JP2886844B2 - Gas turbine with premixed 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 provided with a premixing type combustor having an annular premixing chamber provided on the outer periphery of a pilot nozzle.

[0002]

2. Description of the Related Art In order to protect the environment, gas turbines are required to have even lower pollution. In recent years, "dry combustion systems" with improved combustion systems for gas fuels have been spreading. Low NOx in exhaust is realized. However, when a similar dry-type combustion system is constructed using liquid fuel, evaporation and mixing of the fuel involves many difficulties. However, in order to improve the convenience of use of the liquid fuel, its development has been eagerly desired. Was.

FIG. 3 shows an example of reducing NOx in exhaust gas. The figure shows ASME (The American Society of Mechani
FIG. 2 is a longitudinal sectional view showing a configuration of a dual premixed combustor 50 that can selectively use liquid fuel and gas fuel described in Paper 96-GT-195. The fuel injection nozzle device 51 of this premix type combustor 50
Ejects pilot fuel PF from a pilot nozzle 11 disposed on the center axis thereof, and supplies combustion air CA from the periphery thereof to burn. On the other hand, an annular premixing chamber 12 is formed on the outer periphery of the pilot nozzle 11, and a swirler 13 is mounted in an annular passage upstream of the pilot nozzle 11. The liquid fuel MF is ejected from the main nozzle 14 into the air flow CA supplied to the inside, and is mixed so as to have a constant air-fuel ratio suitable for lowering NOx.
And burned by the combustion flame of the pilot nozzle 11.

A gas fuel nozzle 15 is disposed downstream of the swirler 13. When gas fuel is used instead of liquid fuel, the gas fuel nozzle 15 injects gas fuel into the swirling airflow. And the mixture is burned in the combustion chamber C.

[0005]

In the conventional premixed combustor, the liquid fuel injected from the main nozzle 14 is mixed with air in the premixing chamber 12 to form an air-fuel mixture.
Before flowing into the combustion chamber C, the liquid fuel collides with the wall surface 12a of the premixing chamber 12 and adheres to the wall surface 12a. This wall 1
2a is not at a high temperature because it is far from the combustion flame in the combustion chamber C, and when the temperature of the wall surface 12a is within the temperature range where carbon is attached, the attached liquid fuel is carbonized and carbonized on the wall surface 12a. Accumulates. For this reason, the flow path of the air-fuel mixture is narrowed, the combustion conditions are changed, and NOx is increased. Also,
If the carbon adhering to the wall surface 12a comes off, it flows into the turbine together with the combustion gas and damages the blade, so that there is a problem that it is necessary to periodically perform the carbon removing operation.

On the other hand, when the temperature of the wall surface 12a is lower than the temperature at which the liquid fuel is carbonized, the liquefied liquid fuel
2a, it flows into the combustion chamber C and burns. However, since it burns in the form of large droplets, premix combustion does not occur, and there is a problem that the amount of NOx in the combustion gas increases.

[0007] The present invention solves the above-mentioned problem and prevents the fuel in the air-fuel mixture from adhering to the wall surface and forming large droplets into the combustion chamber without depositing carbon on the wall surface of the premixing chamber. It is an object of the present invention to obtain a gas turbine provided with a premixed combustor having no exhaust gas.

[0008]

According to a first aspect of the present invention, there is provided a gas turbine having a premixed combustor for supplying fuel to compressed air supplied from a compressor and burning the compressed air. A nozzle, an annular premixing chamber disposed on the outer periphery of the pilot nozzle, and a main nozzle for supplying fuel for premixing to the premixing chamber; By covering the portion with the inner peripheral wall of the premixing chamber, the outer peripheral surface of the inner peripheral wall is maintained at a temperature equal to or higher than the carbon deposition temperature. According to the above configuration, since the outer peripheral surface of the inner peripheral wall of the premixing chamber is heated to a temperature equal to or higher than the carbon adhering temperature, the liquid fuel adhered to the inner peripheral wall evaporates without being carbonized, and carbon is deposited on the inner peripheral wall surface. Nothing.

