WO2019167276A1 - Système de stockage de gaz combustible pour turbine à gaz et procédé d'alimentation de turbine à gaz en gaz combustible - Google Patents

Système de stockage de gaz combustible pour turbine à gaz et procédé d'alimentation de turbine à gaz en gaz combustible Download PDF

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Publication number
WO2019167276A1
WO2019167276A1 PCT/JP2018/008130 JP2018008130W WO2019167276A1 WO 2019167276 A1 WO2019167276 A1 WO 2019167276A1 JP 2018008130 W JP2018008130 W JP 2018008130W WO 2019167276 A1 WO2019167276 A1 WO 2019167276A1
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Prior art keywords
fuel gas
temperature
gas turbine
gas
storage tank
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PCT/JP2018/008130
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English (en)
Japanese (ja)
Inventor
和徳 藤田
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三菱日立パワーシステムズ株式会社
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Priority to PCT/JP2018/008130 priority Critical patent/WO2019167276A1/fr
Publication of WO2019167276A1 publication Critical patent/WO2019167276A1/fr

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems

Definitions

  • the present invention relates to a fuel gas storage system of a gas turbine that supplies fuel gas to the gas turbine in an emergency in a power plant equipped with the gas turbine, and a fuel gas supply method to the gas turbine.
  • GTCC gas turbine combined cycle power plant
  • the gas turbine combined cycle power plant may include a fuel gas storage system that stores a predetermined amount of fuel gas for continuing operation of the gas turbine and supplies the fuel gas when necessary.
  • fuel gas storage system for a gas turbine, for example, there is one described in Patent Document 1 below.
  • the present invention can be switched to the fuel oil-fired operation without causing the gas turbine to stop emergencyly.
  • the fuel gas stored in the storage system is discharged, the pressure drop in the fuel gas supply line is suppressed within an allowable range, and the storage system for continuing the gas turbine operation is focused.
  • Such a fuel gas storage system for a gas turbine needs to supply a fuel gas at a predetermined pressure to the gas turbine. Sometimes the fuel gas in the storage tank is depressurized and supplied to the gas turbine.
  • the fuel gas storage system of the gas turbine needs to supply fuel gas at a predetermined temperature or more to the gas turbine, but in the conventional system, after the storage tank is pressurized to a predetermined pressure, it is stored closed. During that time, the temperature of the fuel gas in the storage tank is approximately the same as the ambient (atmosphere) temperature. Therefore, when releasing the fuel gas from the storage tank, the temperature of the fuel gas that has decreased in temperature is increased by reducing the pressure. Supply to gas turbine. In that case, a temperature raising equipment for raising the temperature of the fuel gas to a predetermined temperature is required. Conventionally, such temperature raising equipment is installed (stored) on a system for releasing the gas in the storage tank to the fuel gas supply line.
  • the equipment cost is increased.
  • the fuel gas is released, it is necessary to quickly raise the temperature of the fuel gas with the temperature raising equipment and supply it to the gas turbine.
  • the present invention solves the above-described problems, and suppresses an increase in equipment cost and operation cost, and at the same time, can quickly supply a fuel gas having a pressure and temperature necessary for the gas turbine, and a fuel gas storage system for a gas turbine.
  • An object of the present invention is to provide a method for supplying fuel gas to a gas turbine.
  • a fuel gas storage system for a gas turbine stores fuel gas in the fuel gas storage system for a gas turbine that supplies stored fuel gas from an auxiliary fuel gas supply line to the gas turbine.
  • a storage tank a circulation line for circulating the fuel gas stored in the storage tank to the outside, a circulation flow rate adjusting valve provided in the circulation line, a compressor provided in the circulation line for boosting the fuel gas,
  • a temperature controller for adjusting a temperature of the fuel gas which is provided in the circulation line and is heated by being pressurized by the compressor; and a target storage temperature in which a temperature of the fuel gas stored in the storage tank is set in advance.
  • a controller for controlling the temperature regulator so as to be maintained in the region.
  • a pressure reducing valve is provided in the auxiliary fuel gas supply line, and a lower limit temperature in the target storage temperature region is a fuel supply lower limit temperature supplied to the gas turbine. It is characterized in that the temperature is equal to or higher than a temperature obtained by adding a temperature drop that falls when the gas passes through the pressure reducing valve.
