CN1878986A - Device for stabilizing combustion in gas turbine engines - Google Patents

Abstract

Disclose is a burner for a gas turbine combustor that uses a central bluff body flame holder and a quarl to shape the recirculation zone in order to stabilize the combustion process. The burner includes, among other elements, a cylindrical main body and a flame holder. The flame holder is disposed within a fuel-air mixing chamber and includes a base portion and an elongated bluff body. The base portion engages with the main body of the burner in a supporting manner and the elongated bluff body extends in an axially downstream direction from the base portion through the internal mixing chamber so as to position a combustion ignition point downstream of the internal mixing chamber. In a representative embodiment, the burner further includes a quarl device disposed adjacent to the downstream end portion of the burner main body. The quarl device defines an interior recirculation chamber and a burner exit. The interior recirculation chamber is adapted for receiving precumbustion gases from the mixing chamber and for recirculating a portion of the combustion product gases in an upstream direction so as to aid in stabilizing combustion.

Description

Stable Combustion Devices for Gas Turbine Engines

【Technical field to which the invention belongs】

The present invention relates to a combustor for a gas turbine, in particular to a combustor suitable for stable engine combustion, and more particularly to a combustor combined with a nozzle device and utilizing a central blunt flame arrester to stabilize the combustion process.

【Prior technology】

There are many applications of gas turbines, including power generation, military and commercial aviation, pipeline transmission, and ocean transportation. In a gas turbine engine, fuel and air are supplied to a combustion chamber where they are mixed and ignited with a flame to initiate combustion. Gas turbine engines have several major technical issues related to the combustion process. These issues include, for example, thermal efficiency of the burner (combustor), proper mixing of fuel and air, flame stabilization, pulsation and noise rejection, and control of pollutant emissions, especially nitrogen oxides (NO _x ). Flame stabilization refers to fixing the position and intensity of the flame in the burner in order to eliminate pulse and reduce noise and achieve other purposes.

Stable combustion in a gas turbine engine requires a cyclic process of combustion products, ie heat and free radicals, which are passed back upstream to the flame initiation point to facilitate the combustion process.

It is currently known that in order to improve the stability of the flame, the fuel-air mixture can be provided with swirled air or swirled to the fuel-air mixture, thereby stabilizing the combustion process. The swirl-stabilized combustion flow system promotes combustion by creating counterflow near the centerline of the combustor, thereby transferring heat and free radicals back upstream to the unburned fuel-air mixture.

The charcoal burners disclosed in US Pat. Nos. 5,131,334, 5,365,865, and 5,415,114 to Monroe et al. all contain flame stabilizers that impart swirl flow to the fuel-air mixture. The flame holder includes a plurality of radially spaced fan blade assemblies fixed to an annular member located on a central fuel supply pipe. The shape and orientation of the fan blades are designed to provide swirling air to the downstream end of the fuel supply pipe.

US Patent No. 5,477,685 to Samuelson, which is hereby incorporated by reference in its entirety, discloses a swirl-stabilized lean burn injector for a gas turbine combustor. In its exemplary embodiment, the fuel-air mixture exits the centrally located nozzle through a plurality of radial outlets. An air cyclone and an orifice device were attached to the downstream end of the Samuelson injector to facilitate recirculation flow. The fuel-air mixture exiting the nozzle radially meets the air traveling axially through the injector in a helical path due to the air swirler. Nozzle devices are used in industrial boilers and furnaces to intensify and change the shape of recirculated hot combustion products.

Conventional burners that use swirl to stabilize combustion, such as the one shown above, need to have sufficient swirl strength to allow recirculation to occur near the centerline, as shown in Figure 1. As noted above, in swirl-stabilized combustion, combustion is stable when the heat and free radicals generated during the combustion process travel upstream back to the recirculation zone where they mix with the unreacted fuel-air mixture and combustion begins. Combustion stability is heavily dependent on the recirculation of these hot combustion products back upstream. Furthermore, as the velocity of the recirculated combustion products increases, the upstream flux of thermally and chemically active combustion products also increases, and the combustion process tends to be more stable over a wider range of operating conditions.

