JPS62102030A - Gas turbine combustion unit - Google Patents

Abstract

PURPOSE:To provide a stable combustion in response to a loaded condition or a replacement use of fuel having different heating amount by a method wherein porous plate whose area can be varied is provided in order to make a selective closable state of each of fuel passage holes in fixed porous plate. CONSTITUTION:Porous plate 38 having variable area has fuel passage holes 39. Fuel passage holes 39 correspond to fuel passage holes 31 of fixed type porous plate 29 and the remaining fuel passage holes 30 can be closed with porous plate 38 of which area can be varied. When a gas turbine is started, or when a low load operation is performed, or when a fuel having a high heating calorie is to be used, an actuator 41 is operated to cause the porous plate 38 for variable area to approach or fixed tot he fixed type porous plate 29 to close the fuel passage holes 30 of the fixed type porous plate 29. Therefore, a pressure difference across the injecting holes of a fuel swirller 25 is sufficiently kept and a non-stable combustion is prevented. In case that large amount of fuel is flowed or when fuel having less heating calorie is to be used, the porous plate 38 of which area can be varied is retracted from the fixed type porous plate 29 beyond a fuel flowing port 37 and then all of the fuel passage holes 30 and 31 of the fixed type porous plate 29 are opened.

Description

DETAILED DESCRIPTION OF THE INVENTION [Technical Field of the Invention] The present invention relates to a gas turbine combustor used in a gas turbine power plant, and more particularly to a gas turbine combustor in which the fuel flow area can be adjusted and controlled.

[Technical fIf11 of the invention and its problems] In a gas turbine power plant, a gas turbine combustor is provided between a compressor and a gas turbine, and the discharge air compressed by the drive of the compressor is used as combustion air. guided to the gas turbine combustor. The guided combustion air mixes with fuel injected from the fuel injection device in the gas turbine combustor and burns, resulting in high-temperature combustion gas. This combustion gas is guided from the combustor transition piece to the gas turbine, where it performs work.

A conventional gas turbine combustor is constructed as shown in FIGS. 9 and 10, and includes a liner outer cylinder 1 and a live inner cylinder 2.
A combustor main body 3 having a double cylinder structure is formed from the above. The 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. The air is injected from the air swirler 5 into the combustion chamber 6 formed within 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 a fuel swirler 8 at the tip, and is mixed with combustion air within the combustion chamber 6. Mixed and burned.

The gas turbine combustor shown in Figure 9 has an air swirler.
5 is disposed on the outer peripheral side of the fuel swirler 8 of the fuel injection device 7, and in the gas turbine combustor shown in FIG. It is a type of In the latter gas turbine combustor, the fuel injection device 7 is internally divided into a fuel passage and a fuel air flow passage by a partition plate.

By the way, a conventional fuel injection device for a gas turbine combustor has a constant fuel injection opening area, and the fuel flow passage area is always constant. For this reason, when the fuel flow rate changes over a wide range from a small flow rate to a large flow rate, in a conventional gas turbine combustor, the pressure difference before and after the fuel injection hole is small in the small fuel flow range, and this fuel pressure difference is small. As a result, fuel is not injected stably, and unstable combustion such as fuel vibration and misfires may occur.

In recent years, fuels have been diversified in consideration of fuel economy, and fuels with high calorific value are now being used. When fuels with greatly different heat generation R are used in one gas turbine, the range of variation in fuel flow rate becomes even larger. At the time of fuel flow, a sufficient pressure difference between the front and rear of the fuel injection hole could not be ensured, and there was a risk that unstable combustion would occur.

(Object of the Invention) The present invention has been made in consideration of the above-mentioned circumstances, and it adjusts and controls the fuel injection area of the fuel injection device according to the load condition of the gas turbine or the switching use of fuels with different calorific values, and The objective is to provide a gas turbine combustor that can achieve stable combustion and handle the diversification of fuels.

[Summary of the invention]

In order to achieve the above-mentioned object, the present invention provides a gas turbine combustor equipped with a fuel injection device in the combustor main body.
The fuel injection device has a fixed perforated plate having a plurality of fuel passage holes in a cylindrical casing, and each fuel passage hole of the fixed perforated plate is connected to a fuel swirler through a fuel passage divided by a partition plate. - Alternatively, a variable area perforated plate is installed which corresponds to the fuel injection hole of the fuel injection nozzle and can selectively close each fuel passage hole of the fixed perforated plate.

