partial combustion behind the certain value, the gas that generates high temperature and certain pressure enters second gas burning turbine expansion acting, after some levels, enter the final-stage combustion chamber until the gas decrease temperature and pressure behind certain value, the make-up gas of sending into the one-level compressor is finished burning and is entered the acting of final stage gas turbine and discharge through air exit then.
In addition, final-stage combustion chamber and final stage gas turbine also can or be annotated the vapour gas turbine and form by the gas turbine of the burning gaseous fuel of routine.If any special requirement, final-stage combustion chamber and final stage gas turbine can not adopt, and with the direct exhaust of previous stage gas turbine, thereby increased the staged-combustion method of this gas fuel of gas turbine and the flexibility of system's design.
The gas turbine cycle system of method of the present invention and multistage combustion thereof can improve the generating efficiency of gas turbine cycle and reduce the discharging of NOx.
Description of drawings
Fig. 1 is the schematic diagram of an embodiment of the multi-stage efficient enzironment-protection turbine gas-fuel staged burning system that realizes of the inventive method, is a coaxial gas turbine engine systems of efficient and environment-friendly type that is divided into three grades of burnings.The fractional combustion efficient and environment-friendly type gas turbine of other progression (comprising secondary) also within the scope of the invention.Label among the figure is represented respectively: 1, oxidant inlet, 2, the one-level compressor, 3, two-stage compressor, 4, the final stage compressor, 5, the one-level gas turbine, 6, the second gas burning turbine, 7, the final stage gas turbine, 8, the one-level inter cooler, 9, the secondary inter cooler, 10, the high-pressure gas import, 11, the one-level combustion chamber, 12, secondary combustion chamber, 13, the final-stage combustion chamber, 14, secondary combustion chamber's oxygenating control valve, 15, final-stage combustion chamber oxygenating control valve, 16, air exit, 17, generator, 18, one-level combustion chamber regenerator, 19, secondary combustion chamber's regenerator, 20, final-stage combustion chamber regenerator.
An example that provides by accompanying drawing and inventor further describes in detail other features of the present invention, characteristic and advantage below.
The specific embodiment
The multi-stage efficient enzironment-protection turbine gas-fuel staged burning system that method of the present invention realizes, combustion chamber and gas turbine are divided into two-stage at least, high-pressure fuel gas all enters gas turbine by the first-stage burning chamber, and the exhaust of previous stage gas turbine is as the fuel of next stage combustion chamber; In the combustion chamber before final stage, send into a certain amount of oxidant respectively, oxidant can be air, oxygen-enriched air or oxygen, oxidant and fuel tolerance have the stoichiometric ratio that departs from of control, guarantee that fuel and oxidant burn in each grade combustion chamber under reducing atmosphere, and make the heat of sending into oxidant and the release of part of fuel solid/liquid/gas reactions cause fuel gas to be warming up to specific high temperature, this high temperature is generally the highest bearing temperature of gas turbine, be fuel gas oxidation or burning step by step, every grade of gas turbine is only finished the burning of part of fuel gas, enter the gas turbine acting of this one-level then, obviously the atmosphere of reproducibility is with the generation of effective contaminant restraining; In the final-stage combustion chamber, the oxidant that replenishes enough stoichiometric proportions is finished the burning of whole fuel gas, enters the acting of final stage gas turbine.The grading combustion technology that oxidant classification that Here it is is sent into can find out clearly that this gas turbine cycle does not have the blending of excessive air, water or steam, therefore can improve the utilization ratio of available energy.
Compressor is divided into some levels by the pressure and the flow of the required oxidant of corresponding gas turbine combustion, between compressor is at different levels inter cooler can be set; Because Compressed Gas not at the same level is sent into respectively in the corresponding combustion chamber according to pressure, supply with the required oxidant of burning of fuel gas, not all oxidant all is compressed to maximum pressure, and this can effectively reduce the power consumption of compressor, improves the net efficiency of gas turbine.
