JP2011085102A - Apparatus and method for cooling intake air of gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an apparatus and a method for cooling intake air of a gas turbine capable of enhancing the equipment reliability, and prolonging the lifetime regarding the maintenance. <P>SOLUTION: The apparatus for cooling intake air of the gas turbine includes a spray nozzle 8 provided in an intake air chamber 9, a cooling water supply system 16 in which a pump 17 for supplying cooling water for cooling the intake air is arranged to the spray nozzle 8, and an atomizing air system 25 for supplying pressurized air to the spray nozzle 8. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to a gas turbine intake air cooling device and a gas turbine intake air cooling method that improve power generation output by cooling air taken in by a gas turbine.

  The power generation output can be improved by spraying atomized water and cooling the air sucked by the gas turbine.

  As a technique related to this gas turbine intake air cooling, for example, a spray device is provided downstream of the silencer, and cooling water whose pressure has been increased by a pump is sprayed on the gas turbine intake air as water droplets having a particle size of 50 μm or less. Some of them have been lowered to increase the weight flow rate (see Patent Document 1).

  Also, there are some which use a plurality of positive displacement pumps having different outputs to adjust the spray flow rate, and control the flow rate of the cooling water sprayed by controlling the number of pumps (see Patent Document 2).

  FIG. 3 shows an example of gas turbine equipment using such a conventional gas turbine intake air cooling technique.

  The gas turbine equipment 50 includes an intake section 1, a gas turbine compressor 2, a gas turbine 3, and a generator 4 in order in the fluid flow direction.

  The intake section 1 includes an intake filter 5 and an intake chamber 9, and the intake chamber 9 includes an intake silencer 6 and a plurality of spray nozzles 7 a to 7 n in order in the fluid flow direction.

  In addition, a water supply pump system 11 connected to the water supply system is formed outside the intake portion 1. This water supply pump system 11 has a control valve 12 for adjusting the water supply flow rate, and water supply paths 13a, 13b,... 13n branched in multiple stages on the downstream side and connected to the spray nozzles 7a. .. 14n provided in the water supply paths 13a, 13b,... 13n, respectively, and downstream of these positive displacement pumps 14a, 14b,. Open / close valves 15a, 15b,... 15n.

  In the gas turbine equipment 50 having the above configuration, the intake air is dedusted by the intake filter 5 provided on the inlet side, then passes through the intake silencer 6 in the intake chamber 9, and is introduced toward the gas turbine compressor 2. The At that time, mist-like water is supplied from the water supply pump system 11 through the spray nozzles 7a.

  Here, in the water supply pump system 11, the positive displacement pumps 14a, 14b,... 14n pump water, and the flow rate is controlled by the on-off valves 15a, 15b,. 7n. In this case, the on-off valves 15a, 15b,.

  The cooling water thus controlled is ejected in a mist form from the spray nozzles 7a, 7b,... 7n, and cools the air. At this time, the water droplets are collected at the bottom of the intake chamber 9 by the action of gravity and are discharged out of the system as drain water.

  On the other hand, the cooled air is compressed by the gas turbine compressor 2 to become high temperature and high pressure, and the high temperature and high pressure air is supplied to a gas turbine combustor (not shown) together with fuel (not shown), where it is burned. Gas is generated, and the generated combustion gas is expanded by the gas turbine 3. At that time, the generator 4 is driven with the generated torque.

Japanese Patent No. 2877098 JP 2002-322916 A

  However, in the gas turbine equipment 50 described above, in order to prevent erosion to the gas turbine compressor 2 (when a particle collides, the surface is damaged due to mechanical damage due to cavitation or the like), the suction air is used. It was necessary to atomize the water droplet size to be atomized by pressure spraying. For this reason, an ultra-high pressure positive displacement pump 14 exceeding 20 MPa had to be used.

  In addition, in order to cover a wide flow range, multiple high-pressure pumps must be installed, and it is necessary to perform flow control by selecting the number of pumps to start while keeping the spray pressure constant at high pressure. It was.

  For this reason, in the conventional gas turbine equipment 50, the use of a plurality of positive displacement pumps increases the size of the entire system, and the device reliability decreases due to the high mechanical vibration and wear of sliding parts, which are disadvantages of the positive displacement type. In addition, there is a problem that the service life is reduced in terms of maintenance.

  The present invention can use a centrifugal pump having a low pump discharge pressure and a small vibration, improve equipment reliability, and improve maintenance life, and a gas turbine intake cooling method and gas turbine intake cooling method The purpose is to provide.

  Another object of the present invention is to provide a gas turbine intake air cooling device and a gas turbine intake air cooling method that can be downsized as a whole system.

  In order to achieve the above-mentioned object, a gas turbine intake air cooling device according to the present invention is a cooling water in which a spray nozzle provided in an intake chamber and a pump for supplying cooling water for intake air cooling to the spray nozzle are arranged. A supply system and an atomizing air system for supplying pressurized air to the spray nozzle are provided.

  Further, the gas turbine intake air cooling method of the present invention supplies intake water cooling water to a spray nozzle provided in the intake air chamber, and simultaneously supplies pressurized air to atomize the cooling water with the air. It is characterized by doing.

  ADVANTAGE OF THE INVENTION According to this invention, apparatus reliability can be improved and the lifetime in a maintenance can be improved.

  Further, according to the present invention, the entire system can be reduced in size.

BRIEF DESCRIPTION OF THE DRAWINGS Schematic which shows the structure of 1st Embodiment which applied the gas turbine inlet-air cooling apparatus which concerns on this invention to gas turbine equipment. Schematic which shows the structure of 2nd Embodiment which applied the gas turbine inlet-air cooling device which concerns on this invention to gas turbine equipment. Schematic which shows the structure which applied the conventional gas turbine intake-air cooling apparatus to gas turbine equipment.