The swirl intensity has a strong influence on the size, shape and intensity of the hot combustion product recirculation zone. The swirl strength is measured by a nondimensional number, which is defined as the ratio of the axial flux of angular momentum to the axial flux of axial momentum. Generally, when the swirl number is less than 0.4, the recirculation zone does not occur. When the swirl number increases, the total pressure at the stagnation point decreases. As shown in Figure 1, the stagnation point is where the upstream flow of combustion products along the centerline meets the downstream axial flow of air from the burner, where all velocities are zero. Typically, swirl numbers greater than about 0.6 create a low pressure region at the leading stagnation point. This low-pressure area makes the combustion products flow upstream from the downstream end of the burner where the pressure in the burner is higher to the stagnation point before the pressure decreases. This is the mechanism leading to the formation of the main recirculation zone (see Figure 1).

Increasing the swirl number (S _n ) tends to decrease the forward stagnation pressure and increase the upstream recirculation velocity near the midline. This increased upstream flow of combustion products increases the flux of hot gases and chemically active species to the stagnation point before intense combustion can begin. When the swirl number is low (ie 0.4<S _n <0.6), the pressure at the stagnation point is only slightly lower than the pressure at the stagnation point in the recirculation zone. Consequently, the flux of heat and chemically active combustion products being transferred back upstream is low and combustion is less stable, especially when the combustion is lean.

The swirl number has other effects on the recirculation zone. For example, an increase in _Sn will reduce the low pressure below the head stagnation point and pull the lag point closer upstream, shortening the recirculation zone. Furthermore, the increased hoop force with increasing S _n also causes the diameter of the recirculation zone to expand.

The nozzle device is used in industrial boilers and furnaces to reduce the influence of the swirl number on the length and diameter of the recirculation zone. The orifice device also allows the diameter of the recirculation zone to be enlarged to the diameter of the outlet of the orifice device without increasing _Sn . Furthermore, when using a jet device, the length of the recirculation zone is less sensitive to the swirl number and exhibits a length of approximately 2 to 2.5 times the diameter of the jet device outlet.

The nozzle arrangement allows the use of high _Sn without creating a large diameter recirculation zone. However, when the burner using the nozzle device is at a strong swirling intensity, the flame tends to move upstream and penetrate deep into the burner and damage the parts of the burner. Again, when combustion is initiated on the lean side of stoichiometry, a richer mixture will increase the flame velocity. This increase in flame speed also causes the flame to move further upstream into the burner. In addition to damaging the burner hardware, uncontrolled flame movement deep into the burner can result in high NOx emissions.

Furthermore, stability issues can become significant when the fuel/air ratio is changed. When lean premixed combustion becomes very lean, the flame speed becomes very sensitive to changes in the fuel/air ratio. Constantly changing flame speeds often lead to displacement of the flame position, resulting in combustion pressure oscillations and noise.

When the flame enters the burner and the fuel/air ratio becomes richer, it can also make the combustion unstable and make the flame go deeper into the burner. A richer fuel/air ratio is typically offset by reducing swirl strength. However this will result in a cycle of flames entering and exiting the burner. This general instability problem can cause very high voltage pulses and elevated NOx emissions. This instability is typical of low frequency instability, usually between 80 and 150 hertz (Hz). The amplitude of the pressure pulse can be as high as 0.1 bar (bar), which is destructive to the gas turbine engine. Furthermore, during the part of the unstable cycle where the combustion is intense, large amounts of nitrogen oxides are produced.

In view of the above-mentioned shortcomings of the prior art, there is a real need for an improved burner, which not only improves the stability of the flame, but also reduces pressure pulse, noise and nitrogen oxide emissions.

【Content of invention】

This application relates to a burner for a gas turbine combustor, which utilizes a central blunt body flame arrester and a nozzle device to stabilize the combustion process. The burner consists of a cylindrical body, flame holder and other components.

The combustor body includes axially opposite upstream and downstream end portions, at least one fuel inlet passage, and at least one air inlet passage formed therein. Fuel and air inlet channels are constructed to supply fuel and air, respectively, to a mixing chamber formed at the downstream end of the main body. The mixing chamber has a plurality of circumferentially spaced surfaces formed therein for swirling and mixing fuel and air supplied to the mixing chamber.

The flame arrester is arranged in the mixing chamber, including a base part and a long blunt body. The base portion engages the burner body in a supporting manner, and the blunt body extends from the base portion in an axially downstream direction through the inner mixing chamber to place the ignition point of combustion downstream of the inner mixing chamber.

