KR20160027267A - A pre-mixed gas turbine combustor with a vortex generator and the driving method thereof - Google Patents

A pre-mixed gas turbine combustor with a vortex generator and the driving method thereof Download PDF

Info

Publication number
KR20160027267A
KR20160027267A KR1020140112857A KR20140112857A KR20160027267A KR 20160027267 A KR20160027267 A KR 20160027267A KR 1020140112857 A KR1020140112857 A KR 1020140112857A KR 20140112857 A KR20140112857 A KR 20140112857A KR 20160027267 A KR20160027267 A KR 20160027267A
Authority
KR
South Korea
Prior art keywords
fuel
combustor
vortex generator
air
present
Prior art date
Application number
KR1020140112857A
Other languages
Korean (ko)
Inventor
이영덕
김구
김한석
손채훈
최근원
Original Assignee
한국기계연구원
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 한국기계연구원 filed Critical 한국기계연구원
Priority to KR1020140112857A priority Critical patent/KR20160027267A/en
Publication of KR20160027267A publication Critical patent/KR20160027267A/en

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

The present invention relates to a generation technology using a gas turbine, and more specifically, to a pre-mixed combustor having a vortex generator mounted thereon and a driving method thereof. The pre-mixed combustor comprises: a swirler (110) supplying air; and a vortex generator formed on a center shaft (115) of the swirler (110). The combustion discharged material can be reduced using the vortex generator.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a premixed combustor equipped with a vortex generator,

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a power generation using a gas turbine, and more particularly, to a premixed combustor equipped with a vortex generator and a driving method thereof.

Among the various industrial fields, the power generation sector concentrates on the consumption of fossil fuels and generates a large amount of CO 2 and combustion emissions. The demand for the improvement of the efficiency of the power plant and the reduction and purification of the CO 2 generation are continuously increased It is a situation. Among various power generation technologies, gas turbines are attracting attention because they have high power generation efficiency and are advantageous for reducing emissions. Accordingly, various researches have been actively conducted to reduce combustion emissions generated in gas turbine combustors .

Techniques for reducing emissions from gas turbine combustors are largely lean burn, quick quench lean burn, catalytic combustion, etc. By applying these techniques, significant levels of emissions Reduction results have been reported.

The lean burn technique is a technique that burns the fuel mixed with excess air near the flammability limit, thereby lowering the temperature of the flame and reducing the generation of NOx. The lean lean burn method is a method in which a smaller amount of air than the theoretical air amount required for combustion is first supplied to the combustor to burn it in the fuel rich state, and then the excess fuel is supplied to the wake of the flame to re- Since the flame transitions from the hyper-rich combustion zone to the lean burn zone immediately, it is possible to suppress the generation of the hot zone of the flame. The catalytic combustion method is advantageous for reducing NOx because the fuel can be oxidized without forming a flame surface by using an oxidation catalyst and uniform combustion can be performed at a low temperature. In addition to the above-mentioned method, a method of recycling exhaust gas (fuel gas recirculation) and a water spraying method have also been proposed.

In recent years, lean pre-mixed combustors have been used to further reduce undesirable emissions levels. However, in the lean premixed combustor according to the prior art, since fuel and air are mixed in the combustion chamber, uniform mixing is not performed, and a hot spot is formed in which the temperature locally rises during combustion. In this region, There was a problem that was generated.

Korean Patent Publication (A) Publication No. 10-2008-0045060

SUMMARY OF THE INVENTION In order to solve the above-described problems, it is an object of the present invention to provide a premixed combustor equipped with a vortex generator capable of reducing combustion emissions by applying a vortex generator in a lean premixed combustor, and a driving method thereof.

It is another object of the present invention to provide a premixed combustor equipped with a vortex generator capable of efficiently combining a vortex generator and a swirler to improve the mixing degree of fuel and air, and a driving method thereof.

It is another object of the present invention to provide a premixed combustor equipped with a vortex generator capable of reducing combustion emissions by optimizing an equivalence ratio between air and fuel supplied to the combustor, and a driving method thereof.

According to an aspect of the present invention, there is provided an air purifier including: a swirler for supplying air; And a vortex generator formed on a central axis 115 of the swirler 110. The premixed combustor includes a vortex generator.

The swivel is a radial swirler 110 through which air is supplied through a first end 111 and a second end 112 located above the first end 111, The number of revolutions S M of the first stage 111 may be higher than the number of revolutions of the second stage 112.

Further, the fuel may be supplied through the fuel hole 140 formed in the lower portion of the combustor 100.

The vortex generator may be formed by machining a thread 122 on the metal rod 121.