(First embodiment)
FIG. 1 shows a configuration of a first embodiment in which a gas turbine intake air cooling device according to the present invention is applied to gas turbine equipment.

  The gas turbine equipment 10 includes an intake section 1, a gas turbine compressor 2, a gas turbine 3, and a generator 4 in order in the fluid flow direction in that the conventional gas turbine intake cooling shown in FIG. This is the same as the device 50.

  However, the gas turbine equipment 10 has a cooling water supply system 16 and an atomized air system (air spray system) 25 outside the intake section 1, and includes a spray nozzle 8 inside the intake chamber 9. Is different from the conventional gas turbine equipment 50.

  The cooling water supply system 16 measures a centrifugal pump 17 that supplies cooling water for air cooling into the intake chamber 1, a motor 18 that rotates the pump 17, a flow meter 19 that measures the flow rate of the cooling water, and the cooling water pressure. A pressure gauge 21 is provided.

  Further, the number of pumps 17 is one pump that satisfies the maximum flow rate and the maximum pressure, and in order to cover a wide flow range, the pump drive motor 18 is controlled by an inverter with a controller 22 having an inverter function. To be done.

  Further, the cooling water supply system 16 includes a bypass return system 24 having a pressure control valve 23 for controlling the pre-pressure of the spray nozzle 8 based on the cooling water pressure measured by the pressure gauge 21, and the rotational speed of the pump 17. And a controller 22 for controlling the pressure regulating valve 23 is provided.

  On the other hand, the atomizing air system 25 is provided with an air compressor 26 for supplying pressurized air.

  In the gas turbine facility 10, the pressurized cooling water supplied from the cooling water supply system 16 and the pressurized air supplied from the atomizing air system 25 are simultaneously injected from the spray nozzle 8 into the intake chamber 9. By supplying the air supplied from the atomizing air system 25 to the cooling water supplied from the cooling water supply system 16, the cooling water can be atomized at a low pressure. This makes it possible to use a centrifugal pump having a lower pump discharge pressure and less vibration than a conventional positive displacement pump.

  Further, the pressure before the spray nozzle 8 is pressure-controlled by a pressure control valve 23 provided in the bypass return system 24 at the outlet of the pump 17, and the excess flow rate is returned to the pump 17 inlet by the bypass return system 24.

  Further, since the pressure control valve 23 and the motor 18 of the pump 17 are controlled by the controller 22 in accordance with the cooling water flow rate so that the cooling water pressure injected from the spray nozzle 8 is constant, the pump power is reduced. It becomes possible to do.

  With this configuration, it is possible to provide an intake air cooling device that can be atomized even with a single low-pressure pump and that can cover a wide flow rate range. Thereby, device reliability can be improved and the lifetime in maintenance can be improved. Furthermore, the entire system can be reduced in size.

(Second Embodiment)
FIG. 2 shows a configuration of a second embodiment in which the gas turbine intake air cooling apparatus according to the present invention is applied to gas turbine equipment. In addition, the same code | symbol is attached | subjected to the structure same as 1st Embodiment, and the overlapping description is abbreviate | omitted.

  The gas turbine equipment 20 is different from the gas turbine equipment 10 shown in FIG. 1 in that an extraction system 27 extracted from the gas turbine compressor 2 is provided, and air pressurized by the extraction system 27 is supplied to the spray nozzle 8. Yes.

  In the gas turbine equipment 20 configured as described above, the pressurizing air compressor 26 as shown in FIG. 1 is not necessary.

  Therefore, according to this gas turbine equipment 20, besides having the same effect as the gas turbine equipment 10 of the first embodiment, the pressurized air required for atomization of the spray cooling water without installing an air compressor is provided. Can be supplied from the gas turbine compressor 2, the system can be further simplified.

DESCRIPTION OF SYMBOLS 1 ... Intake part, 2 ... Gas turbine compressor, 3 ... Turbine, 4 ... Generator, 5 ... Intake filter, 6 ... Intake silencer, 7, 8 ... Spray nozzle, 9 ... Intake chamber, 10, 20, 50 ... Gas Turbine equipment, 11 ... pump system, 12 ... control valve, 13 ... water supply path, 14 ... positive displacement pump, 15 ... open / close valve, 16 ... cooling water supply system, 17 ... pump, 18 ... motor, 19 ... flow meter, 21 ... pressure gauge, 22 ... controller, 23 ... pressure regulating valve, 24 ... bypass return system, 25 ... atomized air system, 26 ... air compressor, 27 ... extraction system

Claims (4)

A spray nozzle provided in the intake chamber;
A cooling water supply system provided with a pump for supplying cooling water for intake air cooling to the spray nozzle;
An atomizing air system for supplying pressurized air to the spray nozzle;
A gas turbine intake air cooling device comprising:   The cooling water supply system further includes a bypass return system branched from the downstream side of the pump and returned to the upstream side of the pump, and the bypass return system includes a pressure gauge disposed on the downstream side of the pump The gas turbine according to claim 1, further comprising: a pressure control valve that adjusts the pressure before the spray nozzle based on the pressure of the cooling water measured in step 1 and a controller that controls an inverter of the motor of the pump. Intake cooling system.   2. The gas turbine intake air cooling apparatus according to claim 1, wherein an air extraction line that extracts air pressurized from a gas turbine compressor and supplies the air to the spray nozzle is used as the atomizing air system.   A gas turbine intake air cooling method comprising: supplying cooling water for intake air cooling to a spray nozzle provided in an intake air chamber, and simultaneously supplying pressurized air to atomize the cooling water with the air.

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