JPH0663647B2 - Gas turbine combustor - Google Patents

Description

Description: TECHNICAL FIELD The present invention relates to a gas turbine combustor used in a gas turbine power plant, and more particularly to a gas turbine combustor capable of adjusting and controlling a fuel flow area.

[Technical Background of the Invention and Problems Thereof] In a gas turbine power plant, a gas turbine combustor is provided between a compressor and a gas turbine, and discharge air compressed by driving the compressor is used as combustion air. Guided to the gas turbine combustor. The guided combustion air mixes with the fuel injected from the fuel injection device in the gas turbine combustor and burns to become high-temperature combustion gas. This combustion gas is guided from the combustor transition piece to the gas turbine,
He is supposed to work on a gas turbine.

A conventional gas turbine combustor is configured as shown in FIGS. 9 and 10, and includes a liner outer cylinder 1 and a liner inner cylinder 2.
The combustor body 3 having a double cylinder structure is formed from An annular space between the liner outer cylinder 1 and the inner cylinder 2 is defined as a flow path 4 for combustion air, and the flow direction of the combustion air passing through the flow path 4 is reversed at the tip of the combustor body 3. It is injected from the air swirler 5 into the combustion chamber 6 formed in the liner inner cylinder 2.

On the other hand, a fuel injection device 7 is provided at the tip of the combustor body 3, and the fuel supplied to the fuel injection device 7 is injected from the fuel swirler 8 at the tip and mixed with combustion air in the combustion chamber 6. Then it is made to burn.

In the gas turbine combustor shown in FIG. 9, the swirler 5 for air is arranged on the outer peripheral side of the swirler 8 for fuel of the fuel injection device 7. Further, the gas turbine combustor in FIG. The swirler 5 is a type incorporated in the fuel injection device 7. In the latter gas turbine combustor, the fuel injection device 7 has a fuel passage and a fuel air flow passage partitioned by a partition plate.

By the way, the conventional fuel injection device of the gas turbine combustor has a constant fuel injection opening area, and the fuel flow passage area is always constant. Therefore, when the fuel flow rate changes in a wide range from a minute flow rate to a large flow rate, in the conventional gas turbine combustor, the differential pressure before and after the fuel injection hole is small in the operating range of the minute fuel flow rate. As a result, the fuel is not stably injected, and unstable combustion such as fuel vibration and misfire may occur.

Further, recently, fuels have been diversified in consideration of fuel economy, and various fuels having different calorific values have been used. When a single gas turbine uses fuels having greatly different heat generation amounts, the variation range of the fuel flow rate becomes larger, and in the fuel injection device having a constant opening area like the conventional gas turbine combustor, a small amount of fuel is used. At the flow rate, the differential pressure across the fuel injection hole could not be sufficiently secured, and there was a risk of unstable combustion.

[Object of the Invention]

The present invention has been made in consideration of the above-mentioned circumstances, and adjusts and controls the fuel injection area of the fuel injection device according to the load state of the gas turbine or the switching use of fuels having different heat generation amounts, to achieve stable fuel combustion and fuel consumption. It is an object of the present invention to provide a gas turbine combustor capable of coping with diversification of

[Summary of the Invention] In order to achieve the above object, the present invention provides a gas turbine combustor including a fuel injection device in a combustor body,
In the above fuel injection device, a fixed type porous plate having a plurality of fuel passage holes is provided in a cylindrical casing, and each fuel passage hole of the fixed type porous plate is provided with a fuel swirler through a fuel passage defined by a partition plate. Alternatively, it is characterized in that an area-variable perforated plate is provided corresponding to the fuel injection hole of the fuel injection nozzle and capable of selectively closing each fuel passage hole of the fixed perforated plate.

Example of Invention

An embodiment of a gas turbine combustor according to the present invention will be described below with reference to the accompanying drawings.

In FIG. 3, reference numeral 10 indicates a gas turbine combustor used in a gas turbine power plant. The gas turbine combustor 10 is provided between a compressor 11 and a gas turbine 12, and is discharged from the compressor 11. A plurality of, for example, 10 or 14 are accommodated in the air discharge chamber 13 along the circumferential direction. The gas turbine combustor 10 includes a liner outer cylinder 15 and a liner inner cylinder 16 having a double cylinder structure, and the combustor body 17 is constituted by the liner inner cylinder 16 and the outer cylinder 15.