The burner also includes an orifice arrangement adjacent the downstream end of the body. The nozzle arrangement delimits the internal recirculation chamber and the burner outlet. An internal recirculation chamber is provided to receive the pre-combustion gas from the mixing chamber and to recirculate part of the combustion product gas in the upstream direction to assist in the stabilization of the combustion.

Imagine a blunt system of flame arrestors placed in the center of the mixing chamber, with a conical upstream section and a substantially cylindrical tip region. Ideally, the axial length of the flame arrester is designed to achieve an _Sn greater than about 0.6. The swirl number is the ratio of tangential momentum to axial momentum, which defines the ratio of the amount of combustion air flowing through the burner rotating to the amount of combustion air leaving the burner under axial flow conditions. A mathematical definition of the swirl number can be found in US Patent No. 5,365,865 to Monroe, the definition of which is incorporated herein in its entirety.

In an exemplary embodiment, at least one air inlet channel is formed in a substantially radially inward direction and fuel enters the mixing chamber of the body in a substantially axial direction. Ideally, the air enters the air inlet in a tangential and radially inward direction to impart swirl to the air passing through the burner, which is designed to achieve an _Sn of greater than about 0.6.

Those skilled in the art will immediately appreciate that the present invention is applicable to any form of combustion chamber or burner, such as a solid fuel burner or stove.

【Implementation】

Those skilled in the art will easily understand the above and other features of the burner of the present application from the detailed description of the following preferred embodiments. In the following reference drawings, similar structures of the present invention are marked with similar component symbols. In Figure 2, a combustor for a gas turbine combustor is generally indicated by the reference numeral 100. The burner 100 uses a central blunt flame arrester 20 and a nozzle arrangement 80 to stabilize the combustion process. The burner 100 includes a cylindrical body 50, a flame holder 20, a nozzle arrangement 80, and other components. The main body 50 and the flame arrester 20 may be attached to each other in a conventional manner, either held together with a tight fit, or mechanically interlocked.

Combustor body 50 includes axially opposite upstream and downstream ends, 52 and 54, respectively. A plurality of axial fuel inlet channels 56 and a plurality of radial air inlet channels 58 are formed in the main body 50 . Those skilled in the art will readily appreciate varying the location, number, and orientation of fuel inlet channels 56 and air inlet channels 58 without departing from the invention shown herein, and the configuration described here is for illustrative purposes only.

Fuel and air inlet channels 56 and 58 are constructed to supply fuel and air, respectively, to a mixing chamber 60 formed at the downstream end of the body. The mixing chamber 60 has a plurality of circumferentially spaced surfaces 62 or turbine vanes formed therein for imparting swirling motion and mixing to the fuel and air supplied to the mixing chamber 60 .

The flame arrester 20 is placed in the mixing chamber 60 and includes a base portion 22 and a long blunt body 24 . The base portion 22 engages the body 50 of the burner 100 in a supporting manner, and the blunt body 24 extends from the base portion 22 through the internal mixing chamber 60 in an axial downstream direction so as to place the combustion ignition point or stagnation point (forward stagnation point) 75 (see Figure 3) is placed downstream of the internal mixing chamber 60. The blunt body 24 also has a plurality of cylindrical grooves 27 formed on its surface and extending axially to define the scale of the turbulent flow in the burner 100 .

The orifice arrangement 80 is adjacent the downstream end 54 of the burner body 50 . The orifice arrangement 80 defines an internal recirculation chamber 82 and a burner outlet 84 . The internal recirculation chamber 82, defined by the internal surface 82a, is configured to receive pre-combustion gas from the mixing chamber 60 and to recirculate a portion of the combustion product gas in an upstream direction to aid in the stabilization of the combustion. In the embodiment disclosed herein, the internal recirculation chamber 82 is a typical venturi shape. However, other shapes that achieve separation of the pressure gradients of the mixing chamber and the recirculation chamber are contemplated by the invention.

The blunt body portion 24 of the flame arrester 20 is centrally located in the mixing chamber 60 and has a tapered upstream section 26 and a downstream neck section 28 having a radially enlarged head. The neck region can be shaped to further improve combustion product recirculation and flame stabilization. The axial length of the flame arrester 20 is selected to anchor the recirculation zone with a swirl number greater than about 0.6, but not greater than 2.0. As previously stated, the swirl number is defined as the ratio of the amount of swirling combustion air flowing through the burner to the amount of combustion air leaving the burner under axial flow conditions.

