JP3427617B2 - Gas turbine combustor - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustor provided with a premix combustor, which is provided in the vicinity of the center of the flow path in the vicinity of the exit of the flow path of the mixed gas of fuel and air in the premix combustor. The present invention relates to a gas turbine combustor equipped with a flame stabilizer.

[0002]

2. Description of the Related Art For example, Japanese Patent Application Laid-Open No. 4-103906 discloses
A gas turbine combustor equipped with a so-called bluff body type premixed combustor is described, and several flame stabilizer shapes are disclosed.By providing such a flame stabilizer, a flame can be stably generated even during lean combustion. It is described that it can be formed.

Japanese Unexamined Patent Publication No. 5-187637 discloses a structure of a premix combustor of a gas turbine combustor which is provided with a so-called recess type premix combustor on one side of the premix combustor outlet. In order to prevent the flashback by extinguishing the eddy currents generated from the end face, for example, at least a part of the inclined portion of the flame stabilizer provided at the inner peripheral side outlet of the premixing combustor is provided in the premixing combustor. A structure is described in which the flow passage is gently inclined and the flow passage is gradually narrowed.

[0004]

It is desirable to have a premixed combustor structure capable of widening the stable combustion range in a plant where the exhaust pressure varies greatly due to exhaust gas re-combustion, operating conditions where the load changes a lot, and the like. However, Japanese Laid-Open Patent Publication No. 5-187637 does not disclose anything about a so-called bluff body type combustor premixed combustor structure.

Further, in the bluff body type flame stabilizer as disclosed in Japanese Patent Laid-Open No. 4-103906, since the flame stabilizer is located in the flow path, the upstream end of the flame stabilizer has a problem of gas flow. Separation vortices may occur.

The separation vortex generated at the tip of the upstream side of the flame stabilizer affects the gas flow downstream of the flame stabilizer, and the separation vortex remains up to the flame held in the flame stabilizer, causing backfire by the separation vortex. It is also necessary to avoid fear.

Therefore, an object of the present invention is, in a gas turbine combustor equipped with a bluff body type flame stabilizer, a gas which can prevent flashback due to the effect of separation vortex due to the flame stabilizer and can secure a wide stable combustion range. It is to provide a turbine.

[0008]

The features of the present invention include a diffusion combustor and a premix combustor, wherein the premix combustor includes:
In a gas turbine combustor provided with a flow path through which a premixed gas of fuel and air flows, and a flame stabilizer disposed so as to divide the flow path into two parts, the flow path of the premixed combustor is , A narrowed portion in which the width of the flow path in the radial direction is gradually narrowed,
A run-up portion that is formed on the downstream side of the narrowed portion and has a substantially constant radial width, and a discharge portion that is formed on the downstream side of the run-up portion and has a gradually widened radial width. Equipment
The position where the support plate faces the approaching section or the narrowing section
Or placed upstream from the position facing the throttle.
That is what I did . The radial width of the discharge portion refers to the radial width of the flow path formed by the premix combustor flow path wall without considering the flame stabilizer.

Thus, in the combustion method of the premix combustor of the gas turbine combustor, the first step of gradually increasing the gas flow rate of the gas flowing through the flow path of the premix combustor, the gas flow rate is substantially Keep it constant,
A second step of rectifying the separated flow generated in the upstream portion, a third step of gradually slowing the gas flow velocity, and a fourth step of burning the gas with the flame held by the flame stabilizer. be able to.

By extinguishing the separation vortex and adjusting the flow at an early stage before the premixed gas is blown out into the combustion chamber, the premixed flame can be blown out without increasing the flow velocity at the premixer outlet. Can be suppressed.

By dividing the premixed gas into the throttle, the run-up section, and the discharge part in this way, the separation vortex is extinguished at a certain early stage before the premixed gas is blown into the combustion chamber, and the flow is rectified. Since it is possible to adjust the flow rate,
It is possible to prevent blowout due to acceleration in the premixer.

Further, this makes it possible to suppress flashback even if the fuel-air ratio of the premixer fluctuates due to load fluctuations.
The stable combustion range can be expanded.