An annular space between the liner outer cylinder 15 and the liner inner cylinder 16 is formed as a flow passage 18 for supplying combustion air, as shown in FIGS. 1 and 2, and the combustion air flow passage 18 is provided in the combustor. It is inverted at the tip (front end) of the main body 17 and communicates with the combustion chamber 21 in the liner inner cylinder 16 through the air swirler 20.

On the other hand, the fuel injection device 2 is provided at the center of the front end of the combustor body 17.
3 is provided, and the fuel supplied by the fuel injection device 23 through the fuel supply pipe 24 is injected into the combustion chamber 21 through the fuel swirler 25. In the combustion chamber 21, the fuel is mixed with combustion air and combusted to become high temperature combustion gas. The combustion gas is guided to the gas turbine 12 through the combustor transition piece 26 (see FIG. 3) and drives the gas turbine 12 to perform work.

By the way, the fuel injection device 23 includes a tubular casing 28 held by the combustor body 17, and the tubular casing 2
A fixed porous plate 29 is fixedly housed in the housing 8. As shown in FIGS. 4 (A) and 5 (A), the fixed porous plate 29 is provided with a large number of fuel passage holes 30 and 31 independently in the circumferential direction. The shapes of the fuel passage holes 30 and 31 are not limited to those illustrated. A plurality of partition plates 33 are provided on the downstream side of the fixed porous plate 29, and the partition plates 33 connect the fuel passages 35 to the fuel injection holes 34 of the fuel swirler 25.
The fuel passage holes 30 and 31 provided in the fixed porous plate 29 correspond to the fuel injection holes 34 of the fuel swirler 25 through the fuel passage 35 in a one-to-one correspondence. Since the fuel injection nozzle can be similarly applied instead of the fuel swirler 25, the fuel swirler 25 is used as a concept including the fuel injection nozzle.

The upstream side of the fixed porous plate 29 is the fuel supply chamber 3.
6, the fuel inlet port 37 is opened in the supply chamber 36. The fuel supply chamber 36 also serves as the cylinder chamber of the perforated plate 38 for varying the fuel injection area, which is capable of adhering to the fixed perforated plate 29 so as to move back and forth. The area varying perforated plate 38 is, for example, the fuel passage hole 3 shown in FIG. 5 (B).
Have 9. The fuel passage hole 39 corresponds to the fuel passage hole 31 of the fixed porous plate 29, and the remaining fuel passage hole 30 can be closed by the area varying porous plate 38. Then, the fuel passage hole 3 provided in the area varying perforated plate 38
The number of nine is set to be smaller than the number of fuel passage holes 30 and 31 of the fixed porous plate 29 by a predetermined ratio according to the operating conditions of the gas turbine or the calorific value of different fuels.

The area varying perforated plate 38 is connected to an actuator 41 via an operating rod 40 as a power transmission mechanism, and the fuel supply port 37 is operated by the operation of the actuator 41.
It can be reciprocated beyond. The actuator 41 is actuated and controlled by receiving an actuator actuation signal from the controller 42. The controller 42 controls the moving position of the actuator 41 in response to a signal A representing a timing for changing the fuel passage area such as a gas turbine load signal or a fuel switching signal.

Next, the operation of the gas turbine combustor 10 will be described.

When the gas turbine is started up or operated under a low load, or when a fuel having a high calorific value is used, as shown in FIG. 1, the actuator 41 is operated to change the area-changing perforated plate 38 to the fixed perforated plate 29. Bring them close together. As a result, the fuel injection device 23 is adjusted so that the fuel injection area is reduced, and the fuel passage hole 30 of the fixed porous plate 29 is closed.

Then, the fuel guided into the supply chamber 36 of the fuel injection device 23 passes from the common fuel passage holes 39 and 31 of the area varying perforated plate 38 and the fixed type perforated plate 29 to the fuel swirler 25 through the fuel flow passage 35. Guided and swirler for fuel 25
Is injected from the inside into the combustion chamber 21, but since the combustion passage hole 30 of the fixed porous plate 29 is closed, fuel does not flow,
Eventually, the fuel injection area in the fuel swirler 25 is reduced. By making it possible to adjust the fuel injection area of the fuel injection device 23, it is possible to sufficiently secure the differential pressure before and after the injection hole of the fuel swirler 25 even at a minute fuel flow rate.
It is possible to prevent unstable combustion such as combustion vibration and blowout. The stability of combustion improves as the number of holes provided in the fuel swirler 25, the fixed porous plate 29, and the area varying porous plate 38 increases.

