JPH04214931A - Gas turbine facility - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to gas turbine equipment including an air compressor, a turbine, and a combustor with fuel nozzles.

0002

[Prior Art] Conventionally, in the above-mentioned type of gas turbine equipment, there has been provided a turbine cooling equipment for introducing a part of the air from the air compressor into the turbine to cool the turbine, and a part of the air from the air compressor. Fuel oil atomization equipment for introducing fuel oil into a fuel nozzle to atomize the fuel oil is known.

FIG. 3 shows a conventional gas turbine installation of this type. This gas turbine equipment includes a turbine cooling equipment 12
0 and fuel oil atomization equipment 121. The turbine cooling equipment 120 includes a discharge port 101a of the air compressor 101 and an air intake port 1 for cooling the moving and stationary blades of the turbine 102.
02a and 102b, and the pipe 10
Intercooler (intercooler) 1 installed in the middle of 7
04 and an air filtration device 105 provided at a downstream position of the intercooler 104 in the middle of the pipe line 107. A constrictor 106 is provided on the conduit 108 that bypasses the intercooler 104 to adjust the temperature of the cooling air. This turbine cooling equipment includes 350~
The discharge air of about 400°C is heated to 200°C by the intercooler 104.
Cooled to about 250°C and cleaned with an air filtration device 5,
Cooling air intake ports 102a and 102b of the turbine 102
to be introduced. In the figure, 104a is a cooling water pipe, 122a, 1
22b is an orifice for adjusting the flow rate, and 123 is a generator.

Further, in FIG. 3, a fuel oil atomization system 1
21 includes a conduit 115 for atomizing air connected from the discharge port 101b of the air compressor 101 to the air inlet 114a of the fuel nozzle 114 of the combustor 103. Conduit 11
5 is provided with an air filtration device 109, an air cooler 110, and an air compressor 111 in this order from the upstream position. A valve 113 for adjusting the bypass flow rate is provided in the pipe line 117 that bypasses the air cooler 110 and the air compressor 111.
and an orifice 124 are provided.

[0005] The air cooler 110 keeps the discharge air temperature of the air compressor 101 (approximately 350 to 400°C) at 8, which is a mechanically permissible temperature for an air compressor 111 made of ordinary materials.
Cool to about 0-100°C. The cooling water pipe 118 of the air cooler 110 has an air temperature of 8
A temperature control valve 112 is provided to adjust the temperature to approximately 0 to 100°C. The atomizing air introduced into the fuel nozzle 114 via the fuel oil atomizing equipment 121 is
The fuel oil supplied from 6 is atomized, contributing to improving the combustion efficiency within the combustor 103.

[0006] The amount of air introduced into the air compressor 101 is
When the ratio is 00, the amount of cooling air flowing into the turbine 102 is approximately 10, and the amount of air flowing into the fuel oil atomization equipment 121 is approximately 1. Further, the temperature of the air that has flowed into the air compressor 111 is increased during the pressure increasing process in the air compressor 111, and the temperature of the air discharged from the air compressor 111 is about 150 to 200 degrees Celsius.

In the figure, reference numeral 125 denotes a conduit through which fuel gas is introduced during fuel gas firing operation. Valve 113 during gas-fired operation
is fully opened, and the air discharged from the air compressor 111 is guided to the pipe line 117. Therefore, no air is introduced into the fuel nozzle 114. On the other hand, during fuel oil burning operation, the valve 113
is fully closed, and air discharged from the air compressor 111 is introduced into the fuel nozzle 114.

[0008]

[Problems to be Solved by the Invention] In the above-mentioned conventional gas turbine equipment, the turbine cooling equipment and the fuel oil atomization equipment are configured independently of each other. There were problems such as a large number of parts used for the same purpose, and complicated piping around the air compressor and turbine. In other words, (1) equipment for the same purpose, such as air filtration equipment and coolers, is installed in turbine cooling equipment 1.
20 and the fuel oil atomization equipment 121, the number of parts increases, making the gas turbine equipment complex and expensive. (2) Pipes 107, 11 from the discharge port of the air compressor 101
Since air is extracted separately through air compressor 5, air compressor 1
The piping around the 01 and the turbine 102 is complicated, making it difficult to perform the piping, which tends to have an adverse effect on maintenance. (3) Since the fuel oil atomization equipment is housed inside the turbine room, if the equipment that makes up the equipment becomes larger,
A problem arises in that storage becomes difficult. In particular, the larger the air filtration device 109 and the air cooler 110 become, the more difficult it becomes to store them.

