CN102607060A - Method for controlling instability of combustion heat sound - Google Patents
Method for controlling instability of combustion heat sound Download PDFInfo
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- CN102607060A CN102607060A CN2012100650528A CN201210065052A CN102607060A CN 102607060 A CN102607060 A CN 102607060A CN 2012100650528 A CN2012100650528 A CN 2012100650528A CN 201210065052 A CN201210065052 A CN 201210065052A CN 102607060 A CN102607060 A CN 102607060A
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- central jet
- gas turbine
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Abstract
The invention relates to a control method of a gas turbine of a power station, in particular to a method for controlling the instability of the combustion heat sound. A high momentum central jet regulator is arranged in a regular combustor, less than 15% smoke of total air flow is added to the combustor through the central jet flow, and the combustion process is regulated and improved through the turbulence ordering structure of the central jet flow. According to the method for controlling the instability of the combustion heat sound, the combustion efficiency is greatly improved, the instability strength of heat sound is reduced, and the problem that the operating point of the regular gas turbine combustor derivates from the design value caused by instable heat sound is solved. Compared with the regular gas turbine combustor, the combustion efficiency A is greatly improved, and the instability strength of the heat sound is reduced. Besides, the combustor has the advantages of simple structure, reliable operation and low maintenance cost.
Description
Technical field
The present invention relates to a kind of control method of power station gas turbine, specifically, is the unsettled control method of a kind of combustion heat sound.
Background information
The discovery of hot voice phenomenon is of long duration, and the research range of early stage hot acoustic vibration mainly concentrates on the hot acoustic vibration of aero-engine, and at present, hot acoustic vibration appears in the gas turbine of a new generation continually, and its research has obtained extensively carrying out.
Traditional gas turbine burner is made up of eddy flow air register and fuel charging gear two parts, and this burner relies on swirling eddy smooth combustion, and gas turbine of new generation adopts the combustion system of lean fuel premixed combustion mostly, can reduce NO
xDischarging good environmental protection characteristic is arranged, but in running, gas turbine faces a very important problem, promptly has the pressure oscillation of low frequency large amplitude in the combustion chamber.The unsettled existence of heat sound will make and reduce efficiency of combustion by equipment work off-design point, increase pollutant emission, and be accompanied by huge noise; To bring structural failure when serious, accident is flame-out.
Existing gas turbine burner adopts and designs repeatedly and debug; Burner model through experimental size carries out hot test and numerical simulation and combines and debug the unsettled shooting condition of heat sound; And then the structure of improving burner avoids unsettled the exciting of heat sound, carries out commercial Application at last again.
But; Existing gas turbine burner exists following shortcoming at the scene: plant-scale gas turbine burner has been got rid of unsettled the exciting of hot sound when design; But often because all factors have been brought out hot sound instability again, therefore present gas turbine burner lacks simple and reliable method in the unsettled control of heat sound at the scene.
Summary of the invention
The purpose of patent of the present invention provides the unsettled control method of a kind of combustion heat sound, and it has solved the heat sound problem of unstable of gas turbine burner, and has improved efficiency of combustion.
Concrete technical scheme of the present invention is following:
The present invention is the unsettled control method of a kind of combustion heat sound; In normal burner, add high momentum central jet adjuster; Burner adds 15% flue gas with interior total air mass flow through central jet, utilizes the turbulent flow coherent structure adjusting of central jet and has improved combustion process.
The unsettled control method of combustion heat sound of the present invention has increased substantially efficiency of combustion and has reduced the unstable intensity of hot sound significantly, has solved conventional gas turbine burner the de-stabilising effect that is heated and has made the problem of operating point off-design value.
Beneficial effect of the present invention is following:
The present invention has set up high momentum central jet adjuster according to the job requirement and the concrete condition of gas turbine burner, and burner adds 15% flue gas with interior total air mass flow through central jet; Utilize the turbulent flow coherent structure adjusting of central jet and improved combustion process; Adopt the soft control method of turbulent flow coherent structure, solved conventional gas turbine burner the de-stabilising effect that is heated and made the problem of operating point off-design value, than the gas turbine burner of routine; Increased substantially efficiency of combustion; And reduced the unstable intensity of hot sound significantly, simultaneously, burner structure is simple, reliable, maintenance is cheap.
Description of drawings
Fig. 1 is the structural representation of the unsettled control method of a kind of combustion heat sound of patent of the present invention;
Fig. 2 is the experiment test system structural representation of the unsettled control method of a kind of combustion heat sound of patent of the present invention.
Among the figure, 1 is a wind, the 2nd, and secondary wind, the 3rd, fuel air, the 4th, high momentum central jet.
The specific embodiment
With reference to Figure of description technical scheme of the present invention is further specified below:
Fig. 1 is the structural representation of the unsettled control method of a kind of combustion heat sound of patent of the present invention, adds high momentum central jet adjusting device by the turbulent burner of routine and forms.Burner given here only is a kind of of normal burner; Regulate swirl strength to realize different steady combustion mechanism through regulating a wind 1 with the ratio of secondary wind 2;, reality can adopt multi-form normal burner when using, like the turbulent burner or the DC burner of band blade.Among Fig. 1, the device of logical high momentum central jet 4 is the core apparatus of patent of the present invention, and the heat sound in the time of can solving the normal burner burning through this device is unstable, has improved the efficiency of combustion of system simultaneously.Burner top is the combustion chamber among Fig. 1, and different equipment has different chamber structures and size.