In other words, even if the pressure in the combustor chamber changes due to various conditions, it is possible to prevent flashback and misfire.

[0014]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Various embodiments according to the present invention will be described below with reference to FIGS. In the description of various embodiments, the same parts are designated by the same reference numerals, and duplicated description will be omitted.

Compressed air A0 is supplied from the air compressor 1 of the gas turbine to the inside of the combustor, and the compressed air A0 passes between the rear flow sleeve 3a and the premix combustion chamber 5 and is premixed as premixed combustion air A2. It flows into the vessel 4. Also,
Part of the air passes between the front flow sleeve 3b and the diffusion combustion chamber 6 and flows into the diffusion combustion chamber 6 as diffusion combustion air A1, and the diffusion fuel F1 injected from the diffusion combustion combustion nozzle 7 is burned. The premixed combustion air A2 that has flowed into the premixer 4 is mixed with the fuel F2 for premixed combustion injected from the fuel nozzle 8 for premixed combustion, and this premixed gas preliminarily exits the premixer 4. A premixed flame is formed inside the mixed combustion chamber 5. This premixed flame is directed from the upstream side to the downstream side, which is provided at the center of the double pipe at the exit of the premixer 4 of the double pipe composed of the cylindrical premixer outer ring 4a and the premixer inner ring 4b. Streamlined ring-shaped flame stabilizer 9 and two flame stabilizer wake circulation flows 12 formed downstream of the inner and outer circumferences
Is held by.

The gas burned in the diffusion combustion chamber 6 and the premixed combustion chamber 5 flows into the gas turbine 2 to rotate the turbine.

The flame stabilizer 9 has a straight ring-shaped annular portion in the premixer 4, and at this portion, a relatively thin flat plate flame standing between the premixer outer ring 4a and the premixer inner ring 4b. It is supported by the container support plate 10. Since the upstream end of the annular portion, which is the support portion of the flame stabilizer 9, is in the flow in the premixer 4,
It becomes an obstacle to the flow in the premixer 4, and a flame holder upstream separation vortex 13 is generated at this portion.

The premixer throttle portion 15, the premixer runway portion 16, the premixer discharge portion 17, etc. formed in the flow path of the premix combustor will be described in detail below.

The premixer internal narrowing portion 15 is an area in the flow path of the premixer in which the width of the flow path is gradually narrowed. In the case where the premixer of the combustor has a cylindrical outer ring member and an inner ring member having a diameter smaller than that of the outer ring member and being substantially concentric, the radial width of the outer ring member or the inner ring member is It is a region that gradually becomes thicker toward the downstream side. Here, it is a region where the gas flow velocity is substantially increased except for the influence of the flame stabilizer. The radial width of the outer ring member may be the width between the inner side surface and the outer side surface of the outer ring member.

In the premixer throttle portion 15, the premixer outer ring 4a and the premixer inner ring 4b upstream of the flame stabilizer 9 are connected to the premixer 4 respectively.
In order to reduce the flow path area of the circle, the center angle from the apex of the circle is narrowed by an arc having an angle of about 30 ° or less at the maximum.

By compressing the flow in the premixer 4 toward the center and increasing the flow velocity, for example, the vortex (in the upstream side of the throttle portion, the throttle portion, or the runner portion near the throttle portion side ( When the upstream end face of the flame stabilizer 9 is applicable, the flame stabilizer upstream separation vortex 13) generated at the upstream end face can be reduced or eliminated. Here, the shape of the premixer throttle portion 15 is an arc, but it may be an optimum curve or straight line in accordance with the specifications required for the premixer 4.
For example, in the case of a straight line, even if it is configured with a curved line so that communication with the upstream flow path and the run-up part is continuous before and after the throttle part, Practically, it is preferable that the angle formed with the upstream flow path is about 30 ° or less. When the shape of the throttle part 15 in the premixer is an arc, if the central angle is too large, the throttle part 1 in the premixer 1
5 is not preferable because the flow is disturbed.