[Embodiments of the invention]

DESCRIPTION OF THE PREFERRED EMBODIMENTS 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 in J3 indicates a gas turbine combustor used in a gas turbine power generation blunt. Compressed air discharge 1? In the member 13, there are a plurality of lines, for example, one line, along the circumferential direction.
It can accommodate 0 or 14 pieces. Gas turbine combustor 1
0 is a liner outer cylinder 15 and a liner inner cylinder 16 with a double cylinder structure.
The liner inner cylinder 16 and outer cylinder 15 constitute a combustor main body 17.

The annular space between the liner outer cylinder 15 and the liner inner cylinder 16 is formed as a flow path 18 for supplying combustion air, as shown in FIGS. It is inverted at the tip (front end) of the main body 17 and communicated with the combustion chamber 21 inside the liner 16 through an air swirler 20.

On the other hand, a fuel injection device 2 is located at the center of the front end of the combustor body 17.
3 is provided, and fuel supplied by this fuel injection device 23 through a fuel supply pipe 24 is injected into the combustion chamber 21 via a fuel swirler 25. In this combustion chamber 21, the fuel is combined with combustion air and combusted, resulting in high-temperature combustion gas. This combustion gas is guided to the gas turbine 12 through the combustor n26 (see FIG. 3), and drives the gas turbine 12 to perform work.

By the way, the fuel injection device 23 includes a cylindrical casing 28 held in the combustor main body 17, and this cylindrical casing 2
A fixed perforated plate 29 is fixed and housed within the housing 8 . The fixed perforated plate 29 is provided with a large number of fuel passage holes 30.31 independently in the circumferential direction as shown in FIGS. 4(A) and 5(A).The shape of each fuel passage hole 30.31 is A plurality of partition plates 33 are provided downstream of the fixed perforated plate 29, and the partition plates 33 allow a fuel passage 35 to be connected to each fuel injection hole 34 of the fuel swirler 25.
The fuel passage holes 30 and 31 provided in the fixed perforated plate 29 correspond one-to-one to the fuel injection holes 34 of the fuel swirler 25 via the fuel passages 35. Note that a fuel injection nozzle can be similarly applied in place of the fuel swirler 25, so the fuel swirler 25 is used as a concept that includes the fuel injection nozzle.

Further, the upstream side of the fixed perforated plate 29 is the fuel supply chamber 3.
6, and a fuel inlet boat 37 opens into this supply chamber 36. Fuel supply 1? The chamber 36 also serves as a cylinder chamber for a variable fuel injection area perforated plate 38 that can be brought into close contact with the fixed perforated plate 29 so as to be movable and retractable. The area variable porous plate 38 has, for example, fuel passage holes 39 shown in FIG. 5(B). The fuel passage holes 39 correspond to the fuel passage holes 31 of the two fixed porous plates, and the remaining fuel passage holes 3° can be opened with a variable area porous plate 38. Therefore, the number of fuel passage holes 39 provided in the variable area perforated plate 38 is greater than the number of fuel passage holes 39 provided in the variable area perforated plate 38.
is set to be smaller than the number by a predetermined ratio depending on the operating conditions of the gas turbine or the heat generation characteristics of different fuels.

The area variable perforated plate 38 is connected to an actuator 41 via an actuating rod 40 as a power transmission mechanism, and the operation of the actuator 41 causes the fuel supply boat 37 to
I am forced to reciprocate by exceeding the limit. The actuator 41 receives an actuator operation signal from the controller 42 and is controlled to operate. The controller 42 is adapted to control the movement position of the actuator 41 in response to a signal representative of the timing of changing the area of the fuel passage, such as a gas turbine load signal or a fuel switching signal.

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

When starting up the gas turbine, operating at a low load, or using high heat generating fuel, as shown in FIG. Bring it close to and in close contact with it. As a result, the fuel injection device 23 is adjusted so that the fuel injection area becomes small, and the fuel passage hole 30 of the fixed perforated plate 29 is closed.

Then, the fuel guided into the supply chamber 36 of the fuel injection device 23 is transferred from the common fuel passage holes 39 and 31 of the variable area perforated plate 38J3J and the fixed perforated plate 29 to the fuel flow path 3.
5 to the fuel swirler 25, and the fuel swirler 25
25 into the combustion chamber 21, the fixed perforated plate 2
Since the fuel passage hole 30 of No. 9 is closed, fuel does not flow therethrough, and as a result, the fuel injection area at the fuel swirler 25 is reduced. By making the fuel injection area of the fuel injection device 23 adjustable, a sufficient differential pressure can be secured before and after the injection hole of the fuel swirler 25 even when the fuel flow is minute at 11 o'clock.1. Unstable combustion such as combustion vibration and blow marks can be prevented. The combustion stability improves as the number of holes provided in the fuel swirler 25, the two fixed perforated plates, and the receptive perforated plate 38 increases.