On the other hand, in the case where a large amount of fuel is flown during the rated load operation of the gas turbine or when the fuel having a small calorific value is used, the fuel injection device 23 needs a large fuel injection area. In this case, as shown in FIG. 2, the actuator 41 is operated to move the area varying perforated plate 38 backward from the fixed perforated plate 29 beyond the fuel inflow port 37, and the respective fuel passages of the fixed perforated plate 29. All the holes 30 and 31 are opened. Therefore, the fuel supplied into the fuel supply chamber 36 passes through all the fuel passages 35 and is injected from the fuel swirler 25 into the combustion chamber 21. Therefore, the combustion injection differential pressure in the fuel swirler 25 is maintained at an appropriate value and stable injection is performed.

Next, a modified example of the gas turbine combustor will be described with reference to FIGS. 6 to 8.

A gas turbine combustor 10A shown in this modified example is one in which a combustion air swirler 20A and a fuel swirler (which may be a fuel injection nozzle) 25A are integrally incorporated in a fuel injection device 23A. Gas turbine combustor 10A
Has a fixed perforated plate 29A that is fixedly housed in the tubular casing 28, and an area varying perforated plate 38A is rotatably housed adjacent to the perforated plate 29A. The area changing perforated plate 38A is connected to a drive motor 46 via a power transmission mechanism such as a gear mechanism 45 or a chain sprocket mechanism, and the drive of the drive motor 46 causes the area changing perforated plate 38A to rotate. The rotational drive of the drive motor 46 is operationally controlled by the controller 42A.

The fuel passage holes 48 and 49 of the area varying perforated plate 38A are the seventh
As shown in FIG. 2A, for example, two types of fuel passage holes 48 having a central angle θ and fuel passage holes 49 having a central angle 2θ are alternately arranged at a predetermined circumferential interval. 48 and 49 are central angles θ formed on the fixed porous plate 29A.
Of the fuel passage holes 30A and 31A. By rotating the area-changing perforated plate 38A by the drive motor 46 by the angle θ, the fixed perforated plate 29A closes the positions where the fuel passage holes 30A and 31A are opened and a part of the fuel passage holes 30A. It is designed to selectively take the position to be set.

The downstream side of the fixed porous plate 29A is provided with the partition plates 50 arranged in the radial direction as shown in FIG.
5A and the fuel air flow path 51, and are independently and alternately arranged. The fuel passage 35A has a one-to-one correspondence between the fuel passage holes 30A and 31A of the fixed porous plate 29A and the fuel injection holes 34A of the fuel swirler 25A.

On the other hand, in the combustion air flow path 51, the inflow port opens to the circumferential side,
Combustion air flowing in from this inlet is swirler for air 2
The fuel is injected into the combustion chamber 21 from 0A.
Therefore, as shown in FIG. 7C, the fuel injection device 23A facing the combustion chamber 21 is provided with the fuel injection holes 34A of the fuel swirler 25A and the combustion air injection holes 52 of the air swirler 20A alternately.

Now, when the gas turbine is started up, when the load is low, or when fuel with a high calorific value is used, the operation control signal A is given to the controller 42A to rotate the drive motor 46, and the power transmission device is used. The variable area perforated plate 38A is rotated by a predetermined angle. That is, the area varying perforated plate 3
8A is rotated counterclockwise by a predetermined angle θ from the state shown in FIG. 7 (A).

As a result, the fuel passage hole 4 opened at the central angle 2θ
9 is the fuel passage hole 31A provided in the fixed type porous plate 29A even if the area varying porous plate 38A is rotated by the angle θ.
Will not be blocked. However, this fuel passage hole 31
The fuel passage hole 30A adjacent to A is completely closed. Therefore, the fuel passage hole 4 is formed in the area varying perforated plate 38A.
Since a large number of holes having the same shape as 8, 49 are installed in accordance with a predetermined area reduction rate, the area-variable perforated plate 38A
The desired fuel injection area can be reduced by rotating by the angle θ, and an appropriate fuel injection differential pressure can be obtained even when the fuel flow rate is small, and unstable combustion such as combustion vibration and misfire can be prevented.