The main object of the present invention is to eliminate the drawbacks of the prior art described above, and to provide gas turbine equipment with a small number of components and a simple piping system.

0010

[Means for Solving the Problems] According to the present invention, there is provided an air compressor having an air intake port and an air discharge port, a turbine having a cooling air intake port, a fuel oil inlet port and an atomizing air inlet port. In the gas turbine equipment, the turbine cooling equipment includes an air discharge port of an air compressor and a cooling air intake port of the turbine. an intercooler (intercooler) provided in the middle of the cooling air path, and an air filtration device provided in the middle of the cooling air path at a position downstream of the intercooler. , the fuel oil atomization equipment includes an atomization air passage branched from a position downstream of the air filtration device in the cooling air passage and connected to an atomization air inlet of the fuel nozzle; A compressor for atomizing air is provided in the middle of the atomizing air passage.

[0011] The fuel oil atomization equipment is provided in the middle of the atomization air passage and upstream of the atomization air compressor, and is configured to introduce the atomization air into the atomization compressor. It may include an air cooler to cool the air.

[0012] Further, the fuel nozzle includes a fuel gas inlet for introducing fuel gas during fuel gas firing operation, and the fuel oil atomization equipment is configured to control the atomization air in the atomization air passage. a connecting passage connecting a downstream position of the compressor for the atomizing air passage and an upstream position of the air cooler of the atomizing air passage, and a control valve means provided in the middle of the connecting passage; The valve means is fully opened during the fuel gas firing operation, and guides the air discharged from the compressor for the atomizing air to the upstream position of the air cooler through the connecting passage, while the valve means It can be configured to operate in a fully closed state during oil-fired operation.

Further, the fuel nozzle includes a fuel gas inlet for introducing fuel gas during fuel gas firing operation, and the fuel oil atomizing equipment is configured to inject the atomizing air into the atomizing air passage. a connecting passage connecting a downstream position of the compressor for the cooling air passage and an upstream position of the intercooler of the cooling air passage, and a control valve means provided in the middle of the connecting passage, the control valve Means is fully opened during fuel gas firing operation, and guides air discharged from the compressor for atomizing air to a position upstream of the intercooler via the connecting passage; It can also be configured to operate in a fully closed state during firing operation.

[0014]

[Operation] After the air extracted from the air discharge port of the air compressor of the gas turbine passes through the intercooler that constitutes the turbine cooling equipment and the air filtration device downstream thereof, a part of it is transferred to the cooling air intake of the turbine. Introduced at the entrance. The other part of the air after passing through the above intercooler and air filtration device is
branched from the downstream side of the air filtration device as atomizing air;
After being compressed by the atomizing air compressor, the atomizing air is introduced into the atomizing air inlet of the fuel nozzle of the combustor to atomize the fuel oil in the combustor. In the arrangement according to claim 2, the branched atomizing air is cooled in an air cooler before entering the atomizing air compressor.

[0015]

DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 shows a first embodiment of the present invention. The gas turbine equipment of this embodiment is for driving a generator 23, and includes an air compressor 1, a turbine 2, and a fuel nozzle 14.
combustor 3, turbine cooling equipment 20, and fuel oil atomization equipment 21.

The turbine cooling equipment 20 has a pipe 7 connecting the discharge port 1a of the air compressor 1 and the cooling air intake ports 2a, 2b of the turbine 2, and a cooling water pipe 4a provided in the middle of the pipe 7. It includes an intercooler (intercooler) 4 and an air filtration device 5 provided at a downstream position of the intercooler 4 in the middle of a pipe line 7 . A constrictor 6 is provided on a conduit 8 that bypasses the intercooler 4 to adjust the temperature of the cooling air. These points are similar to the conventional equipment shown in FIG.

The fuel oil atomizing equipment 21 is branched from a position downstream of the air filtering device 5 in the cooling air pipe line 7 and is connected to the fuel nozzle 1.
A pipe line 15 for atomizing air connected to the air inlet 14a of No. 4, and an air compressor 1 provided in the middle of the pipe line 15.
1.