On the other hand, when flowing fuel in multiple stages during rated load operation of the gas turbine, or when using fuel with a small calorific value, the fuel 13 + injection rjJ device 23 has a large fuel injection (g).
Area is required. In this case, the actuator 41 is actuated as shown in FIG.
8 is retracted from the fixed perforated plate 29 beyond the fuel inlet boat 37, and each fuel passage hole 30.31 of the fixed perforated plate 29 is
are all released. Therefore, the fuel supplied into the fuel supply chamber 36 passes through all the fuel passages 35 and is injected into the combustion chamber 21 from the fuel swirler 25. Therefore, the fuel injection pressure difference in the fuel swirler 25 is maintained at an appropriate value, and stable injection is achieved.

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

A gas turbine combustor 10A shown in this modification has a combustion air swirler 2OA and a fuel swirler (which may be a fuel injection nozzle) 25A integrated into a fuel injection device 23A.

The gas turbine combustor 10A has a fixed perforated plate 29A fixed and housed within the cylindrical casing 28, the perforated plate 29A1. : A perforated area variable plate 38A is rotatably housed adjacent to the plate. The variable area 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.
6, the variable area perforated plate 38A is rotated. The rotation of the drive motor 46 is controlled by the controller 42A.

The fuel passage holes 48 and 49 of the variable area perforated plate 38A are the seventh
As shown in Figure (A), there are two types of fuel passage holes, for example, fuel passage holes 48 with a center angle θ and fuel passage holes 49 with a center angle 2θ, which are arranged alternately at predetermined intervals in the circumferential direction. 48.49 is the central angle θ formed in the fixed perforated plate 29A.
It corresponds to each fuel passage hole 30A, 31A. By rotating the variable area perforated plate 38A by an angle θC by the drive motor 46, the fixed perforated plate 29A
is configured to selectively take a position where each of the fuel passage holes 30A, 31Δ is open and a position where some of the fuel passage holes 30A are closed.

Further, on the downstream side of the fixed perforated plate 29A, as shown in FIG.
5A and a fuel air flow path 51, which are arranged independently and alternately. The fuel passages 35A are each fuel passage hole 30A of the fixed perforated plate 29A.

31A to fuel swirler 25A fuel injection hole 34A and 1
We are matching them on a one-to-one basis.

On the other hand, the combustion air flow path 51 has an inlet opening 1 m in the circumferential side, and the combustion air flowing in from this inlet is passed through an air swirler.
The fuel is injected into the combustion chamber 21 from 20A. Therefore, in the fuel injection device 23A facing the combustion chamber 21, the fuel injection holes 34A of the fuel swirler 25A and the combustion air injection holes 52 of the air swirler 20A are aligned, as shown in FIG. 7(C). provided.

Now, when starting up the gas turbine, operating at low load, or using fuel with high heat generation m, an operation control signal is given to the controller 42A to rotationally drive the drive motor 46, and the drive motor 46 is rotated via the power transmission device. The area variable porous plate 38A is rotated by a predetermined angle.

That is, the area variable porous plate 38A is moved counterclockwise to the seventh
It is rotated by a predetermined angle θ from the state shown in Figure (A).

As a result, the fuel passage hole 4 opening at the center angle 2θ
9 indicates that even if the variable area perforated plate 38Δ rotates by an angle θ, the fuel passage hole 31A provided in the fixed perforated plate 29A
will not be blocked. However, this fuel passage hole 31
The fuel passage hole 30A adjacent to A is completely closed. Therefore, the area variable porous plate 38A has fuel passage holes 4
Since a large number of holes having the same shape as B and /19 are installed according to a predetermined area reduction rate, the area variable perforated plate 38
It is possible to reduce the fuel injection area by a predetermined amount by rotating the angle O. ? This prevents unstable combustion such as combustion vibrations and misfires.

Next, if the fuel is to flow more frequently or if a fuel with a small calorific value is used, the area variable perforated plate 38△ can be rotated by an angle of θ1 in the direction of time, as shown in FIG. 7 (A>). Therefore, each fuel passage hole 30A, 3 installed in the fixed perforated plate 29A is arranged.
1A is completely opened without being blocked by the area variable perforated plate 38A. Therefore, a sufficiently large fuel passage area is ensured, and stable combustion can be achieved by the ideal fuel injection device as designed.