The ratio of the throttle portion is preferably such that the flow passage sectional area on the most downstream side of the throttle portion is reduced by 15 to 30% with respect to the radial passage sectional area on the upstream side of the throttle portion. . The ratio can be set in terms of flame holding performance, increase in pressure loss inside the premixer 4, and the like. These conditions and premixer 4
The height of the throttle part 15 in the premixer and the size of the throttle R are determined by the space that can be held.

When the throttling ratio is less than 10%, the throttling effect is not sufficient, and it is difficult to obtain the effect of widening the combustion stable range. Flame stabilizer upstream separation vortex 1 generated at the upstream end of flame stabilizer 9
3 is likely to remain up to the outlet of the premixer 4, and stable combustion cannot be expected. However, the length of the pre-mixer run-up part 16 can be made sufficient in terms of space, and the pre-mixer run-up part 16 can be provided.
This is not the case when the flame stabilizer upstream separation vortex 13 can be extinguished only by the rectifying effect of. Practically 1
When the amount is reduced by 5% or more, the effect of expanding the combustion stable range is relatively obtained, and when the amount is further decreased, the combustion stable range is expanded.

On the other hand, if it is significantly reduced below 30%, the pressure loss of the premixer may increase, the air flow rate may decrease, the fuel-air ratio may increase, and NOx may increase, so the balance falls within the above range. It is preferable. The reduction rate of the flow path width in the narrowed portion is determined in consideration of disappearance of the separation vortex, pressure loss, and the like.

However, if there is a margin to increase the pressure loss and the NOx generated by the premixed flame satisfies the required specifications, the flame stabilizer upstream separation vortex 13 disappears in the premixer throttle portion 15. The throttle ratio may exceed 30% depending on the balance between stable combustion and generated NOx.

The in-premixer run-up section 16 preferably has a region downstream of the throttle section, in which the width of the flow passage in the radial direction of the combustor is substantially constant. When the premixer of the combustor has a cylindrical outer ring member and an inner ring member having a diameter smaller than that of the outer ring member and being substantially concentric, the width of the outer ring member or the inner ring member is substantially constant. Area. Here, there is a region where the gas flow velocity is substantially constant except for the influence of the flame stabilizer. By providing the run-up portion, the effect of eliminating the vortex can be enhanced in relation to the throttle portion. Further, the combustion range can be widened by providing the run-up portion. Further, for example, the combustion stable range can be widened by lengthening the run-up portion in which the width of the flow path is substantially constant. Further, even if the throttle portions are the same, by providing the run-up portion, or by providing the longer run-up portion, it is possible to reduce the NOx as compared with a combustor that does not have such a rectifying effect.

It is possible to eliminate the separation vortex that has not disappeared in the constriction part, uniform the flow velocity and streamline, and the discharge part such as the flame-holding part of the flame stabilizer whose outlet shape is restricted is adjusted by the run-up part. By supplying the generated flow, a stable flame can be formed in the combustion chamber.

It is possible to prevent turbulence of the gas streamlines that occurs in the downstream portion of the throttle portion. The configuration in which the throttle portion, the run-up portion, and the discharge portion are provided can widen the range in which stable combustion can be performed when the fuel-air ratio is changed, compared to when the shape of the throttle portion is made gentle and the discharge portion is provided. Since the gas flow can be adjusted to make the velocity distribution of the gas more uniform, it is possible to contribute to stable combustion in a lean combustion state.

However, if the length of the throttle and the size of the flame stabilizer are taken into consideration, or if the length of the combustor is too long, a structure without a runner can be used.

When the upstream end of the flame stabilizer is located in the middle of the run-up section, the cross-sectional area of the flow path of the premix combustor is, strictly speaking, the area of the flame stabilizer before and after the upstream end. It may change by the thickness of the support ring. However, if the thickness of the support ring itself is substantially constant and the thickness is structurally required, it is not necessary to consider changes in the width and cross-sectional area of the flow path for simplification of calculation. Good.

The relationship between the premixer internal throttle portion 15 and the premixer internal run-up portion 16 is based on the shape of the premixer internal throttle portion 15 determined from the point of increase of pressure loss in the premixer 4, etc. In order to eliminate the upstream separation vortex 13, the length of the in-premixer run-up portion 16 can be made relatively short when the throttling effect is large, but must be long when the throttling effect is small. There is. For example, the throttle ratio of the throttle unit 15 in the premixer is 15%.
If it is about 30%, it is desirable that the length of the pre-mixer run-up portion 16 is twice or more the length of the pre-mixer throttle portion 15.