  • the fuel gas stored in the storage tank is depressurized by the pressure reducing valve and supplied from the auxiliary fuel gas supply line to the gas turbine, so the temperature of the fuel gas decreases.
  • the lower limit temperature in the target storage temperature region is set to a temperature obtained by adding the drop temperature to the target supply temperature, the fuel gas at an appropriate temperature can be supplied to the gas turbine.
  • the storage tank is a hollow long tube having a predetermined length
  • the circulation line has one end at an inlet portion on one side in the longitudinal direction of the storage tank. It is connected, The other end part is connected with the exit part of the other side of the longitudinal direction in the said storage tank, It is characterized by the above-mentioned.
  • the storage tank is a hollow long tube, one end of the circulation line is connected to the inlet of the storage tank, and the other end is connected to the outlet of the storage tank. It circulates through the circulation line comprised by this, stabilization of the gas property in a storage tank and uniform heating can be aimed at, and generation
  • the storage tank is disposed so as to be inclined such that the position of the outlet portion is lower than the position of the inlet portion, and a drain line is connected to the outlet portion side. It is characterized by that.
  • the storage tank is inclined and the drain line is connected to the outlet side, even if drain is generated in the storage tank, the drain flows to the outlet side and is discharged to the outside from the drain line. Therefore, the retention of the drain in the storage tank can be suppressed.
  • the storage tank is disposed so as to be inclined such that the position of the outlet portion is higher than the position of the inlet portion, and a drain line is connected to the inlet portion side. It is characterized by that.
  • the storage tank is inclined and the drain line is connected to the inlet side, so even if drain is generated in the storage tank, the drain flows into the inlet and is discharged from the drain line to the outside. In addition, the retention of drain in the storage tank can be suppressed.
  • a fuel gas source is connected to the gas turbine via a main fuel gas supply line, and the auxiliary fuel gas supply line is connected from the storage tank to the circulation control valve and the The compressor and the temperature controller are bypassed and connected to the main fuel gas supply line.
  • the fuel gas stored in the storage tank is supplied from the auxiliary fuel gas supply line to the gas turbine regardless of the operation of the flow rate control valve, compressor and temperature controller. can do.
  • the auxiliary fuel gas supply line also serves as at least a part of the circulation line.
  • a fuel gas source is connected to the gas turbine via a main fuel gas supply line, and the auxiliary fuel gas supply line is connected from the storage tank to the main fuel gas supply line. It is characterized by being.
  • the auxiliary fuel gas supply line is directly connected from the storage tank to the main fuel gas supply line, the reliability can be improved.
  • the fuel gas supply method to the gas turbine of the present invention is a method of circulating the fuel gas stored in the storage tank to the outside in the fuel gas supply method to the gas turbine for supplying the stored fuel gas to the gas turbine. Boosting the fuel gas when the fuel gas circulates and adjusting the temperature so that the temperature of the fuel gas is maintained within a preset target storage temperature range; and the main fuel to the gas turbine And a step of stopping the circulation of the fuel gas when the gas supply system is abnormal and depressurizing the fuel gas stored in the storage tank and supplying it to the gas turbine through an auxiliary supply line. .
  • the fuel gas stored in the storage tank is depressurized and supplied from the auxiliary fuel gas supply line to the gas turbine. Since the temperature of the fuel gas is maintained in the target storage temperature region by the gas circulation, the fuel gas having an appropriate temperature can be supplied to the gas turbine. As a result, when the main fuel gas supply system to the gas turbine is abnormal, it is not necessary to install equipment for heating the fuel gas stored in the storage tank in the auxiliary supply line, which increases equipment costs and operating costs. In addition to being able to suppress, the fuel gas having the pressure and temperature required for the gas turbine can be rapidly supplied.
  • the fuel gas storage system for a gas turbine and the fuel gas supply method to the gas turbine of the present invention it is possible to suppress an increase in equipment cost and operation cost, and to reduce the fuel gas having the pressure and temperature required for the gas turbine. It can be supplied quickly.
  • FIG. 1 is a schematic configuration diagram illustrating a fuel gas storage system of a gas turbine according to a first embodiment.
  • FIG. 2 is a schematic diagram showing the operation of the fuel gas storage system of the gas turbine when the fuel gas supply system is normal.
  • FIG. 3 is a schematic diagram showing the operation of the fuel gas storage system of the gas turbine when the fuel gas supply system is abnormal.