Final-stage combustion chamber and final stage gas turbine are made up of the gas turbine or the notes vapour gas turbine of the burning gaseous fuel of routine, final-stage combustion chamber and final stage gas turbine perhaps are not set, by the direct exhaust of previous stage gas turbine.
Also also be provided with regenerator before the combustion chambers at different levels as required, be used for the waste heat heated oxidant of gas turbine is sent into the combustion chamber again.
Multi-stage efficient enzironment-protection turbine gas-fuel staged burning of the present invention system can also become a kind of gas turbine that can improve efficiency of plant.
Supplemental oxidant method for determination of amount in the combustion chamber at different levels of the present invention, make and only finish the partial combustion process in every grade of combustion chamber of this system, thereby control burning back generates the temperature of flue gas at particular value, usually may be selected to be the maximum temperature that gas turbine can bear, to realize efficient low NOx combustion and high cycle efficieny.
Referring to Fig. 1, multi-stage efficient enzironment-protection turbine gas-fuel staged burning of the present invention system, comprise: multistage compressor, it is used for implements spatial scalable compression and oxidant (air, oxygen-enriched air or oxygen) is supplied with in classification, between compressor is at different levels inter cooler can be set, improve clean generating efficiency to reduce the compressor power consumption; Composite chamber, it is used for fractional combustion fuel gas, so that generate high-temperature fuel gas; Multistage gas turbine, it is driven by the high-temperature high-pressure fuel gas from the combustion chamber of this grade; Connect pipeline of compressor outlets at different levels, combustion chamber at different levels and gas turbines at different levels or the like.Can produce on 1400 ℃ of ranks such as 1350 ℃～1650 ℃ in the described combustion chamber or the combustion gas of higher temperature.The temperature of combustion gas is high more, and the power of gas turbine output is just big more.
Multi-stage efficient enzironment-protection turbine gas-fuel staged burning systemic circulation of the present invention is as follows:
Air, oxygen-enriched air or pure oxygen enter one-level compressor 2 by oxidant inlet 1, after being compressed to certain pressure, a part is sent into the burning needs of final-stage combustion chamber 13 for fuel gas, enter two-stage compressor 3 behind the remainder process one-level inter cooler 8 and further be compressed to more high pressure, and then telling a part, to send into secondary combustion chamber 12 required for the fuel gas burning, and remainder enters the final stage compressor after through secondary inter cooler 9 and further sends into the burning of one-level combustion chamber 11 for fuel gas again after the compression.
Having the high-pressure fuel gas of uniform temperature to enter one-level combustion chamber 11 by high-pressure gas import 10 mixes with the oxidant that final stage compressor 4 is sent here, the gas that generates HTHP after the partial combustion enters the 5 expansion actings of one-level gas turbine, pressure and temperature is reduced to and enters that secondary combustion chamber 12 is mixed with the supplemental oxidant that two-stage compressor 3 is sent here and partial combustion behind the certain value, the gas that generates high temperature and certain pressure enters the 6 expansion actings of second gas burning turbine, the gas decrease temperature and pressure enters final-stage combustion chamber 13 behind certain value, the make-up gas of sending into one-level compressor 2 is finished burning and entered 7 actings of final stage gas turbine and discharge gas-turbine installations through air exit 16 then.The compressor 2,3,4 of three levels and generator 17 are driven by the gas turbine 5,6,7 of three levels.Regenerator 18,19,20 is respectively by extracting the part heated oxidant to certain high temperature from exhaust.
Secondary combustion chamber's oxygenating control valve 14 among the figure, final-stage combustion chamber oxygenating control valve 15 can be used to regulate respectively the supplemental oxidant amount that enters combustion chambers at different levels, finishes regulating action to a certain degree.