The premixer discharge part 17 is located on the downstream side of the in-premixer run-up part 16 and is located at the position opposite to the position where the width of the flame stabilizer 9 arranged in the flow path gradually begins to widen. The downstream area corresponds.

For example, there is a region in which the radial width of the flow channel gradually widens toward the downstream side. Further, when the premixer of the combustor has a cylindrical outer ring member and an inner ring member having a diameter smaller than that of the outer ring member and being substantially concentric, the width of the outer ring member or the inner ring member is downstream. It has a region that gradually becomes thinner toward the side.

Specifically, for example, the run-up section 1 in the premixer
6, the flame stabilizer 9 spreads toward the downstream side from the place where the premixed gas is rectified by the in-premixer running portion 16, and the premixer has a shape substantially following the shape of the flame stabilizer 9. Outer ring 4a
The inner ring 4b of the premixer is also expanded, and the premixed gas is blown out to the premix combustion chamber 5.

By providing the premixer discharge part 17,
The premixed gas can be blown into the premixed combustion chamber 5 while being rectified by the in-premixer running section 16. Due to the effect of the throttle part 15 in the premixer and the run-up part 16 in the premixer, there is no vortex or unstable flow in this blowout flow and it is a uniform flow. Circulating flow 1
2 is stable and stable fuel with little fluctuation is obtained. At the same time, the flame does not return from the unstable flow, which helps prevent flashback.

In this embodiment, the shape of the premixer discharge part 17 is an arc, but it may be an optimum curve or straight line that meets the specifications required for the premixer 4.

As in this embodiment, the pre-mixer 4 outlet is divided into a pre-mixer throttle part 15, a pre-mixer run-up part 16 and a pre-mixer discharge part 17 to play respective roles. In comparison with a premixer that simply reduces the flow passage cross-sectional area at the outlet of the premixer 4 and obtains a uniform and large flow velocity for stable combustion, Since the flow velocity is adjusted, it is possible to prevent the performance from deteriorating even when the premixed flame is extinguished.

The details will be described below.

1) Make the cross-sectional area of the flow passage wider than that of the run-up portion. If the flow speed is only increased by the throttle and the run-up part to prevent flashback, it becomes effective to adjust the flow rate to the desired state by adjusting the discharge part to prevent the premixed combustion from being blown out. Is. As a result, it is possible to adjust the flow accelerated by the throttle unit and the like in the discharge unit. Therefore, there is no fear that the flow velocity at the outlet of the premixer will be considerably high, and blowout of the premix flame can be prevented.

2) Make the same area the same as the run-up area. From the viewpoint of flashback prevention, the flow velocity may be maintained.

3) There is a region where the same area gradually becomes narrower than the run-up portion. From the viewpoint of flashback prevention, the flow velocity may be maintained. For example, the flow passage cross-sectional area of the discharge portion can be reduced by about 10 to 15% with respect to the cross-sectional area of the run-up portion.

Since the discharge part is provided, the shape of the discharge part is processed to obtain a wider stable combustion range, so that an optimum gas flow state can be obtained and the stable combustion range can be expanded. For example, although the separation vortex could be eliminated, if the combustion stability is further improved, or if the state of the combustor changes over time, etc.
As described above, the ejection portion can be modified appropriately.

If the average flow velocity of the discharge part is about ± 15% of the average flow velocity of the runner part, stable combustion can be obtained without impairing the effect of the runner part. Specifically, it can be appropriately adjusted according to the specifications of the combustor.

For example, the stable range can be adjusted so as not to affect the extinguishing action of the separation vortex, and the maintainability is excellent. The discharged premixed gas is flame-held and burned by the flame stabilizer.

The flame stabilizer includes a flame holding portion and a support ring portion.