  • FIG. 4 is a schematic configuration diagram illustrating a gas turbine combined cycle power plant.
  • FIG. 5 is a schematic configuration diagram illustrating a fuel gas storage system of a gas turbine according to the second embodiment.
  • FIG. 4 is a schematic configuration diagram illustrating a gas turbine combined cycle power plant.
  • the gas turbine combined cycle power plant 10 includes a gas turbine 11, an exhaust heat recovery boiler (HRSG) 12, a steam turbine 13, and a generator 14. .
  • HRSG exhaust heat recovery boiler
  • the gas turbine 11 includes a compressor 21, a combustor 22, and a turbine 23, and the compressor 21 and the turbine 23 are coupled to each other by a rotating shaft (rotor) 24 so as to be integrally rotatable.
  • the compressor 21 compresses the air taken in from the air intake line L1.
  • the combustor 22 mixes and combusts the compressed air supplied from the compressor 21 through the compressed air supply line L2 and the fuel gas supplied from the fuel gas supply line L3.
  • the turbine 23 is rotationally driven by the combustion gas supplied from the combustor 22 through the combustion gas supply line L4.
  • the exhaust heat recovery boiler 12 generates steam by exhaust heat of exhaust gas discharged from the gas turbine 11 (turbine 23) through the exhaust gas discharge line L5.
  • the exhaust heat recovery boiler 12 includes a superheater, an evaporator, and a economizer as a heat exchanger.
  • the exhaust heat recovery boiler 12 generates steam by performing heat recovery in the order of the superheater, the evaporator, and the economizer when the exhaust gas from the gas turbine 11 passes through the inside.
  • the exhaust heat recovery boiler 12 is connected to a chimney (not shown) via an exhaust gas exhaust line L6 that exhausts used exhaust gas that has generated steam.
  • the steam turbine 13 is driven by superheated steam generated by the exhaust heat recovery boiler 12.
  • the steam turbine 13 has a turbine 25, and the rotation shaft 26 is connected to the rotation shaft 24 of the gas turbine 11 in a straight line.
  • a steam supply line L7 for supplying superheated steam from the superheater of the exhaust heat recovery boiler 12 to the turbine 25 is provided, and used steam that has driven the turbine 25 is cooled by a condenser 27 (for example, It is cooled by seawater) to become condensate, and is supplied to the exhaust heat recovery boiler 12 via the condensate / water supply line L8.
  • the generator 14 is provided at the end of the rotating shaft 26.
  • the rotating shaft 24 of the gas turbine 11 and the rotating shaft 26 of the steam turbine 13 may be provided integrally.
  • the generator 14 generates power by the transmitted rotational force when the gas turbine 11 and the steam turbine 13 are driven and the rotating shafts 24 and 26 are rotated.
  • the rotary shaft 24 of the gas turbine 11 and the rotary shaft 26 of the steam turbine 13 may be separate, and may be a so-called multi-shaft type in which a generator is connected to each.
  • the compressor 21 compresses air in the gas turbine 11, and the combustor 22 mixes and supplies the supplied compressed air and fuel gas for combustion.
  • the turbine 23 is rotationally driven by the combustion gas supplied from the combustor 22. Further, the exhaust gas discharged from the gas turbine 11 (turbine 23) is sent to the exhaust heat recovery boiler 12, the exhaust heat recovery boiler 12 generates steam, and the superheated steam is sent to the steam turbine 13.
  • the turbine 25 is rotationally driven by this superheated steam.
  • the generator 14 generates power when the rotary shafts 24 and 26 are driven and rotated by the gas turbine 11 and the steam turbine 13.
  • the fuel gas is supplied from the main fuel gas supply system to the combustor 22 of the gas turbine 11.
  • the main fuel gas supply system fails, the pressure of the fuel gas supplied to the combustor 22 of the gas turbine 11 decreases, and it becomes difficult to continuously operate the gas turbine continuously. Therefore, the gas turbine combined cycle power plant 10 may include a fuel gas storage system.
  • FIG. 1 is a schematic configuration diagram showing a fuel gas storage system of a gas turbine according to a first embodiment.
  • a gas pipeline L10 as a fuel gas source is connected to a gas turbine 11 (combustor 22) via a fuel gas supply line L3 as a main fuel gas supply line.