[0018] In this gas turbine equipment, 350
Bleed air from the discharge port 1a of the air compressor 1 at a temperature of about 400°C is cooled to about 200 to 250°C by an intercooler 4, purified by an air filtration device 5, and used as cooling air for the turbine 2. It is introduced into the intake ports 2a and 2b. Further, a part of the air that has passed through the air filter device 5 is guided to the pipe line 15, and after being pressurized by the air compressor 11, is introduced into the fuel nozzle 14. The air introduced into the fuel nozzle atomizes the fuel oil introduced into the fuel nozzle 14 through the conduit 16 and the fuel oil inlet 14b of the fuel nozzle 14. The atomized fuel is guided to the combustor 3.

As in the case of the conventional equipment shown in FIG. 3, if the amount of air introduced into the air compressor 1 from the air intake port 1c of the air compressor 1 is 100, the amount of cooling air flowing into the turbine 2 is approximately 10. , the amount of air flowing into the fuel oil atomization equipment 21 is at a ratio of about 1. Therefore, the amount of air passing through the portion of the pipe line 7 from the air compressor 1 to the branching point 7a between the pipe line 7 and the pipe line 15, the intercooler 4, and the air filtration device 5 is smaller than that in the conventional case. It is necessary to increase the amount by about 10%. The distribution of the amount of air flowing into each device and each pipe is as follows:
It is set by taking into consideration the resistance of each device and pipeline to the passage of air, and appropriately determining the diameter of the pipeline. If the air amount distribution is inappropriate, orifices 22a, 22b of appropriate diameters are installed to adjust it to an appropriate value.

The above description has been made assuming that the gas turbine equipment performs only fuel oil burning operation. However, it is also possible to modify the gas turbine equipment so that the fuel oil-fired operation and the fuel gas-fired operation can be selected as appropriate. The portion so modified is shown in dashed lines in FIG. In this modified embodiment, the line 25 for fuel gas
A fuel gas inlet 14c connected to the fuel nozzle 14 is provided in the fuel nozzle 14. The fuel oil atomization equipment 21 includes a conduit 30 that connects a portion of the conduit 15 located downstream of the air compressor 11 and a portion of the conduit 7 located upstream of the intercooler 4 . A valve 13 for flow rate adjustment is provided in the middle of the conduit 30, and an orifice 24 is provided in the conduit 26 that bypasses the valve.

[0021] In the above modified embodiment, during fuel oil-fired operation, the flow of fuel gas through the pipe 25 is interrupted;
Fuel oil is introduced into the fuel nozzle 14 through the line 16 . Valve 13 is brought into a fully closed state. Therefore, the air compressor 11
The discharge air from the fuel nozzle 14 is introduced into the fuel nozzle 14. The orifice 24 is provided for the same purpose as the orifices 22a and 22b, which is to adjust the amount of air introduced into the fuel nozzle 14 to an appropriate value.

During fuel gas firing operation, the flow of fuel oil through the pipe line 16 is blocked, while fuel gas is introduced into the fuel nozzle 14 through the pipe line 25. Valve 13 is left fully open. Therefore, the air discharged from the air compressor 11 does not flow toward the fuel nozzle 14, which has a large resistance, but is introduced into the pipe line 30. The introduced air passes through an intercooler 4 and an air filtration device 5, and part of it passes through the cooling air intake 2a of the turbine 2,
2b, and a portion passes through the pipe 15, the compressor 11, and then circulates through the pipe 30 again.

The operation of the valve 13 described above and the introduction and shutoff of fuel from the pipes 16 and 25 to the fuel nozzle 14 are automatically performed depending on whether fuel oil burning operation or fuel gas burning operation is selected. It will be held on.

As described above, in the first embodiment, the portion of the pipe line 7 from the air compressor 1 to the branching point 7a between the pipe line 7 and the pipe line 15, the intercooler 4, and the air filtration device are The amount of air passing through 5 increases by about 10% compared to the conventional case. Therefore, it is possible that the above-mentioned portions of the conduit 7, the intercooler 4 and the air filtration device 5 are somewhat larger than the conventional system of FIG. However, this embodiment provides the following advantages. (1) Since air for turbine cooling and air for fuel oil atomization can be extracted from the air compressor 1 through a common pipe line, piping can be simplified. (2) Air filtration device exclusively for air for fuel oil atomization (1 in Figure 3)
09), and only one air filtration device is required. Therefore, it is possible to simplify the arrangement of equipment in the turbine chamber, save space, and reduce costs.