Provide the s main working parameters of the example reference in the accompanying drawing below:
High pressure gas suction parameter: volume content 46%CO, 54%CO
2, pressure 12.25MPa, 600 ℃ of temperature, flow Q NM
3/ min;
Air is sent in the one-level combustion chamber: pressure 12.25MPa, 600 ℃ of temperature, flow 0.41Q Nm
3/ min;
One-level gas turbine pressure ratio 3.5, intake air temperature: 1400 ℃, delivery temperature: 950 ℃;
Secondary combustion chamber sends into air: pressure 3.5MPa, 600 ℃ of temperature, flow 0.32Q Nm
3/ min;
Second gas burning turbine pressure ratio 3.5, intake air temperature: 1400 ℃, delivery temperature: 950 ℃.
Air is sent in three grades of combustion chambers: pressure 1.0MPa, 600 ℃ of temperature, flow 0.37Q Nm
3/ min.
Final stage gas turbine pressure ratio 10, intake air temperature: 1400 ℃, 667 ℃ of delivery temperatures.
Exhaust 16: pressure 0.1MPa, flow 1.86Q Nm
3/ min.
The pressure ratio of one-level compressor 2: 10, air mass flow 1.1Q Nm
3/ min.
The pressure ratio of two-stage compressor 3: 3.5, air mass flow 0.73Q Nm
3/ min.
The pressure ratio of final stage compressor 4: 3.5, air mass flow 0.41Q Nm
3/ min.
Claims (8)
1. multi-stage efficient enzironment-protection turbine gas-fuel staged burning method, it is characterized in that, the completing combustion of fuel gas is divided into some levels, being about to all high-pressure fuel gas all sends into the first-stage burning chamber and passes through subsequent stages gas turbine and combustion chamber successively, in the end send into a certain amount of oxidant respectively in the institute's combuster before the one-level, atmosphere in the control combustion chamber is reducing atmosphere and makes the heat of sending into oxidant and the release of part of fuel solid/liquid/gas reactions cause fuel gas to be warming up to specific high temperature that generally this temperature is selected the maximum temperature that combustion gas turbine can bear; Indoor in final-stage combustion, the oxidant that replenishes enough stoichiometric proportions is sent into the acting of final stage gas turbine after finishing whole fuel gas burnings and making it to reach a certain particular temperature value, realizes efficient low NOx combustion and high cycle efficieny.
2. the method for claim 1 is characterized in that, described combustion chamber and gas turbine are divided into two-stage at least.
3. the method for claim 1, it is characterized in that, described oxidant is air, oxygen-enriched air or oxygen, oxidant and fuel tolerance have the stoichiometric ratio that departs from of control, guarantee that fuel and oxidant burn in each grade combustion chamber under reducing atmosphere, be fuel gas oxidation or burning step by step, every grade of gas turbine is only finished the burning of part of fuel gas, enter the gas turbine acting of this one-level then, in the final-stage combustion chamber, the oxidant that replenishes enough stoichiometric proportions is finished the burning of whole fuel gas, enters the acting of final stage gas turbine.
4. the method described in claim 1, it is characterized in that, described final-stage combustion chamber and final stage gas turbine are made up of the gas turbine or the notes vapour combustion gas steam turbine of the burning gaseous fuel of routine, if any special requirement, do not adopt final-stage combustion chamber and final stage gas turbine, by the direct exhaust of previous stage gas turbine.