  • the fuel gas supply line L3 is provided with a compressor 31, an on-off valve 32, a pressure sensor 33, and a temperature sensor 34 as necessary.
  • the fuel gas storage system 40 of the gas turbine 11 can supply the stored fuel gas from the auxiliary fuel gas supply line L11 to the gas turbine 11, and includes a storage tank 41, a circulation line L12, and a circulation flow rate adjustment valve 42. And a compressor 43, a temperature controller 44, and a control device 45.
  • the storage tank 41 stores the fuel gas of the gas turbine 11 and includes a plurality of tank main bodies 51.
  • the plurality of tank bodies 51 are hollow long tubes having a predetermined length, and are arranged in parallel at predetermined intervals.
  • the circulation line L12 is used to continuously exchange the gas in the storage tank 41 by circulating the fuel gas stored in the storage tank 41 outside.
  • the circulation line L12 is connected at one end to an inlet 51a on one side in the longitudinal direction of the plurality of tank main bodies 51 constituting the storage tank 41, and at the other end thereof is an outlet on the other side in the longitudinal direction of the plurality of tank main bodies 51. It is connected to the part 51b.
  • the circulation line L12 serves as a part of the fuel gas supply line L3 and a part of the auxiliary fuel gas supply line L11.
  • the plurality of tank main bodies 51 are arranged so as to be inclined such that the position of the outlet 51b is lower than the position of the inlet 51a.
  • the drain line L13 is connected to the outlet 51b, and the drain valve 52 is provided in the drain line L13.
  • the compressor 43, the temperature controller 44, and the circulation flow rate adjustment valve 42 are arranged in order along the circulation direction of the fuel gas.
  • the recirculation flow rate adjustment valve 42 can adjust the recirculation flow rate of the fuel gas flowing through the recirculation line L12 by adjusting the opening degree.
  • the compressor 43 can increase the pressure of the fuel gas flowing through the circulation line L12.
  • the temperature adjuster 44 can adjust the temperature of the fuel gas flowing through the circulation line L12.
  • the temperature controller 44 can include a heater 53 and / or a cooler 54, and the fuel gas flowing through the circulation line L ⁇ b> 12 is heated by the heater 53 or cooled by the cooler 54. The temperature of the gas can be adjusted.
  • bypass line L12 may be provided with a bypass line L14 that bypasses the temperature controller 44.
  • the bypass line L14 is provided with an opening / closing valve 55.
  • the temperature of the fuel gas can be adjusted by closing the on-off valve 55 and flowing the entire fuel gas to the temperature controller 44.
  • the on-off valve 55 is opened and all of the fuel gas flows through the bypass line L14, the temperature of the fuel gas is not adjusted and the temperature remains unchanged. It should be noted that by adjusting the opening degree of the on-off valve 55, a part of the fuel gas is allowed to flow to the bypass line L14, and the remaining fuel gas is heated or cooled by the temperature controller 44 to adjust the temperature of the fuel gas. Good.
  • an on-off valve 56 is provided on the downstream side of the temperature controller 44 and the bypass line L14.
  • the auxiliary fuel gas supply line L11 has a proximal end portion connected between the on-off valve 56 in the circulation line L12 and the inlet portion 51a of each tank body 51, and a distal end portion of the pressure sensor 33 and temperature sensor in the fuel gas supply line L3. 34 is connected to the upstream side.
  • the auxiliary fuel gas supply line L11 also serves as at least a part of the circulation line L12, and is connected to the fuel gas supply line L3, bypassing the circulation flow rate adjustment valve 42, the compressor 43, and the temperature regulator 44. ing.
  • the auxiliary fuel gas supply line L11 is provided with a pressure reducing valve 57 in parallel with the recirculation flow rate control valve 42, the compressor 43, and the temperature controller 44.
  • the control device 45 controls the temperature regulator 44 so that the temperature of the fuel gas stored in the storage tank 41 is maintained within a preset target storage temperature region.
  • the lower limit temperature in the target storage temperature range is a temperature obtained by adding a temperature drop at which the fuel gas drops when passing through the pressure reducing valve 57 to the target supply temperature of the fuel gas supplied to the gas turbine 11.
  • the target supply pressure P0 and the supply lower limit temperature T0 are set for the fuel gas supplied to the gas turbine 11.