In a preferred embodiment of the present invention, the pilot nozzle, a premixing chamber and a main nozzle are mounted on the top of an inner cylinder of the combustor, and the compressor is provided between the inner cylinder and a housing covering the same. An air passage for supplying the compressed air from the inner cylinder to the combustion chamber inside the inner cylinder is formed, and an air inlet of the premixing chamber faces the air passage facing radially outward of the inner cylinder. . According to this configuration, since the air is heated on the outer surface of the inner cylinder while flowing in the air passage, the premixing in the premixing chamber is promoted. In addition, since the air flow path in the premixing chamber is bent in the axial direction from the air inflow port facing radially outward of the inner cylinder, the premixed air collides with the outer peripheral surface of the inner peripheral wall of the premixing chamber to rotate the shaft. The liquid fuel attached to the inner peripheral wall evaporates without being carbonized because it is bent in the direction and is sprayed on the inner peripheral wall surface having a high temperature.

[0010] Preferably, a fuel injection port of the main nozzle is disposed at an intermediate portion between an inner peripheral wall and an outer peripheral wall forming the premixing chamber. According to this configuration, since the fuel ejection port is separated from the inner peripheral wall and the outer peripheral wall, the ejected fuel is less likely to adhere to these walls.

Further, in the embodiment of the present invention, the gas for supplying gaseous fuel to the premixing chamber is provided upstream of the air inlet of the premixing chamber or downstream of the second swirler provided at the air inlet. A fuel nozzle is provided. According to this configuration, the liquid fuel and the gas fuel can be switched and used.

Preferably, a swirler is provided around the pilot nozzle to swirl the compressed air into the fuel chamber while swirling the compressed air. According to this configuration, since the pilot fuel injected from the pilot nozzle and the air flowing into the fuel chamber while swirling from the swirler are sufficiently mixed, a diffusion combustion region with less unevenness in the circumferential temperature distribution is formed. The inner peripheral wall of the premixing chamber can be uniformly heated in the circumferential direction.

[0013]

DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described below with reference to the drawings. FIG. 1 is a longitudinal sectional view showing a schematic configuration of a gas turbine provided with a single can combustor. The gas turbine 1 includes a centrifugal two-stage compressor 3, 4 for sucking air A from an air inlet and compressing the air A, a combustor 5 for supplying fuel to the compressed air for combustion, and a combustion gas G And a turbine 6 driven by The combustor 5 has a combustion chamber C
, And the combustion gas G generated in the combustion chamber C is guided to the turbine 6 by the scroll 9 to be rotated, and is connected to the turbine 6 by the rotating shaft 10.
The stage compressors 3 and 4 and a load L such as a generator are driven.

FIG. 2 is a longitudinal sectional view showing the structure of the head of the combustor 5. In FIG. 2, the combustor 5 has an inner cylinder 21 forming a combustion chamber C and a housing 22 covering the outer periphery thereof.
An air passage 23 is formed between the inner cylinder 21 and the housing 22. The combustor 5 is a single-can type, and is provided so as to protrude radially outward of the turbine 6 in FIG. 1. The compressed air CA supplied from the centrifugal two-stage compressors 3 and 4 is compressed by the air. The gas flows through the passage 23 toward the distal end of the combustor 5, and becomes the combustion gas G in the inner cylinder 21 and flows toward the proximal end of the combustor 5.

The fuel injection nozzle device 17 provided at the top of the combustor 5 has a pilot nozzle 24 for injecting pilot fuel at the center, and a pilot air passage 26 provided on the outer periphery of the pilot nozzle 24. The pilot air passage 26 communicates with the air passage 23 via an inlet 33, and has an outlet having an annular shape for swirling the compressed air CA supplied from the air passage 23 and flowing into the inner cylinder 21. Of the first swirler 25 are disposed.