FIG. 2 shows a second embodiment of the invention. In this embodiment, an air cooler 10 is provided at a position upstream of a fuel oil atomizing air compressor 11 in a pipe line 15 for fuel oil atomizing air in the fuel oil atomizing equipment indicated by the reference numeral 21A. ing. The air cooler 10 exits the air filtration device 5 and enters the conduit 1
The temperature of the air guided to 5 (about 200 to 250℃) is
80 to 1, which is the mechanically permissible temperature of a normal air compressor 11.
Cool to about 00°C. The cooling water pipe 18 of the air cooler 10 has an air temperature of 80 to 100°C at the outlet of the cooler 10.
A temperature control valve 12 is provided to adjust the temperature. The temperature of the air flowing into the air compressor 11 is increased during the pressure increasing process in the air compressor 11, and the temperature of the air discharged from the air compressor 11 is about 150 to 200°C.

The portions of the gas turbine equipment of the second embodiment that have been modified so that fuel oil-fired operation and fuel gas-fired operation can be appropriately selected are shown by chain lines in FIG. In this modification, the fuel oil atomization equipment 21A includes a pipe line 15
, the part located downstream of the air compressor 11 and the pipe line 15
It includes a pipe line 30A that connects the air cooler 10 to a portion located at an upstream position of the air cooler 10. A valve 13 for flow rate adjustment is provided in the middle of the pipe 30A, and an orifice 24 is provided in the pipe 26 that bypasses the valve 13.

The configuration of the second embodiment other than the above-mentioned points is the same as that of the first embodiment described above, so the explanation thereof will be omitted. In Figures 1 and 2, like parts are designated with like reference numerals. As in the case of the first embodiment, the valve 13 of the second embodiment is fully closed during fuel oil burning operation, and is fully open during fuel gas burning operation.

The second embodiment provides the same advantages as the first embodiment described above. In addition, the following advantages can also be obtained: (1) In the conventional equipment shown in FIG. 3, high-temperature air of about 350 to 400°C is introduced into the cooler 110, whereas in the second embodiment, air is cooled to about 200 to 250°C by the intercooler 4. The air is introduced into the air cooler 10 through the conduit 15. Therefore, the materials used for the pipe line 15, air cooler 10, valve 12, etc. can be made of lower grade materials. (2) As mentioned above, since the temperature of the air introduced into the air cooler 10 decreases, the amount of heat exchanged in the air cooler 10 decreases to 1/2 to 1/3 of the conventional amount. Therefore, the size of the air cooler can be significantly reduced compared to conventional ones, which greatly contributes to cost reduction and maintenance space in the turbine chamber. (3) In the second embodiment, air cooled by the air cooler 10 is introduced into the air compressor 11. Therefore, the air compressor 11 does not need to be made of expensive parts made of materials that can withstand high temperatures. Further, it is possible to avoid problems such as carbonization of the fuel due to air having an excessively high temperature being introduced into the fuel nozzle 14.

[0029]

[Effects of the Invention] According to the present invention, the following effects can be obtained. (1) Since air for turbine cooling and air for fuel oil atomization can be extracted from the air compressor through a common pipe line, piping can be simplified. (2) There is no need to provide an air filtration device exclusively for air for fuel oil atomization, and only one air filtration device is required. Therefore, it is possible to simplify the arrangement of equipment in the turbine chamber, save space, and reduce costs.

Particularly, when the configuration according to claim 2 is adopted, the following effects (3), (4), and (5) can be obtained in addition to the above effects. (3) Since the air cooled by the intercooler is introduced into the air cooler for cooling the air introduced into the compressor for atomizing air, the materials used in the air cooler It is possible to lower the grade and lower the price. (4) Since the temperature of the air introduced into the air cooler is lowered by the intercooler as described above, the amount of heat exchanged in the air cooler is lower than that of the atomizing air cooler in the prior art. decreases to 1/2 to 1/3 of Therefore, the size of the air cooler can be significantly reduced compared to conventional ones, which greatly contributes to cost reduction and maintenance space in the turbine chamber. (5) Air cooled by an air cooler 10 provided upstream of the air compressor in the atomizing air passage is introduced into the air compressor for atomizing air. Therefore, the air compressor does not need to be made of expensive parts made of materials that can withstand high temperatures. Further, it is possible to avoid problems such as carbonization of the fuel due to excessively high temperature air being introduced into the fuel nozzle.