The combustor 100 is used to make the combustion cycle process more stable and to substantially reduce the tendency for sparking or pressure pulses to occur due to combustion instability in gas turbine engines using lean premixed combustion. The center body flame arrestor 20 and the nozzle device 80 have two key functions: 1) the position of the combustion initiation point is fixed in space, and 2) a higher swirl velocity can be achieved without causing the combustion to flash back (flash back). Enter the mixing chamber 60 of the burner 100. The flame anchoring of the blunt flame arrester 20 on the central axis allows for natural fluctuations in the fuel/air ratio and variations in swirl velocity without altering the flame position. The ability to increase the swirl intensity without causing flashback and the fixation of the combustion initiation point both make the combustion process more stable. Thus, the use of the nozzle arrangement 80 and the blunt body flame arrester 20 fundamentally changes the stability of swirl stabilized combustion compared to prior art burners.

The flame arrestor 20 substantially prevents the flame from flashing back along the centerline of the burner 100 into the mixing chamber 60 . By preventing flashback along the centerline from entering the mixing chamber 60, the fuel-air mixture can have a higher tangential swirl component. Increased swirl strength without flashback makes the orifice device more efficient in enhancing the recirculation of hot gases upstream, making the overall combustion process more stable. Increased heat recirculation upstream stabilizes combustion of leaner fuel-air mixtures. This will provide greater flexibility and robustness in engine operation while maintaining low engine emissions.

The orifice means 80 is used to make the recirculation zone smaller than that which would result from the influence of the swirl number alone. The nozzle arrangement 80 allows for high swirl numbers while maintaining a small diameter and short length recirculation zone. A high swirl number causes a large difference in pressure between the stagnation point and the stagnation point. This high pressure gradient will cause the thermochemically active combustion products to flow at high velocity and flux along the vicinity of the centerline to the stagnation zone before the initiation of combustion. The high flux of thermochemically active combustion products in the combustion initiation zone allows stable combustion of lean fuel and air mixtures. Combustion stability of lean fuel and air mixtures is important for low nitrogen oxide (NO and _NO2 ) emissions from gas turbine engines.

Maintaining a small recirculation zone is beneficial in maintaining the chemical activity of the hot combustion gases, allowing faster and more stable combustion initiation, especially at low combustion temperatures, which often occurs at low nitrogen oxides _NOx (nitrogen monoxide NO and nitrogen dioxide NO ₂ ) when the engine is below 1700K. Low residence time in recirculation becomes more important for chemically active combustion products as combustion pressure increases and combustion temperature decreases. Under high pressure, chemically active substances (or free radicals that are helpful for rapid initiation of combustion) are quickly relieved to an equilibrium level under the influence of high pressure. The lifetime of free radicals above equilibrium levels is shortened with increasing stress. When combustion temperatures are low, such as in low _NOx engines, the efficient use of the high non-equilibrium levels of these free radicals is all the more important because the free radicals are at low equilibrium levels at low temperatures.

Figure 3 is a cross-sectional view of a swirl stabilized combustor 100 depicting the upstream recirculation of combustion products to sustain the combustion process. The upstream and downstream ends of the combustor 100 are referenced by "U" and "D", respectively. As shown, the flow of combustion products is divided into different zones, namely a main recirculation zone 90 and an external recirculation zone 92 .

As previously stated, the procedure of swirling the fuel-air mixture to move the products of combustion upstream is generally used to stabilize combustion. In the disclosed combustor 100, the blunt flame trap 20 anchors the primary recirculation zone 90 in a fixed position. A flame front or combustion initiation point 94 of the premixed fluid is created along the outer surface of the primary recirculation zone 90 where heat and free radicals are mixed and unreacted premixed fuel and air are initiated. The flame starts at the end of the flame holder 20 and expands in a conical shape in the downstream direction.

The burner 100 maintains the position of the flame at the end 24 of the flame holder 20 even if the ratio of the fuel-air mixture changes significantly. When lean premixed combustion becomes very lean, the flame speed becomes very sensitive to the fuel/air ratio. This change in flame speed often results in a displacement of the flame position, which may result in oscillations in combustion pressure. By anchoring the flame position and preventing flame movement with a central blunt flame arrester 20, pressure oscillations are prevented.