Fig. 2 is the experiment test system structural representation of the unsettled control method of a kind of combustion heat sound of patent of the present invention.Test adopts methane to act as a fuel, and air is as oxidant.Air gets into from the passage of the logical wind 1 of turbulent burner and the passage of logical secondary wind 2 respectively after through the metering of two flowmeters, gets into the combustion chamber through the swirl vane in the passage separately then.CH
4From the passage of the logical fuel air 3 of turbulent burner, introducing the combustion chamber through flowmeter metering back burns.
In the combustion chamber, be designed with the dynamic pressure transducer installing port, the fluctuation pressure signal in the combustion process is sent into computer and is preserved and analyze after adopting data acquisition unit to gather.
The tail gas major part that burner the produces gas disposal that truncates, a small amount of tail gas through the flue gas recirculation pump after, get into after the flowmeter metering from the passage of the logical high momentum central jet 4 of turbulent burner and introduce the combustion chamber.
High momentum central jet 4 is drawn the flow rate of setting from burner tail gas, in burner, adds 15% flue gas with interior total air mass flow, utilizes the turbulent flow coherent structure of high momentum central jet 4 to regulate and has improved combustion process.
The flow of each spout adopts Alicat series mass flow control system, and precision is that 0.8%R. adds 0.2%F.S..It is the S type thermocouple of 0.25%F.S. that precision is adopted in test, and temperature signal employing precision is that 6 half Agilent 34970A main frame and Agilent 34908A Wiring module gathered, and maximum sample rate is 250Hz.It is 0.5%F.S that precision is adopted in pressure measxurement, and frequency response is the CYG series dynamic pressure transducer of 20KHZ.The fluctuation pressure signal adopts NI 6008 series of high speed data collecting systems to gather, and sample rate is 100KHz, and precision is 12.Adopt Virtual Instrument Development environment Labview to develop the parallel real-time data acquisition program of high-speed and continuous.Flue gas Measurement and analysis appearance is Testo 340 flue gas analyzers, and its certainty of measurement is in 2.5%.
The burner testing experiment has been tested noise characteristic, the combustion completion of the gas turbine burner under certain air rate (certain stoichiometric ratio and certain swirl strength).When not adopting high momentum central jet adjusting device to add flue gas, it is the violent pressure fluctuation of 1215Pa that burner has excited effective amplitude; After adopting high momentum central jet adjuster to add flue gas, burner is through the flue gas of total air mass flow of central jet adding 12%, and producing the pressure fluctuation effective amplitude is 389Pa, and noise has reduced by 68.0%, and efficiency of combustion has improved 9.2%.
Claims (2)
1. unsettled control method of combustion heat sound; It is characterized in that; In normal burner, add high momentum central jet adjuster; Described burner adds 15% flue gas with interior total air mass flow through central jet, utilizes the turbulent flow coherent structure adjusting of central jet and has improved combustion process.
2. the unsettled control method of combustion heat sound according to claim 1; It is characterized in that; Increase substantially efficiency of combustion and reduced the unstable intensity of hot sound significantly, solved the be heated problem of the operating point off-design value that de-stabilising effect makes of conventional gas turbine burner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100650528A CN102607060A (en) | 2012-03-13 | 2012-03-13 | Method for controlling instability of combustion heat sound |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100650528A CN102607060A (en) | 2012-03-13 | 2012-03-13 | Method for controlling instability of combustion heat sound |
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| CN102607060A true CN102607060A (en) | 2012-07-25 |
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| CN2012100650528A Pending CN102607060A (en) | 2012-03-13 | 2012-03-13 | Method for controlling instability of combustion heat sound |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112066415A (en) * | 2019-06-10 | 2020-12-11 | 中国航发商用航空发动机有限责任公司 | Combustion chamber, gas turbine and method for suppressing oscillatory combustion |
| CN113418188A (en) * | 2021-06-21 | 2021-09-21 | 中国人民解放军国防科技大学 | Double-cyclone combustion instability control method and system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1188211A (en) * | 1996-12-20 | 1998-07-22 | 联合工艺公司 | Premixing fuel injector with low acoustics |
| US20030143502A1 (en) * | 2002-01-31 | 2003-07-31 | Heier Kevin Ray | Large scale vortex devices for improved burner operation |
| CN1707163A (en) * | 2004-06-08 | 2005-12-14 | 通用电气公司 | Burner tube and method for mixing air and gas in a gas turbine engine |
| CN101408315A (en) * | 2008-11-27 | 2009-04-15 | 浙江大学 | Low-noise high-efficiency gas turbine combustor |
-
2012
- 2012-03-13 CN CN2012100650528A patent/CN102607060A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1188211A (en) * | 1996-12-20 | 1998-07-22 | 联合工艺公司 | Premixing fuel injector with low acoustics |
| US20030143502A1 (en) * | 2002-01-31 | 2003-07-31 | Heier Kevin Ray | Large scale vortex devices for improved burner operation |
| CN1707163A (en) * | 2004-06-08 | 2005-12-14 | 通用电气公司 | Burner tube and method for mixing air and gas in a gas turbine engine |
| CN101408315A (en) * | 2008-11-27 | 2009-04-15 | 浙江大学 | Low-noise high-efficiency gas turbine combustor |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112066415A (en) * | 2019-06-10 | 2020-12-11 | 中国航发商用航空发动机有限责任公司 | Combustion chamber, gas turbine and method for suppressing oscillatory combustion |
| CN112066415B (en) * | 2019-06-10 | 2022-04-01 | 中国航发商用航空发动机有限责任公司 | Combustion chamber, gas turbine and method for suppressing oscillatory combustion |
| CN113418188A (en) * | 2021-06-21 | 2021-09-21 | 中国人民解放军国防科技大学 | Double-cyclone combustion instability control method and system |
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Application publication date: 20120725 |