The present invention also provides a method of making a machine, comprising: supplying air to a first end (111) of a transverse direction swivel (110) and a second end (112) located above the first end (111); And passing a vortex generator in which fuel and air are formed in a central axis 115 of the transverse swivel 110. The vortex generator includes a vortex generator.

The number of revolutions of the first stage 111 may be higher than the number of revolutions of the second stage 112.

Further, the fuel may be supplied through the fuel hole 140 formed in the lower portion of the combustor 100.

The vortex generator may be formed by machining a thread 122 on the metal rod 121.

Also, when the fuel is methane (CH 4 ), and the injection flow rate at the outlet 180 of the combustor 100 is the rated speed, the equivalence ratio of air to fuel may be 0.755 or more.

Also, when the fuel is methane and the injection flow rate at the outlet 180 of the combustor 100 is less than the rated speed, the equivalent ratio of air to fuel may be 0.650 or more and 0.730 or less.

As described above, according to the present invention, the combustion exhaust can be reduced through the swirler 110 and the premixed combustor equipped with the vortex generator.

In addition, when the two-stage traverse swivel (110) is used, the present invention can improve the mixing degree of the fuel and the air by supplementing the decrease in the number of swirls generated due to the rough surface of the vortex generator.

Further, the present invention has an effect of improving the degree of mixture of fuel and air by forming the number of revolutions of the first end 111 of the transverse direction swiveler to be higher than the number of revolutions of the second end 112. [

In addition, the present invention has an effect of reducing combustion emissions by controlling the equivalence ratio of air and fuel to 0.755 or more when the injection flow rate at the outlet 180 of the combustor 100 is the rated speed .

In addition, the present invention is effective in reducing combustion emissions by controlling the equivalence ratio of air to fuel to 0.650 or more and 0.730 or less when the injection flow rate at the outlet 180 of the combustor 100 is less than the rated speed.

1 is a cross-sectional view of a premixed combustor according to an embodiment of the present invention;
2 is a photograph showing a lateral swivel and vortex generator mounted in a premixed combustor according to an embodiment of the present invention;
3 is a schematic view of an experimental apparatus for a premixed combustor according to an embodiment of the present invention.
FIG. 4 is a graph showing discharge characteristics of a combustion exhaust according to a driving method of a premixed combustor according to an embodiment of the present invention. FIG.
FIG. 5 is a self-luminescent image of an OH radical measured according to an equivalence ratio change of a premixed combustor according to an embodiment of the present invention. FIG.

Hereinafter, embodiments of a premixed combustor equipped with a vortex generator according to the present invention and a method of driving the same will be described in detail with reference to the accompanying drawings. In the drawings, the same reference numerals are used to designate the same or similar components throughout the drawings. In the following description of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the subject matter of the present invention rather unclear.

FIG. 1 is a cross-sectional view of a premixed combustor according to an embodiment of the present invention, and FIG. 2 is a photograph showing a lateral direction swirl and a vortex generator installed in a premixed combustor according to an embodiment of the present invention. 1, the overall structure of the premixed combustor is shown, and on the lower right side, the lateral swivel 110 of the premixed combustor is shown enlarged. Fig. 2 (a) shows the two-stage structure of the transverse swivel, and Fig. 2 (b) shows the vortex generator formed on the central axis 115 of the transverse swivel.

1, the premixed combustor according to an embodiment of the present invention includes a swirler 110 and a combustion chamber 150. As the swivel (110), both the horizontal swivel or the longitudinal swivel are applicable.

In addition, when the surface of the vortex generator according to the embodiment of the present invention as described later is rough, the degree of mixing of air and fuel in the combustor is increased. On the other hand, in order to prevent the number of revolutions from decreasing, A two-stage transverse swivel can be used to compensate. but,

However, it is apparent to those skilled in the art that the technical spirit of the present invention can be applied not only to the transverse swivel but also to the longitudinal swivel.

The transverse direction swirler 110 has a primary stage 111 and a secondary stage 112 through which air is introduced. As can be seen in FIG. 1, the first end 111 is located closer to the fuel inlet than the second end 112. As described above, when the two-stage traverse swivel 110 is used, the air supplied through the first stage 111 and the fuel supplied through the fuel hole 140 pass through the vortex generator in the combustor, The number of turns may decrease as the degree increases. Therefore, there is an effect that the second end 112 is provided in the lateral direction swivel 110 to separately supply the air to supplement the reduced number of revolutions.