A cross-sectional view of the burner 100 is provided in FIG. 4 a illustrating the conical flame 98 anchored in the flame holder 20 . Figures 4b to 4d show the burner 200 without a center body flame arrester. In the burner 200, when the swirl strength is strong, or the premixed fuel/air mixture is rich, the flame 298 tends to move toward the burner and deep into it, as shown in Fig. 4b. Making the mixture richer will increase the flame velocity when the combustion is on the lean side of stoichiometry. The increased flame velocity enables the flame to travel further upstream. Increasing the swirl intensity also produces the same tendency to move the flame further upstream. It is generally undesirable for the flame 298 to enter the combustor mixing zone 260, as shown in Figure 4b. Uncontrolled flame movement deep into the burner 200 can damage burner hardware and result in high NOx emissions. Retrofitting the burner with the addition of a central blunt body flame arrester 20 at the nozzle will anchor the stagnation point 96 before the main recirculation zone 90 at the end of the flame arrester 20 to prevent the main recirculation zone 90 and the flame from entering the mixing chamber 60 . For various swirl intensities that would otherwise drive the stagnation point 96 deep into the burner 100, or toward the outlet 84, or even outside the burner, the center blunt flame arrester fixes the stagnation point 96 (see FIG. 3 ) at The end of the flame arrester 20. Thus, the central blunt flame arrester 20 anchors the stagnation point 96 and the flame 198 in a single location so that they do not move continuously as the swirl intensity varies.

The central blunt flame arrester 20 has an optimal position where the swirl number can be increased or decreased in the same manner and the forward stagnation point 96 and the flame 198 continue to be attached to the flame arrester 20 . If the swirl intensity continues to decrease, the flame 198 will continue to adhere to the flame holder 20 until finally the flame jumps away from the flame holder and stabilizes at a considerable distance downstream, or outside the burner outlet 84 . Starting from the same optimum swirl number and central blunt flame arrester position, increasing the swirl intensity does not affect the flame position until, at a critical swirl intensity, the flame position jumps upstream and engulfs the main recirculation zone The end of the flame arrester 20. As long as operating conditions remain within a reasonable range of swirl strength and fuel/air ratio, the flame location will remain in place even if engine conditions change. These ranges have proven to be quite large, which is a positive characteristic of the burner 100 .

Movement of the flame position is a significant problem for combustion systems operating under very lean conditions. The flame 198 shown in Figures 4c and 4d is produced at the leanest fuel/air ratio and/or lowest swirl intensity. Swirl stable combustion can become very unstable when the combustion is very lean. However, the most effective way to reduce _NOx emissions is to lean the combustion so that the flame temperature can drop below the temperature at which diatomic nitrogen and oxygen ( _N2 and _O2 ) decompose and recombine into NO and _NO2 . If nearly twice as much air is mixed with the fuel before the fuel and air mixture is burned, the excess air acts as an inert substance heated by the combustion process. As long as sufficient or more air is supplied to the combustion process, the amount of energy released by the combustion process is determined only by the amount of fuel that has been burned. The amount of air that exceeds the combustion requirement does not affect the amount of energy released during the combustion process, but because the combined amount of fuel and air increases and the energy released remains unchanged, the temperature of the flame and combustion products decreases. The reduction in flame temperature also reduces the synthesis of _NOx (NO and _NO2 ). This is the principle on which all current gas turbine engines with low NO _X emissions are based.

As mentioned above, the addition of the central blunt flame arrester 20 to the burner 100 allows for an increase in the swirl intensity without flashback of the flame into the mixing chamber 60 . The ability to increase swirl intensity is to increase the counterflow of hot combustion products back upstream. The increased flow of hot combustion products provides more heat and free radicals, making combustion more solid and less unstable.

If the flame front starts outside the burner, the burner will have a maximum airflow rate for a constant pressure drop across the burner. If some disturbance causes the flame to jump into the burner, the mass flow rate of air through the burner will decrease because the heat generated by the combustion process will expand the air and increase the volume flow rate through the burner outlet . This increase in volume flow rate for a fixed pressure drop will result in a decrease in air mass flow rate through the burner. For most gas turbine engines, between 6 and 100 burners are used depending on the power rating of the engine. If the flame jumps into some burners, but not all, the burner with the flame inside will burn more intensely. This is because the same fuel is equally supplied to each burner via a common fuel manifold. The burner with the flame inside burns richer due to the decrease in air mass flow rate due to the increase in volumetric flow rate due to combustion inside the burner outlet. When the combustion is initially lean, the result of a denser combustion is an increase in flame velocity. The increase in flame speed allows the flame to penetrate deeper into the burner. This will increase the volumetric flow rate and additionally reduce the air mass flow rate for a denser combustion. Once inside, it is possible for the flame to stay inside some burners while staying out of others. If this occurs, it will result in high _NOx and hot spots when entering the turbine inlet corresponding to the richer combustor.