A3. In the embodiments of the present invention, the shapes and sizes of the fuel passage holes formed in the fixed perforated plate and the variable area perforated plate can be variously prepared and are not limited to those shown in FIGS. 5 and 7. .

[Effect beam of invention]

As described above, the gas turbine combustor according to the present invention has
A fixed perforated plate having a plurality of fuel passage holes is provided in the cylindrical casing of the fuel injection device, and the fuel swirler or fuel is inserted into the fixed perforated plate through the fuel passage defined by the partition plate. In addition to corresponding to the fuel injection holes of the injection nozzle, a variable area perforated plate that can selectively close each fuel injection hole of the fixed perforated plate was installed. Adjustments can be made to suit the flow rate and type of fuel, ensuring stable and efficient combustion throughout the entire operating range of the gas turbine, and stably burning fuels with different calorific values in one gas turbine combustor. This enables diversification of fuels and flexible operation of gas turbines.

[Brief explanation of drawings]

FIG. 1 and FIG. 2 show a gas turbine fuel vt according to the present invention.
FIG. 3 is a diagram showing the installed state of the gas turbine combustor, and FIG. 4(A) is a fixed perforated plate of a fuel injection device incorporated into the gas turbine combustor. 4(B) is a diagram showing the fuel swirler of the fuel injection device, and FIGS. 5(A) and (B) are the fixed perforated plate of the fuel injection device. FIG. 6 is a diagram showing a modified example of the gas turbine combustor according to the present invention, and FIG. 7(A) is a diagram showing a modified example of the gas turbine combustor according to the present invention. (B) and (C) are views respectively showing a variable area perforated plate, a fixed perforated plate, and a swirler for combustion air and fuel of the fuel injection device incorporated in the gas turbine combustor of Fig. 6;
FIG. 8 is a diagram showing the structure of the fixed perforated plate downstream of the fuel injection device d, and FIGS. 9 and 10 are diagrams showing a conventional gas turbine combustor, respectively. 10... Gas turbine combustor, 11... Compressor, 1
2... Gas turbine, 15... Liner outer cylinder, 16
...liner inner cylinder, 17...combustor body, 18...
・Combustion air flow path, 20.20A...air swirler
121... Combustion chamber, 23... Fuel injection device, 2 J
*2 b△・・・Fuel swirler-129, 29A・
・・Fixed perforated plate, 30.31.30A, 31A...
Fuel v1 passage hole, 33°50...partition plate, 34.34A
...Fuel injection hole, 35... Fuel passage, 36... Fuel supply chamber, 38.38△... Porous plate for variable area, 41... Actuator, 42, /12Δ... Controller, 4G... Drive motor, 51... Combustion air flow path. Applicant's agent Hisato Hatano ＼ Bancer 3 Figure No. 4 Yoke (E) (,4) Certain 5 Artwork 6th item (,4) (B)
<(:) Certain 7 ■ Certain 6 countries

Claims (1)

[Claims] 1. In a gas turbine combustor equipped with a fuel injection device in the combustor body, the fuel injection device is provided with a fixed perforated plate having a plurality of fuel passage holes in a cylindrical casing, and the fixed perforated plate has a plurality of fuel passage holes. Each fuel passage hole of the fixed type perforated plate is made to correspond to a fuel injection hole of a fuel swirler or a fuel injection nozzle through a fuel passage divided by a partition plate, and each fuel passage hole of the fixed type perforated plate is selectively connected to the fuel injection hole of a fuel swirler or a fuel injection nozzle. A gas turbine combustor characterized in that a variable area perforated plate that can be closed is installed in the gas turbine combustor. 2. The gas turbine combustor according to claim 1, wherein the variable area perforated plate is housed in the fuel supply chamber upstream of the fixed perforated plate. 3. The gas turbine combustor according to claim 1, wherein the variable area perforated plate is held by an actuator so as to be movable relative to the fixed perforated plate via a power transmission mechanism. 4. The gas turbine combustor according to claim 1, wherein the variable area perforated plate is rotatably supported by a drive motor via a power transmission mechanism. 5. The gas turbine combustor according to claim 3 or 4, wherein the actuator or the drive motor is operated and controlled by a controller according to the load operating state of the gas turbine and the type of fuel used.