The upstream end of the support ring portion is
It may be arranged so as to face the approach portion. The detailed position can be determined in consideration of the thermal stress received by the flame stabilizer, the separation vortex generated near the upstream end of the support ring portion, the structural size (length) of the combustor, and the like. When it is provided in the approaching portion, it is preferably arranged on the upstream side of the approaching portion.

Besides, the upstream end of the support ring portion may be arranged at a position facing the throttle portion. Alternatively, it may be arranged upstream from the position facing the narrowed portion.

By being in the run-up portion, it is possible to reduce the influence of thermal stress and the like. In addition, if the length in the axial direction of the gas turbine is too short, the separation vortex generated in the upstream part of the support ring will not disappear, and the length will not reach the flame held by the flame stabilizer. Is preferred.

The shape of the flame stabilizer 9 corresponds to the operating method of the gas turbine or the combustor and the required low NOx performance.
The ratio of the height of the downstream end, the front-rear position of the downstream end of the flame stabilizer 9, and the like change. The spread shape of the flame stabilizer 9 spreads downstream from the place where the premixed gas is rectified by the pre-mixer inflow part 16 so as to satisfy these conditions. It is preferable that the premixer 4 has a shape that smoothly spreads so as not to disturb the uniform flow rectified by the in-premixer run-up portion 16 by changing the shape of the flow path.

For example, the shape of the flame stabilizer is changed so that it spreads smoothly toward the downstream side in a shape suitable for the operating method of the gas turbine or the combustor and the low NOx performance.

At the same time, by changing the shape of the inner and outer walls forming the premixer flow passage to a shape substantially conforming to the shape of the flame stabilizer, the flow conditioned in the run-up section is disturbed due to the change of the flow passage shape. Can be prevented, the premixed gas can be blown out into the combustion chamber in this uniform flow state, the circulating flow generated downstream of the flame stabilizer is stabilized, and flame stabilization by the flame stabilizer is promoted and stabilized. Combustion is obtained.

The width of the end face of the flame stabilizer on the combustion chamber side is preferably about 1/2 of the radial width of the flow passage on the upstream side of the throttle portion.

A schematic diagram of the combustion stable range according to the embodiment is shown in FIG.

This is because the flow passage cross-sectional area is 25
%, The runner length is double the length of the throttle,
This is a structure in which the flow passage cross-sectional area of the discharge portion is increased by 12% of the flow passage cross-sectional area of the run-up portion.

The gas turbine combustor according to the present invention and the gas turbine combustor to which the structure according to the present invention is not applied are compared with each other in terms of tolerance to fluctuations in the fuel-air ratio at each load. The description will be made based on the margin (hereinafter referred to as the base) of the combustion stable range on the misfire side at the time of ignition.

When the flame is ignited by the premixed combustor, the margin on the flame return side is 1.5 times that of the base in the gas turbine combustor to which the present invention is not applied, while the margin of the present invention is 2.
Enlarged by a factor of 2.

Further, in base load (rated operation) operation, the margin of the combustion stability range on the misfire side is 1.3 times that of the base in the gas turbine to which the present invention is not applied, whereas in the gas turbine of the present invention, Expands 1.4 times the base.

The margin on the flame return side is 1.7 times that of the base in the gas turbine to which the present invention is not applied, while it is expanded to 4.2 times that of the base in the gas turbine of the present invention.

Since the combustion range can be expanded by the present embodiment, even in a plant or the like where exhaust gas pressure fluctuation due to exhaust gas reburning is large, the exhaust gas pressure fluctuation has a great influence on the pressure inside the fuel chamber, and temporarily, As the pressure in the combustion chamber rises, the flow velocity at the premixer outlet decreases, the amount of air entering the premixer decreases, and the fuel-air ratio rises, reaching the flame return region as shown in FIG. 4 and leading to flashback. The possibility etc. can be prevented.

In a plant with a large load change, when the load is low, that is, when operating in a so-called narrow combustion stable range,
It is possible to suppress the possibility of reaching the flame return area shown in FIG. 4 due to various disturbances such as changes in temperature and humidity. Also,
The load can be greatly changed by expanding the combustion stable range.