Next, when a large amount of fuel is flown or a fuel having a small calorific value is used, by rotating the area-changing perforated plate 38A clockwise by an angle θ, the fuel passage hole shown in FIG. There are 48 and 49 arrangements. Therefore, the fuel passage holes 30A and 31A provided in the fixed porous plate 29A are provided.
Are all opened without being blocked by the area varying perforated plate 38A. Therefore, a sufficiently wide fuel passage area is secured, and stable combustion can be obtained by the ideal fuel injection differential pressure as designed.

In the embodiment of the present invention, various shapes and sizes of the combustion passage holes formed in the fixed type perforated plate or the area varying perforated plate are conceivable, and are not limited to those shown in FIGS. 5 and 7.

〔The invention's effect〕

As described above, the gas turbine combustor according to the present invention,
A fixed porous plate having a plurality of fuel passage holes is provided in a tubular casing of a fuel injection device, and the fuel passage holes of the fixed porous plate are swirled for fuel or fuel injection through a fuel passage defined by a partition plate. Since the area-variable perforated plate that corresponds to the fuel-injection holes of the nozzle and can selectively close each fuel-injection hole of the fixed perforated plate is installed, the fuel-injection area can be controlled by the area-variable perforated plate. It can be adjusted and controlled to suit the kind of fuel, stable and efficient combustion can always be obtained in the entire operating range of the gas turbine, and fuels with different calorific values can be stably burned by one gas turbine combustor. Therefore, it becomes possible to diversify the fuel and to flexibly operate the gas turbine.

[Brief description of drawings]

1 and 2 are partial cross-sectional views showing an embodiment of a gas turbine combustor according to the present invention, FIG. 3 is a view showing a mounting state of the gas turbine combustor, and FIG. 4 (A) is a gas. The figure which shows the structure of the fixed type porous plate downstream side of the fuel-injection apparatus incorporated in a turbine combustor, FIG. 4 (B) is the figure which shows the fuel swirler of the said fuel-injection apparatus, FIG. 5 (A) and (B). ) Is a diagram showing a fixed type perforated plate and an area varying perforated plate of the fuel injection device, respectively, and FIG. 6 is a diagram showing a modified example of the gas turbine combustor according to the present invention, and FIGS. 7 (A) and 7 (B). ),
(C) is a view showing a perforated plate for area adjustment, a fixed perforated plate, combustion air and a swirler for fuel, which are incorporated in the gas turbine combustor of FIG. 6, respectively, and FIG. 8 is the fuel injection device. And FIG. 9 and FIG. 10 are views showing the structure of the stationary type perforated plate on the downstream side of the conventional gas turbine combustor, respectively. 10 ... Gas turbine combustor, 11 ... Compressor, 12 ...
... gas turbine, 15 ... liner outer cylinder, 16 ... liner inner cylinder, 17 ... combustor body, 18 ... combustion air flow path, 20, 20A ... air swirler, 21 ... combustion chamber, 23 ...... Fuel injection device, 25,25A …… Fuel swirler, 29,29A …… Fixed perforated plate, 30,31,
30A, 31A ... Fuel passage hole, 33, 50 ... Partition plate, 34, 34A ... Fuel injection hole, 35 ... Fuel passage,
36 ... Fuel supply chamber, 38, 38A ... Area varying perforated plate, 41 ... Actuator, 42, 42A ...
Controller, 46 ... Drive motor, 51 ... Combustion air flow path.

Claims (5)

[Claims] 1. A gas turbine combustor having a fuel injection device in a combustor body, wherein the fuel injection device is provided with a fixed porous plate having a plurality of fuel passage holes in a cylindrical casing. Each fuel passage hole of is made to correspond to the fuel injection hole of the fuel swirler or the fuel injection nozzle through the fuel passage partitioned by the partition plate,
A gas turbine combustor comprising an area-variable perforated plate capable of selectively closing each fuel passage hole of the fixed perforated plate. 2. The gas turbine combustor according to claim 1, wherein the perforated plate for varying the area is housed in a fuel supply chamber upstream of the fixed perforated plate. 3. The gas turbine combustor according to claim 1, wherein the area varying perforated plate is held by an actuator so as to be movable back and forth with respect to the fixed type perforated plate via a power transmission mechanism. 4. The gas turbine combustor according to claim 1, wherein the perforated plate for varying the area is rotatably supported by a drive motor via a power transmission mechanism. 5. The gas turbine combustor according to claim 3, wherein the actuator or the drive motor is operationally controlled by a controller according to the load operating state of the gas turbine and the type of fuel used.