The combustion process within the burner will also affect the characteristics of the swirl, which can lead to a reversal of the previous sequence of drawing the flame into the burner. As the flame is drawn into the burner, the mass flow rate of air will decrease. The density of the air passing through the cyclone does not change resulting in a lower velocity and a reduction in the swirl intensity. The reduction in swirl intensity tends to move the stagnation point downstream before the main recirculation. The combustion process itself also tends to reduce the swirling intensity, because the combustion process expands the flow in all directions equally. Instability occurs when the flame moves into the burner causing the fuel/air ratio to become richer, which will push the flame deeper into the burner. Counteracting the richer fuel/air ratio that produces higher flame speeds is the decline in swirl strength. This will create a cycle of flames entering and exiting the burner. This general instability problem can cause very high voltage pulses and elevated _NOx emissions. This instability is a general low frequency instability, usually between 80 and 150 Hz. The amplitude of the pressure pulse can reach 0.1 bar pressure oscillation which is destructive to the gas turbine engine. Furthermore, in the part of the cycle where the combustion is dense, a large amount of _NOx is produced. The invention of applying a central blunt flame arrester to an orifice-based burner makes the flame position insensitive to variations in swirl intensity and fuel/air ratio, while allowing the flame to stabilize at a fixed position at the end of the flame arrester. This eliminates pressure oscillations and elevated _NOx emissions resulting from flame movement.

The present invention has been described in detail for the preferred specific embodiments, and those skilled in the art will be able to easily understand that various changes and/or modifications can be made by using the content disclosed in the present invention, without departing from the scope of the attached patent application The defined spirit and technical scope of the present invention.

The swirl number is the ratio of tangential momentum to axial momentum, which defines the ratio of the flow of combustion air rotating through the burner to the flow of combustion air flowing axially away from the burner.

[Simple description of icons]

In order to enable those who are familiar with the technology of this application to immediately understand how to make and use this application, please refer to the following drawings:

Fig. 1 is a cross-sectional perspective view of a swirl-stabilized burner of the prior art;

Fig. 2 is a cross-sectional perspective view of a swirl-stabilized burner containing a blunt body flame arrester of the present invention;

Figure 3 is a cross-sectional view of the burner of Figure 2 illustrating the swirling flow within the burner, the anchoring of the stagnation point before the main recirculation zone, and the flame front next to the central blunt flame arrester;

Figure 4a is a cross-sectional view of a burner constructed according to a preferred embodiment of the present invention, which illustrates that the flame is stabilized in the central blunt flame arrester;

Figure 4b is a cross-sectional view of a burner without a center blunt flame arrester of the prior art, which illustrates the flame at the flashback position;

Figure 4c is a cross-sectional view of the burner in Figure 4b, which illustrates that the flame is located at the downstream end of the burner, near the outlet; and

Figure 4d is a cross-sectional view of the burner in Figure 4b, illustrating that the flame is located outside the burner outlet.

[Brief description of component symbols]

100 Burner 198 Flame

20 Flame arrester 22 Base part

24 Blunt Body 26 Upstream Conical Section

27 column well 28 downstream neck area

200 Burner 260 Mixing Zone

298 flame

50 Main body 52 Upstream end

54 downstream end 56 fuel inlet channel

58 air inlet channel

60 Mixing chamber 62 Surface or turbine blades

75 front lag point

80 spout device 82 recirculation chamber

82a Internal Surface 84 Burner Outlet

90 Main Recirculation Zone 92 External Recirculation Zone

94 Starting point of combustion 98 Conical flame

Claims (20)

1. the burner of gas turbine (gas turbine) combustion chamber (combustor) usefulness comprises:

A) cylindrical body, have in axial relative upstream and downstream end, this main body has at least one fuel inlet channel and formation at least one air intake channel wherein, these channels are applicable to that fuel supplying and air are to the mixing chamber that is defined in downstream end respectively, and this mixing chamber is configured to make the fuel that is supplied to mixing chamber to produce eddy flow with air and it is mixed; And

B) flameholder (flame holder), be disposed in this mixing chamber, and comprise the pedestal part that engages with burner body, and from pedestal part through the internal mix chamber vertically downstream direction extend with the long bluff body (elongated bluff body) of control the position in combustion ignition point downstream, internal mix chamber.