5. realize the multi-stage efficient enzironment-protection turbine gas-fuel staged burning system of the described method of claim 1, it is characterized in that this system comprises:
Multistage compressor, be used for implements spatial scalable compression and classification and supply with oxidant, on the one-level compressor oxidant inlet is arranged, compressor is divided into some levels by the pressure and the flow of the required oxidant of corresponding gas turbine combustion, inter cooler is set between compressor is at different levels or inter cooler is not set; Compressed Gas not at the same level is sent into respectively in the corresponding combustion chamber according to pressure, supplies with the required oxidant of burning of fuel gas;
Multistage gas turbine, it is driven by the high-temperature high-pressure fuel gas from the combustion chamber of this grade, is used to drive generator for electricity generation, also can drive compressor and calm the anger;
Composite chamber is used for fractional combustion fuel gas, so that generate high-temperature fuel gas, its first-stage burning chamber is connected between final stage compressor and the gas turbine; Other grade combustion chamber is arranged between the two-stage gas turbine, and the high-pressure gas import is arranged on the first-stage burning chamber, and the exhaust of previous stage gas turbine is as the fuel of next stage combustion chamber;
Air, oxygen-enriched air or pure oxygen enter the one-level compressor by oxidant inlet, after being compressed to certain pressure, a part is sent into the burning needs of final-stage combustion chamber for fuel gas, enter two-stage compressor behind the remainder process one-level inter cooler and further be compressed to more high pressure, and then telling a part, to send into the penultimate stage combustion chamber required for fuel gas burning, enter three grades of compressors behind the remainder process secondary inter cooler and further be compressed to more high pressure, after some levels, further send into of the burning of one-level combustion chamber again after the compression for fuel gas until entering the final stage compressor;
Having the high-pressure fuel gas of uniform temperature to enter the one-level combustion chamber by the high-pressure gas import mixes with the oxidant that the final stage compressor is sent here, the gas that generates HTHP after the partial combustion enters one-level gas turbine expansion acting, pressure and temperature is reduced to and enters that secondary combustion chamber is mixed with the supplemental oxidant that the penultimate stage compressor is sent here and partial combustion behind the certain value, the gas that generates high temperature and certain pressure enters second gas burning turbine expansion acting, after some levels, enter the final-stage combustion chamber until the gas decrease temperature and pressure behind certain value, the make-up gas of sending into the one-level compressor is finished burning and is entered the acting of final stage gas turbine and discharge through air exit then.
6. the system described in claim 5, it is characterized in that, described oxidant content is determined as follows: the heat of sending into the release of oxidant and part of fuel solid/liquid/gas reactions causes generation fuel gas to be warming up to specific high temperature, and generally this high temperature is the highest bearing temperature of gas turbine cycle system.
7. the system described in claim 5, it is characterized in that, described final-stage combustion chamber and final stage gas turbine are made up of the gas turbine or the notes vapour combustion gas steam turbine of the burning gaseous fuel of routine, final-stage combustion chamber and final stage gas turbine perhaps are not set, by the direct exhaust of previous stage gas turbine.
8. the system described in claim 7 is characterized in that, also also is provided with regenerator before the described combustion chambers at different levels as required, is used for the waste heat heated oxidant of gas turbine is sent into the combustion chamber again.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100174249A CN100462630C (en) | 2007-02-14 | 2007-02-14 | Multi-stage efficient enzironment-protection turbine gas-fuel staged burning method and system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100174249A CN100462630C (en) | 2007-02-14 | 2007-02-14 | Multi-stage efficient enzironment-protection turbine gas-fuel staged burning method and system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101025272A true CN101025272A (en) | 2007-08-29 |
| CN100462630C CN100462630C (en) | 2009-02-18 |
Family
ID=38743784