[Brief explanation of the drawing]

FIG. 1 is a schematic diagram showing gas turbine equipment according to a first embodiment of the present invention.

FIG. 2 is a schematic diagram showing gas turbine equipment according to a second embodiment of the present invention.

FIG. 3 is a schematic diagram showing conventional gas turbine equipment.

[Explanation of symbols]

1,101: Air compressor 2,102: Turbine 3,103: Combustor 4,104: Intercooler 4a, 104a: Cooling water pipe 5,105,109: Air filtration device 110: Air cooler 11,111: Fog Compressor 14, 114 for chemical air
: Fuel nozzles 16, 116: Fuel oil supply pipes 18, 118: Cooling water pipes 20, 120: Turbine cooling equipment 21, 121: Fuel oil atomization equipment 2a, 2b, 102a, 102b: Cooling air intake port 25
, 125: Fuel gas supply pipe

Claims (6)

[Claims] 1. An air compressor having an air intake and an air discharge, a turbine having a cooling air intake, and a combustor including a fuel nozzle having a fuel oil inlet and an atomizing air inlet. , a turbine cooling facility, a fuel oil atomization facility,
In the gas turbine equipment, the turbine cooling equipment includes a cooling air passage connecting an air discharge port of the air compressor and a cooling air intake of the turbine, an intercooler provided in the middle of the cooling air passage, an air filtration device provided in the middle of the cooling air passage at a downstream position of the intercooler, and the fuel oil atomization equipment is branched from the downstream position of the air filtration device in the cooling air passage. The fuel nozzle is characterized by comprising an atomizing air passage connected to an atomizing air inlet of the fuel nozzle, and a compressor for atomizing air provided in the middle of the atomizing air passage. gas turbine equipment. 2. The fuel oil atomization equipment is provided at a position upstream of the atomization air compressor in the middle of the atomization air passage, and the fuel oil atomization equipment is provided at a position upstream of the atomization air compressor. 2. A gas turbine installation as claimed in claim 1, including an air cooler for cooling air introduced into the gas turbine. 3. The fuel nozzle includes a fuel gas inlet for introducing fuel gas during fuel gas firing operation, and the fuel oil atomization equipment is configured to inject the atomization air into the atomization air passage. a connecting passage connecting a downstream position of the compressor for the atomizing air passage and an upstream position of the air cooler of the atomizing air passage;
and a control valve means provided in the middle of the connecting passage, the control valve means being fully opened during fuel gas firing operation to direct the air discharged from the compressor for the atomizing air into the atomizing air. 3. The gas turbine equipment according to claim 2, wherein the air is guided to an upstream position of the air cooler via a connecting passage, and is operated in a fully closed state during fuel oil burning operation. 4. The fuel nozzle includes a fuel gas inlet for introducing fuel gas during fuel gas firing operation, and the fuel oil atomization equipment is configured to control the atomization air in the atomization air passage. a connecting passage connecting a downstream position of the compressor for the cooling air passage and an upstream position of the intercooler of the cooling air passage;
and a control valve means provided in the middle of the connecting passage, the control valve means being fully opened during fuel gas firing operation to direct the air discharged from the compressor for the atomizing air into the atomizing air. 2. The gas turbine equipment according to claim 1, wherein the gas turbine equipment is led to an upstream position of the intercooler through a connecting passage, and is operated so as to be in a fully closed state during fuel oil burning operation. 5. The fuel oil atomization equipment includes a bypass passage provided in the connecting passage and bypassing the control valve means, and a flow rate regulating orifice provided in the bypass passage. Gas turbine equipment. 6. The fuel oil atomization equipment includes a bypass passage provided in the connecting passage and bypassing the control valve means, and a flow rate regulating orifice provided in the bypass passage. Gas turbine equipment.