In general, the swirl number (S M ) is a very important parameter in the combustion furnace and the gasifier. It helps to stabilize the flame by forming a recirculation zone in the center of the reactor. Especially, it increases the mixture of fuel and oxidizer It plays an important role. The number of revolutions is determined according to the shape of the revolving machine, and the number of revolutions of the transverse revolving machine 110 can be calculated by the following equation (1).

Figure pat00001

Where h is the tangential air inlet height, n is the number of revolving vanes, t is the tangential air inlet width, R i is the outer radius of the swirler, R P is the fuel injection hole radius, R o Is the exit radius of the combustor.

In the embodiment of the present invention, referring to FIG. 2 (a), the lateral swivel 110 forms the ratio of the air flowing into the first stage 111 and the second stage 112 to 3: 1 , Which can be controlled by the ratio of the inflow area. The number of revolutions of the lateral direction swivel 110 can be set to 2.67 and 1.97 in the first stage 111 and the second stage 112, respectively, according to the equation (1). As a result, the air having the strong turning effect in the first stage 111 can be contacted with the air in the second stage 112, which is supplied with a somewhat lower turning strength, and the degree of mixing can be enhanced.

The combustion chamber 150 is formed on the top of the combustor, as seen in Fig. The fuel flows into the fuel chamber 130 from the bottom. The fuel chamber 130 communicates with the fuel hole 140, and the fuel is injected through the fuel hole 140 in the air supply direction. In an embodiment of the present invention, the fuel hole 140 may be formed by twenty around the central axis 115 of the swivel 110. [ Also, the mixed gas of air and fuel flows through the vortex generator formed on the central axis 115 of the combustor to increase the degree of mixing and flow toward the nozzle of the outlet 180 of the combustor.

Referring to FIG. 2 (b), in the embodiment of the present invention, the vortex generator formed on the central axis of the swirler has a threaded shape 122 and a projection 123. The threaded shape 122 can be formed by machining the metal rod 121. The projection 123 of the vortex generator may be fitted or screwed into the groove 116 (see FIG. 1) formed at the center of the swivel 110. [

3 is a schematic view of an experimental apparatus for a premixed combustor according to an embodiment of the present invention.

3, the experimental apparatus of the premixed combustor includes a combustor 100, a fuel supply device 160, an air supply device 170, exhaust gas measurement devices 210 and 220, a Coriolis mass flow meter 300, A valve 400, an ICCD camera 500 for flame measurement, and an image processing apparatus 600.

The combustor 100 may be formed in accordance with an embodiment of the present invention as described above. In particular, the combustion chamber may be formed of a quartz tube.

The fuel supply device 160 may use methane (CH 4 : 99.95%) as the fuel, the air supply device 170 compresses atmospheric air using a compressor, and then removes moisture through a freeze- .

Two Coriolis mass flow meters 300 are provided and may be connected to the fuel supply device 160 and the air supply device 160, respectively. In particular, the Coriolis mass flow meter 300 can be a Micromotion CMF025 model. The control valve 400 is connected to the Coriolis mass flow meter 300 and is capable of controlling the flow rate of fuel and air supplied to the combustor 100.

The exhaust gas measuring apparatuses 210 and 220 include an exhaust gas collecting pipe 210 and a gas analyzer 220. The exhaust gas collecting pipe 210 can collect the combustion exhaust gas using a water-cooled sampling probe having a triple-tube structure. The exhaust gas collecting pipe 210 may be installed at a position as shown in FIG. 1 in the combustion chamber. The gas analyzer 220 can analyze the flue gas from which water has been removed by using a water separator. In particular, it is desirable that the gas analyzer 220 be capable of continuous measurement, and in the embodiment of the present invention, Greenline's MK2 model (electrochemical method) can be used.

The ICCD camera 500 for flame measurement can be installed close to the combustor 100. The camera 500 can measure the structure of the flame formed in the combustion chamber of the combustor 100 and the self-emission signal of the OH radical. In particular, the camera 500 can measure the self-emission of the OH radical by mounting a filter having a wavelength of 307 nm, and can be photographed with the amplification 80 and the exposure 100 ms. The image processing apparatus 600 receives the photographed image from the camera 500. The image processing apparatus 600 may acquire an image with an average value for 100 frames. The image processing apparatus 600 may use a laptop-image processor (PI-MAX).

FIG. 4 is a graph showing the discharge characteristics of the combustion exhaust according to the driving method of the premixed combustor according to the embodiment of the present invention, and Table 1 shows the rated condition of the combustion test of the combustor according to the embodiment of the present invention. .