As the second embodiment, the flame stabilizers 9 may be in the flow of the premixer 4, and the number thereof is not particularly limited, and may be two stages or three stages. A case where the flame stabilizer 9 has two stages will be described with reference to FIG.

The outer flame stabilizer 9a and the inner flame stabilizer 9b are installed in parallel at the outlet of the premixer 4, and an annular premixer is provided between the outer flame stabilizer 9a support portion and the inner flame stabilizer 9b support portion. The inner partition plate 14 is installed, and the premixer inner partition plate 14, the premixer outer ring 4a, and the inner ring 4b form a premixer inner narrowing portion 15 at the outlet of the premixer 4, and the outer flame stabilizer is further downstream thereof. 9a and the inner flame stabilizer 9b form a premixer in-progress part 16 and a premixer discharge part 17.

The same effects as those of the premixer structure described with reference to FIGS. 1 and 2 are obtained, a stable flame is obtained, and the stable combustion range is expanded.

Further, since the premixer internal partition plate 14 is installed in the flow path, a premixer internal partition plate upstream separation vortex is generated at the upstream end, but this premixer internal partition plate upstream separation occurs. The vortices also disappear in the course of passing through the premixer internal throttle portion 15 and the premixer internal run-up portion 16 as in the case of the flame stabilizer upstream separation vortex 13 generated at the upstream ends of the outer flame stabilizer 9a and the inner flame stabilizer 9b. Therefore, a stable flame can be obtained without affecting the premixed flame.

[0065]

According to the present invention, it is possible to suppress the influence of the separation vortex and form a stable circulation flow downstream of the flame stabilizer to obtain a stable premixed flame and prevent a flashback. A stable combustion range can be secured over a wide range.

[Brief description of drawings]

FIG. 1 is a sectional view of a combustor including a premixer and a flame stabilizer according to the present invention.

FIG. 2 is a sectional view of a premixer and a flame stabilizer according to an embodiment of the present invention.

FIG. 3 is a sectional view of a premixer and a flame stabilizer according to a second embodiment of the present invention.

FIG. 4 is a schematic diagram of a combustion stable range according to the present embodiment.

[Explanation of symbols]

1 ... Air compressor, 2 ... Gas turbine, 3a ... Rear flow sleeve, 3b ... Front flow sleeve, 4 ... Premixer,
4a ... outer ring of premixer, 4b ... inner ring of premixer, 5 ... premixed combustion chamber, 6 ... diffusion combustion chamber, 7 ... combustion nozzle for diffusion combustion,
8 ... Combustion nozzle for premixed combustion, 9 ... Flame stabilizer, 9a ... Outer flame stabilizer, 9b ... Inner flame stabilizer, 10 ... Flame stabilizer support plate, 12
... Flame stabilizer wake circulation flow, 13 ... Flame stabilizer upstream separation vortex, 14 ...
Premixer internal partition plate, 15 ... Premixer internal throttle, 16 ...
Pre-mixer run-up part, 17 ... Pre-mixer discharge part, 18 ... Pre-mixer partition plate upstream separation vortex.

Front Page Continuation (72) Inventor Yasutaka Komatsu 3-1-1 Sachimachi, Hitachi, Ibaraki Hitachi Ltd. Hitachi factory (72) Inventor Kaichi Moritomo 3-1-1, Sachimachi, Hitachi, Ibaraki Hitachi Ltd. Hitachi factory (72) Inventor Yoji Nakayama 3-1-1, Saiwaicho, Hitachi City, Ibaraki Prefecture Hitachi Ltd. Hitachi factory (72) -Inventor Naohiko Iwata 3-chome, Hitachi City, Ibaraki Prefecture No. 1 Stock company Hitachi Ltd. In Hitachi factory (56) Reference JP-A-6-272862 (JP, A) (58) Fields investigated (Int.Cl. ⁷ , DB name) F23R 3/18-3/34 F23D 14/02

Claims (6)