2. burner as claimed in claim 1 also comprises:

Spout (quarl) device, the downstream end that is adjacent to burner body is arranged, this spout device defines interior recirculation chamber and burner outlet, this interior recirculation chamber is applicable to pre-burning (precombustion) gas of reception from mixing chamber, and along the combustion product gas of updrift side recycle sections, with auxiliary smooth combustion.

3. burner as claimed in claim 1, wherein, the bluff body of this flameholder is disposed at the axial centre place in the mixing chamber.

4. burner as claimed in claim 1, wherein, this flameholder bluff body has tapered zone.

5. burner as claimed in claim 1, wherein, this flameholder bluff body has the cusp field that radially amplifies.

6. burner as claimed in claim 1, wherein, the axial length of this flameholder is set as in order to reach the swirl number per min greater than about 0.6.

7. burner as claimed in claim 1, wherein, this at least one air intake channel is along the direction formation of radial inward in fact.

8. burner as claimed in claim 1, wherein, fuel edge axial direction in fact enters the mixing chamber of main body.

9. burner as claimed in claim 1, wherein, this at least one the fuel inlet channel that is formed at burner body comprises the spire that is used for giving angular momentum to fuel.

10. burner as claimed in claim 1, wherein, this flameholder bluff body has many and is formed at its outer surface and axially extended groove (flute).

11. the burner of gas turbine (gas turbine) combustion chamber (combustor) usefulness comprises:

A) cylindrical body, have in axial relative upstream and downstream end, this main body has at least one fuel inlet channel and formation at least one air intake channel wherein, these channels are applicable to that fuel supplying and air are to the mixing chamber that is defined in downstream end respectively, and this mixing chamber is configured to make the fuel that is supplied to mixing chamber to produce eddy flow with air and it is mixed; And

B) flameholder is disposed in this mixing chamber, and comprise the pedestal part that engages with burner body, and from pedestal part through the internal mix chamber vertically downstream direction extend long bluff body with the position in control combustion ignition point downstream, internal mix chamber; And

C) spout (quarl) device, the downstream end that is adjacent to burner body is arranged, this spout device defines interior recirculation chamber and burner outlet, this interior recirculation chamber is suitable for receiving from mixing chamber pre-burning (precombustion) gas, and along the combustion product gas of updrift side recycle sections, with auxiliary smooth combustion.

12. burner as claimed in claim 11, wherein, the bluff body of this flameholder is disposed at the axial centre place in the mixing chamber.

13. burner as claimed in claim 11, wherein, this flameholder bluff body has tapered zone.

14. burner as claimed in claim 11, wherein, this flameholder bluff body has the cusp field that radially amplifies.

15. burner as claimed in claim 11, wherein, the axial length of flameholder is suitable for making the swirl number per min of main recirculation to be stabilized in about 0.6 and about 2.0 scopes.

16. burner as claimed in claim 11, wherein, this at least one air intake channel is along the direction formation of radial inward in fact.

17. burner as claimed in claim 11, wherein, fuel edge axial direction in fact enters the mixing chamber of main body.

18. burner as claimed in claim 11, wherein, this at least one the fuel inlet channel that is formed at burner body comprises the spire that is used for giving angular momentum to fuel.

19. burner as claimed in claim 11, wherein, this flameholder bluff body has many and is formed at its outer surface and axially extended groove (flute).

20. the burner of gas turbine (gas turbine) combustion chamber (combustor) usefulness comprises:

A) cylindrical body, have axially relative upstream and downstream end, this main body has at least one fuel inlet channel and formation at least one air intake channel wherein, these channels are applicable to respectively fuel supplying and air to the mixing chamber that is defined in downstream end, and the fuel that this mixing chamber is configured to be supplied to mixing chamber produces eddy flow and it is mixed with air; And

B) be disposed in the mixing chamber and be used for the device of position that will control internal mix combustion ignition point downstream.

Images