Parameter Unit Value Remark Air mass flow rate kg / hr 45.49 combustor exit velocity: 20m / s Air supply temperature K 300 ambient condition Air supply pressure kPa 101.3 ambient condition Fuel mass flow rate kg / hr 1.872 25kWth-class Air-fuel ratio kg / kg 24.3 rated condition Equivalence ratio
(陸)
-
0.7 rated condition 0.65-0.8 variables

4 (a) shows the concentration of the combustion exhaust (NOx) according to the presence or absence of the vortex generator (VG) when the combustor outlet injection flow rate is 20 m / s, and FIG. 4 b) indicates when the combustor outlet injection flow rate is 15 m / s. The presence or absence of the vortex generator was distinguished from the case of using the central axis of the threaded swivel according to the embodiment of the present invention and the case of using a smooth metal rod (see Fig. 2).

In the embodiment of the present invention, as can be seen from Table 1, the rated condition of the combustor outlet oil was set at 20 m / s. In order to change the equivalence ratio condition while keeping the flow rate of the combustor outlet injection constant, the experiment was performed by adjusting the fuel supply amount with the air supply amount fixed and by the equivalence value (Φ). The concentration of combustion exhaust (NOx) measured by the gas analyzer was converted to the oxygen concentration of 15% using equation (2).

Figure pat00002

Referring to FIG. 4 (a), it can be seen that in the case where the exit injection flow rate of the combustor is 20 m / s, which is the rated condition, and the equivalence ratio is 0.755 or more, the combustion exhaust is reduced when the vortex generator VG is applied. That is, in the section where the jet flow rate is 20 m / s and the equivalence ratio is less than 0.755, the combustion exhaust concentration is lower than when the vortex generator VG is not installed. However, in the section where the equivalent ratio is 0.755 or more, vortex is generated at the center of the combustor by the vortex generator (VG), and the mixing degree is increased.

Referring to FIG. 4 (b), it is confirmed that when the flow rate of the outlet of the combustor is 15 m / s, which is less than the rated condition, and the equivalence ratio is 0.650 or more and 0.730 or less, combustion effluent is reduced when the vortex generator VG is applied . That is, when the flow rate of the combustor outlet injection is lower than the rated condition, it can be seen that the combustion exhaust concentration is reduced at an equivalence ratio lower than that at the rated condition.

5 is a self-luminescent image of an OH radical measured according to the change of the equivalence ratio of the premixed combustor according to an embodiment of the present invention. 5A shows the case where the vortex generator VG is not mounted when the outlet injection flow rate of the combustor is 20 m / s which is the rated speed, and FIG. 5B shows the case where the vortex generator VG is mounted .

Generally, the self-luminescence of OH radicals in the flame region can be used to explain the heat release characteristics of the reaction zone, thereby explaining the structure of the flame and the extent of the local oxidation reaction can do.

As can be seen from FIG. 5, as the equivalence ratio increases, the amount of fuel supplied increases, so that the self-emission of the OH radical is strongly measured in a wide region. Particularly, when the vortex generator VG is mounted (refer to FIG. 5A), the OH of the center portion of the flame recirculation region is increased compared with the case where the vortex generator VG is not mounted (see FIG. 5B) The strength of the self-luminescence of the radical is increased, and the region in which the intensity is strongly exhibited is also widely measured. This is considered to be due to the reduction of the recirculation in the flame region as the number of turns decreases as the fuel-air mixture gas contacts the vortex generator (VG) within the combustor.

The foregoing description is merely illustrative of the technical idea of the present invention and various changes and modifications may be made by those skilled in the art without departing from the essential characteristics of the present invention. Therefore, the embodiments disclosed in the present invention are intended to illustrate rather than limit the scope of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments. The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.

100: combustor 110: lateral direction swivel
111: first stage 112: second stage
115: center shaft 116: groove
121: metal rod 122: threaded shape
123: projection 130: fuel chamber
140: fuel hole 150: combustion chamber
160: fuel supply device 170: air supply device
180: outlet 200: flue gas measuring device
210: Flue gas collection pipe 220: Gas analyzer
300: Coriolis mass flow meter 400: Control valve
500: ICCD camera for flame measurement 600: Image processing device

Claims (11)