(57) [Claims] 1. A diffusion combustor and a premixed combustor, wherein the premixed combustor is provided in a flow path through which a premixed gas of fuel and air flows, and divides the flow path into two parts. In a gas turbine combustor provided with a flame stabilizer arranged, the flow passage of the premixing combustor has a narrowed portion in which a radial width of the flow passage is gradually narrowed, and a downstream portion of the narrowed portion. And a discharge part that is formed and has a substantially constant radial width of the flow path, and a discharge part that is formed on the downstream side of the runaway part and in which the radial width of the flow path gradually increases. and, to face the supporting portion of the flame holder to the approach portion or iris portion
Position, or upstream from the position facing the throttle section
Gas turbine combustor, characterized in that the placed. 2. A diffusion combustor and a premixed combustor, wherein the premixed combustor is supported by a support plate in a flow path through which a premixed gas of fuel and air flows, and the flow path is divided into two parts. In a gas turbine combustor provided with a flame stabilizer arranged so as to have a flow path of the premix combustor, a cylindrical outer ring member, an inner ring member having a diameter smaller than the outer ring member and substantially concentric As a constituent element, a narrowed portion in which the width of the outer ring member in the radial direction is gradually thickened, a run-up portion formed downstream of the narrowed portion, the width of the narrowed portion being substantially maintained, and a run-up portion of the run-up portion. The upstream end of the support portion of the flame stabilizer, which is formed downstream and has a discharge portion in which the radial width of the outer ring member is gradually reduced , is supported by the support plate.
A position facing the runner or the throttle, or the throttle
The gas turbine combustor is characterized in that the gas turbine combustor is arranged upstream from the position facing the . 3. The gas turbine combustor according to claim 2, wherein the inner ring member is located at a position facing the throttle portion of the outer ring member, and is located in a radial direction between an inner peripheral side surface and an outer peripheral side surface of the outer ring member. And another narrowing portion whose width gradually increases, a position facing the running portion of the outer ring member, and another running portion having a substantially constant radial width, and facing the narrowing portion of the outer ring member. The gas turbine combustor further comprising: another discharge portion having a gradually narrowing width in the radial direction. 4. A diffusion combustor and a premix combustor, wherein the premix combustor is supported by a support plate in a flow path through which a premixed gas of fuel and air flows, and the flow path is divided into two parts. In a gas turbine combustor provided with a flame stabilizer arranged so as to have a flow path of the premix combustor, a cylindrical outer ring member, an inner ring member having a diameter smaller than the outer ring member and substantially concentric As a constituent element, a narrowed portion whose flow passage cross-sectional area gradually decreases, a run-up portion formed downstream of the narrowed portion and having substantially the same cross-sectional area, and a cross-sectional area formed downstream of the run-up portion. Yes but the discharge part having a gradually narrowed region downstream portion of the run-up portion
And the support portion of the flame stabilizers that are supported by the support plate the run-up unit or
Or the position facing the narrowed portion or facing the narrowed portion.
The gas turbine combustor is characterized in that it is placed upstream from the position where 5. A diffusion combustor and a premixing combustor are provided, wherein the premixing combustor is provided in a flow path through which a premixed gas of fuel and air flows, and divides the flow path. The flame stabilizer has a flame stabilizer disposed therein, and the flame stabilizer has a flame stabilizer and a support for supporting the flame stabilizer.
In a gas turbine combustor comprising a port ring portion, the flow passage of the premix combustor is formed downstream of the throttle portion, and a throttle portion where the radial width of the flow passage is gradually narrowed , The cross-sectional areas are substantially the same
The run-up portion and the discharge portion formed on the downstream side of the run-up portion, in which the width of the flow passage in the radial direction gradually increases , and the support ring portion faces the run-up portion or the narrowed portion.
Position, or upstream from the position facing the throttle section
Gas turbine combustor, characterized in that arranged in. 6. The combustion method for a premixed combustor for a gas turbine combustor according to claim 1 , wherein a first step of gradually increasing a gas flow velocity of the gas flowing through the flow path of the premixed combustor, Maintaining the gas flow rate substantially constant, upstream of the flame stabilizer
A second step of rectifying the separated flow generated in the section, a third step of gradually slowing the gas flow velocity, and a fourth step of burning the gas with the flame held by the flame stabilizer. Combustion method for a premixed combustor of a gas turbine combustor.