On the outer periphery of the pilot air passage 26,
An annular premixing chamber 27 composed of an outer peripheral wall 27b and an inner peripheral wall 27c is arranged, and the premixing chamber 27 has a circular shape facing the air passage 23 facing radially outward of the inner cylinder 21. Air inlet 27a. A second swirler 28 for swirling the inflow air is attached to the annular air inlet 27a, and a plurality of main nozzles 29 for supplying fuel for premixing are provided on the downstream side of the swirler 28 in the circumferential direction. It is provided at intervals. The pilot nozzle 24
From the start, the liquid fuel is injected during both the start and the normal operation, and the liquid fuel is injected from the main nozzle 29 only during the normal operation.

The downstream end of the inner peripheral wall 27a covers a part of the outer periphery of the diffusion combustion region S1 by the fuel injected from the pilot nozzle 24.
1 is set to be heated to a temperature higher than about 600 ° C. which is the carbonization temperature of the liquid fuel by the diffusion combustion flame in FIG. On the side wall of the combustor 5, a spark plug 30 that is operated only during operation is mounted, and a plurality of gas fuel nozzles 3
1 are arranged at equal intervals in the circumferential direction.

The pilot nozzle 24 is provided with a liquid pilot fuel PF via a pilot fuel passage 34, the main nozzle 29 is provided with a main fuel MF via a main fuel passage 39, and the gas fuel nozzle 31 is provided with a gas fuel passage 41. The gaseous fuel GF is supplied via each. These fuels PF, MF, GF are controlled by fuel control means (not shown). From the opening at the end 29b of the main nozzle 29 opposite to the injection port 29a, the pilot air passage 2
Part of the air of No. 6 flows in and promotes atomization of the fuel.

Next, the operation of this embodiment will be described.
Part of the compressed air CA from the two-stage compressors 3 and 4 in FIG. 1 flows into the combustion chamber C through the air passage 23 from the dilution air hole 35 provided on the peripheral wall of the inner cylinder 21, A part of the air flows into the combustion chamber C from the air passage 23 through the inlet 33, the pilot air passage 26 and the first swirler 25, and the remainder flows into the premixing chamber 27 through the second swirler 28.
In the air flow blown into the inner cylinder 21 while being swirled by the first swirler 25, the atomized pilot fuel PF injected from the pilot nozzle 24 is mixed and atomized, and burns to form the diffusion combustion region S1. Is done. At this time, since the air passing through the swirler 25 is swirling, the air sufficiently mixes with the pilot fuel PF from the pilot nozzle 24. As a result, the diffusion combustion region S1 with less unevenness in the circumferential temperature distribution is formed.
Can be uniformly heated in the circumferential direction.

On the other hand, from the main nozzle 29 to the premixing chamber 27
The atomized liquid main fuel MF is injected into the inside. Compressed air CA is introduced into the premixing chamber 27 at the radially outer inlet 2.
7a, the gas flows in while being swirled by the second swirler 28, mixes with the main fuel MF injected from the main nozzle 29, and becomes a mixture having a constant air-fuel ratio suitable for NOx reduction. 27c, it is bent in the axial direction and sent to the combustion chamber C in the inner cylinder 21, ignited by the combustion flame in the diffusion combustion region S1, burns, and spreads from the outer periphery of the diffusion combustion region S1 to the downstream side. A premix combustion region S2 is formed.

At this time, the inner peripheral wall 27c is in the diffusion combustion area S
Since the combustion flame is heated to about 600 ° C. or higher, which is the lowest temperature at which carbon is not generated by the combustion flame 1, even if the fuel droplets become coarse due to the collision of the air-fuel mixture with the inner peripheral wall 27c, the coarse fuel droplets become large. Is evaporated on the inner peripheral wall 27c without being carbonized. Further, since the fuel ejection port 29a of the main nozzle 29 is disposed at an intermediate portion between the outer peripheral wall 29b and the inner peripheral wall 29c, that is, at a position away from the two walls 29b, 29c, the injected fuel is supplied to the two walls 29b, 29c.
Since it becomes difficult to adhere to the surface 29c, carbon adhesion to the wall surface is suppressed.

Premixed combustion is also realized when gas fuel GF is used instead of liquid main fuel MF, but in this case, unlike liquid fuel, the problem of carbon adhesion does not exist originally.