Air-supplied swirler (110); And
And a vortex generator formed in a central axis (115) of the swirler (110). ≪ Desc / Clms Page number 20 > The method according to claim 1,
Characterized in that the swivel is a radial swirler (110) in which air is supplied through a first end (111) and a second end (112) located above the first end (111) Premixed combustor with vortex generators. 3. The method of claim 2,
Wherein the number of revolutions (S M ) of the first stage (111) is higher than the number of revolutions of the second stage (112). The method according to claim 1,
Wherein the fuel is supplied through a fuel hole (140) formed in a lower portion of the combustor (100). The method according to claim 1,
Wherein the vortex generator is formed by machining a threaded shape (122) on the metal rod (121). Supplying air to a first end (111) of the transverse swivel (110) and a second end (112) located above the first end (111); And
Passing a vortex generator in which fuel and air are formed in a central axis (115) of the transverse swirler (110). The method according to claim 6,
Wherein the number of revolutions of the first stage (111) is higher than the number of revolutions of the second stage (112). The method according to claim 6,
Wherein the fuel is supplied through a fuel hole (140) formed in a lower portion of the combustor (100). The method according to claim 6,
Wherein the vortex generator is formed by processing a threaded shape (122) on the metal rod (121). The method according to claim 6,
The fuel uses methane (CH 4 )
Wherein the equivalence ratio of air to fuel is equal to or greater than 0.755 when the jet flow rate at the outlet (180) of the combustor (100) is at a rated speed. The method according to claim 6,
The fuel uses methane,
Wherein the equivalence ratio of air to fuel is equal to or greater than 0.650 and equal to or less than 0.730 when the injection flow rate at the outlet (180) of the combustor (100) is less than the rated speed.
KR1020140112857A 2014-08-28 2014-08-28 A pre-mixed gas turbine combustor with a vortex generator and the driving method thereof KR20160027267A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020140112857A KR20160027267A (en) 2014-08-28 2014-08-28 A pre-mixed gas turbine combustor with a vortex generator and the driving method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020140112857A KR20160027267A (en) 2014-08-28 2014-08-28 A pre-mixed gas turbine combustor with a vortex generator and the driving method thereof

Publications (1)

Publication Number Publication Date
KR20160027267A true KR20160027267A (en) 2016-03-10

Family

ID=55538671

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020140112857A KR20160027267A (en) 2014-08-28 2014-08-28 A pre-mixed gas turbine combustor with a vortex generator and the driving method thereof

Country Status (1)

Country Link
KR (1) KR20160027267A (en)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20080045060A (en) 2006-11-17 2008-05-22 제너럴 일렉트릭 캄파니 Triple annular counter rotating swirler

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20080045060A (en) 2006-11-17 2008-05-22 제너럴 일렉트릭 캄파니 Triple annular counter rotating swirler

Similar Documents

Publication Publication Date Title
EP2182279B1 (en) Oxyfuel boiler system and method of controlling the same
EP1917469B1 (en) Method using a cogeneration system with oxygen-enriched air assisting system
RU2006106648A (en) METHOD FOR BURNING FUEL SUBSTANCES, INCLUDING WASTE
WO2012102206A1 (en) Burner combustion method
CN102588113A (en) Stoichiometric exhaust gas recirculation and related combustion control
JP2004525335A (en) Apparatus and method for injecting liquid fuel into an air stream for a combustion chamber
US20080267783A1 (en) Methods and systems to facilitate operating within flame-holding margin
CN105737203A (en) Swirler and pre-mixing combustor adopting same
RU2008111638A (en) DEVICE FOR MODIFICATION OF GAS FUEL COMPOSITION
JP2004526933A (en) Burner device that mixes fuel and air to burn
CN205351318U (en) Air classification hangs down NOx gas burner with adjustable whirl intensity
CN103672969A (en) Dual-fuel combustion chamber nozzle of combustion gas turbine
US11898756B2 (en) Multi-nozzle fuel injection method for gas turbine
KR20160027267A (en) A pre-mixed gas turbine combustor with a vortex generator and the driving method thereof
KR102437258B1 (en) Combustion system using pressurized pure oxygen
JP2585798B2 (en) Low NOx combustion device
KR102261150B1 (en) A Low-NOx combustor capable of internal recirculation of flue gas by using venturi effect through improvement of burner structure
CN204213971U (en) Premixed swirl formula nozzle on duty
CN110375330A (en) A kind of classification oxygen supply combustion chamber and gas turbine classification oxygen supply combustion method
RU2506446C1 (en) Method of operating gas engines with low-calorific ch4-containing gas and mixer to this end
JP2015034649A (en) Gas turbine combustor
CN109442400A (en) A kind of standing vortex formula flue gas is interior to recycle low NO
US20240019118A1 (en) Burner, System, and Method for Hydrogen-Enhanced Pulverized Coal Ignition
JP2665486B2 (en) gas turbine
CN217103618U (en) Sleeve lime kiln device for reducing emission of nitrogen oxides

Legal Events

Date Code Title Description
A201 Request for examination
E902 Notification of reason for refusal
E601 Decision to refuse application