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007100174249A Expired - Fee Related CN100462630C (en) | 2007-02-14 | 2007-02-14 | Multi-stage efficient enzironment-protection turbine gas-fuel staged burning method and system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100462630C (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103742262A (en) * | 2013-12-18 | 2014-04-23 | 杨浩仁 | External combustion type engine and working principle thereof |
| CN103775238A (en) * | 2013-01-25 | 2014-05-07 | 摩尔动力(北京)技术股份有限公司 | Quasi carnot engine |
| CN103790660A (en) * | 2013-01-29 | 2014-05-14 | 摩尔动力(北京)技术股份有限公司 | Ultimate temperature ratio engine |
| CN112901343A (en) * | 2021-02-01 | 2021-06-04 | 中国航发沈阳发动机研究所 | Ground gas turbine with low pollutant emission |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4236071C2 (en) * | 1992-10-26 | 2002-12-12 | Alstom | Method for multi-stage combustion in gas turbines |
| DE10051221A1 (en) * | 2000-10-16 | 2002-07-11 | Alstom Switzerland Ltd | Burner with staged fuel injection |
| WO2003095814A1 (en) * | 2002-05-08 | 2003-11-20 | Paul Marius A | High efficiency gas turbine power generator systems |
| FR2852358B1 (en) * | 2003-03-13 | 2006-06-09 | METHOD AND DEVICE FOR COGENERATION BY GAS TURBINE WITH POSTCOMBUSTION CHAMBER | |
| DE10360951A1 (en) * | 2003-12-23 | 2005-07-28 | Alstom Technology Ltd | Thermal power plant with sequential combustion and reduced CO2 emissions and method of operating such a plant |
| US7096674B2 (en) * | 2004-09-15 | 2006-08-29 | General Electric Company | High thrust gas turbine engine with improved core system |
-
2007
- 2007-02-14 CN CNB2007100174249A patent/CN100462630C/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103775238A (en) * | 2013-01-25 | 2014-05-07 | 摩尔动力(北京)技术股份有限公司 | Quasi carnot engine |
| CN103775238B (en) * | 2013-01-25 | 2016-06-22 | 摩尔动力(北京)技术股份有限公司 | Quasi-Carnot engine |
| CN103790660A (en) * | 2013-01-29 | 2014-05-14 | 摩尔动力(北京)技术股份有限公司 | Ultimate temperature ratio engine |
| CN103790660B (en) * | 2013-01-29 | 2016-06-22 | 摩尔动力(北京)技术股份有限公司 | Limit temperature compares electromotor |
| CN103742262A (en) * | 2013-12-18 | 2014-04-23 | 杨浩仁 | External combustion type engine and working principle thereof |
| CN112901343A (en) * | 2021-02-01 | 2021-06-04 | 中国航发沈阳发动机研究所 | Ground gas turbine with low pollutant emission |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100462630C (en) | 2009-02-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101555835B (en) | Method and system for controlling load point of gas turbine engine | |
| US7926292B2 (en) | Partial oxidation gas turbine cooling | |
| US8176724B2 (en) | Hybrid Brayton cycle with solid fuel firing | |
| JPH08261013A (en) | Combined-cycle power plant and improving method of efficiency thereof | |
| US5410869A (en) | Method of operating a combination power plant by coal or oil gasification | |
| US20010039797A1 (en) | Advanced Cheng combined cycle | |
| JPH09125983A (en) | Operating method of power station plant | |
| EP0954687A1 (en) | Combustion turbine with fuel heating system | |
| CN106224099B (en) | A kind of double fuel cogeneration water filling forward and reverse Gas Turbine Combined-cycle system | |
| CN111799819B (en) | Coal gasification solid oxide fuel cell hybrid energy storage power generation system | |
| CN101881219A (en) | With external flame heater preheating inlet air and reduce outside seepage flow | |
| CN102933819A (en) | Lean-fuel intake gas turbine | |
| EP1862529A2 (en) | Hydrogen blended combustion system with flue gas recirculation | |
| US6189310B1 (en) | Combined gas turbine power system using catalytic partial fuel oxidation | |
| CA2319663C (en) | Gas turbine system and combined plant comprising the same | |
| CN100462630C (en) | Multi-stage efficient enzironment-protection turbine gas-fuel staged burning method and system | |
| EP1172525A1 (en) | Method of repowering boiler turbine generator plants and repowered boiler turbine generator plants | |
| CA2527948A1 (en) | Method for obtaining ultra-low nox emissions from gas turbines operating at high turbine inlet temperatures | |
| CN101551121A (en) | Multi-stage, efficient and environment-friendly type staged-combustion method and system for gas fuel of gas turbine | |
| JPH11238520A (en) | Fuel cell power generating apparatus | |
| Hassan et al. | Parametric and exergetic analysis of a power plant with CO2 and capture using chemical looping combustion | |
| CN109578098A (en) | The Natural Gas Co-generation electrification technique of zero carbon emission | |
| CN214944467U (en) | Compressed air-gas reheating type combined cycle power generation system | |
| CN114471401A (en) | Brayton cycle system and method based on chemical regenerative ammonia source partial cracking | |
| CN106089437B (en) | Supercritical carbon dioxide low temperature dynamical system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090218 Termination date: 20120214 |