At the start, fuel PF is injected only from pilot nozzle 24 to form diffusion combustion region S1. Therefore, when the fuel MF is also injected from the main nozzle 29 after the start is completed, the inner peripheral wall 29c is already at 600 ° C.
Since the temperature is raised as described above, carbon adhesion is prevented.

Although the combustor 5 is of a single-can type in the embodiment, it may be of a multi-can type, and is not a type that projects in the radial direction of the gas turbine but is oriented in the axial direction. It may be a type.

Further, instead of arranging the gas fuel nozzle 31 upstream of the air inlet 27a in FIG. 2, the gas fuel nozzle 31 is located downstream of the second swirler 28 and upstream of the main nozzle as shown by a two-dot chain line. The fuel nozzle 31A may be provided.

[0026]

As described above, the gas turbine provided with the premixing type combustor according to the present invention is configured so that the outer peripheral surface of the inner peripheral wall of the premixing chamber is maintained at a temperature higher than the carbon deposition temperature. The liquid fuel adhering to the inner peripheral wall of the premixing chamber evaporates without being carbonized, and no carbon is deposited on the inner peripheral wall, so that maintenance for removing carbon is not required.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional view showing a schematic configuration of a gas turbine according to the present invention.

FIG. 2 is a longitudinal sectional view showing a configuration of a head of a premixed combustor according to one embodiment of the present invention.

FIG. 3 is a longitudinal sectional view showing the configuration of a conventional dual type premixed combustor.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Gas turbine, 3, 4 ... Compressor, 5 ... Combustor, 6 ...
Turbine, 17: fuel injection nozzle device, 21: inner cylinder, 2
2 housing, 23 air passage, 24 pilot nozzle, 25 first swirler, 26 pilot air passage, 27 premix chamber, 27a inlet, 27b outer wall, 27c inner wall, 28 Second swirler, 29: main nozzle, 31, 31A: gas fuel nozzle, C: combustion chamber, CA: compressed air, G: combustion gas, S1: diffusion combustion area.

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. ⁶ , DB name) F23R 3/30 F23R 3/16 F23R 3/28 F23R 3/34

Claims (6)

(57) [Claims] 1. A pilot nozzle for supplying fuel to compressed air supplied from a compressor and burning it, an annular premixing chamber disposed around the pilot nozzle, and a premixing chamber in the premixing chamber. A main nozzle for supplying fuel, by covering at least a part of an outer periphery of a diffusion combustion region by the pilot nozzle with an inner peripheral wall of the premixing chamber,
A gas turbine provided with a premixed combustor for maintaining an outer peripheral surface of the inner peripheral wall at a carbon deposition temperature or higher. 2. The compressor according to claim 1, wherein the pilot nozzle, the premixing chamber, and the main nozzle are mounted on a top portion of an inner cylinder of the combustor, and a space between the inner cylinder and a housing that covers the inner cylinder is provided from the compressor. An air passage for supplying compressed air to the combustion chamber inside the inner cylinder is formed, and the premixing air inlet of the premixing chamber faces the air passage facing radially outward of the inner cylinder. Gas turbine equipped with a combustor. 3. The gas according to claim 1, wherein a fuel injection port of the main nozzle is provided with a premixed combustor arranged at an intermediate portion between an inner peripheral wall and an outer peripheral wall forming the premixing chamber. Turbine. 4. The premixed combustor according to claim 1, wherein a gas fuel nozzle for supplying gaseous fuel to the premixing chamber is provided upstream of the air inlet of the premixing chamber. Gas turbine equipped with. 5. A gas fuel is supplied to the premixing chamber downstream of a second swirler provided at an air inlet of the premixing chamber for swirling inflow air, according to any one of claims 1 to 3. A gas turbine comprising a premixed combustor provided with a gas fuel nozzle. 6. The gas according to claim 1, further comprising a first swirler provided with a first swirler for causing compressed air to flow into a combustion chamber while swirling around an outer periphery of the pilot nozzle. Turbine.