  • the pressure sensor 33 and the temperature sensor 34 measure the pressure and temperature of the fuel gas flowing through the fuel gas supply line L ⁇ b> 3, and output the measurement result to the control device 45.
  • the control device 45 monitors that the pressure and temperature of the fuel gas flowing through the fuel gas supply line L3 are equal to or higher than the target supply pressure P0 and the supply lower limit temperature T0.
  • the fuel gas storage system 40 suppresses the temperature drop by circulating the fuel gas stored in the storage tank 41 to the outside through the circulation line L12 when the gas pipeline L10 is normal. That is, the recirculation flow rate adjustment valve 42 is opened, the compressor 43 is driven, and the temperature adjuster 44 is operated as necessary.
  • the fuel gas storage system 40 supplies the fuel gas stored in the storage tank 41 to the gas turbine 11 from the auxiliary fuel gas supply line L11 when the gas pipeline L10 is abnormal. At this time, the fuel gas is depressurized by the pressure reducing valve 57 and supplied to the gas turbine 11, so that the temperature decreases.
  • the controller 45 causes the pressure and temperature of the fuel gas flowing from the auxiliary fuel gas supply line L11 to the fuel gas supply line L3 to be equal to or higher than the target supply pressure P0 and the supply lower limit temperature T0. It is necessary to adjust the temperature of the fuel gas. Therefore, the control device 45 adjusts the temperature of the fuel gas stored in the storage tank 41 in consideration of the temperature drop at which the fuel gas drops when passing through the pressure reducing valve 57.
  • the storage tank 41 is provided with a pressure sensor 61 and a temperature sensor 62 for detecting the pressure and temperature of the stored fuel gas. Further, in the circulation line L12, a temperature sensor 63 is provided between the on-off valve 56 and the connecting portion of the auxiliary fuel gas supply line L11.
  • the target storage pressure region and the target storage temperature region of the fuel gas stored in the storage tank 41 are set, the lower limit temperature of the target storage temperature region is T1, and the fuel gas falls when passing through the pressure reducing valve 57. Assuming that the temperature drop is ⁇ T, the lower limit temperature T1 of the target storage temperature region is set as follows.
  • T1 T0 + ⁇ T
  • T2 the upper limit temperature of the target storage temperature region
  • T3 the endurance temperature of the pipe constituting the circulation line L12
  • the control device 45 maintains the temperature of the fuel gas stored in the storage tank 41 and the temperature of the fuel gas circulating in the circulation line L12 based on the measurement results of the temperature sensors 62 and 63 within the target storage temperature region T1 to T2. Thus, the temperature controller 44 and the on-off valve 55 are controlled. The control device 45 controls the compressor 43 based on the measurement result of the pressure sensor 61 so that the pressure of the fuel gas stored in the storage tank 41 is maintained in the target storage pressure region.
  • FIG. 2 is a schematic diagram illustrating the operation of the fuel gas storage system of the gas turbine when the fuel gas supply system is normal
  • FIG. 3 is a schematic diagram illustrating the operation of the fuel gas storage system of the gas turbine when the fuel gas supply system is abnormal.
  • the fuel gas supply method to the gas turbine 11 includes a step of circulating the fuel gas stored in the storage tank 41 outside and returning the fuel gas to the storage tank 41, and boosting the fuel gas during the circulation of the fuel gas. Adjusting the temperature so that the temperature of the fuel gas is maintained within a preset target storage temperature range, and stopping the circulation of the fuel gas when the gas pipeline L10 is abnormal, and storing the fuel gas stored in the storage tank 41 And a step of supplying the gas turbine 11 with a reduced pressure.
  • the fuel gas in the gas pipeline L10 is supplied to the gas turbine 11 (combustor 22) via the fuel gas supply line L3. . Further, the fuel gas in the gas pipeline L10 is supplied to the circulation line L12. And while driving the compressor 43 and opening the on-off valves 55 and 56, the fuel gas supplied to the circulation line L12 is pressurized and stored in each tank body 51 of the storage tank 41.
  • each tank body 51 of the storage tank 41 When fuel gas is stored in each tank body 51 of the storage tank 41, a predetermined amount of fuel gas is circulated through the circulation line L12 and each tank body 51 by opening the circulation flow rate adjustment valve 42. At this time, the controller 45 controls the temperature regulator 44 and the temperature controller 44 so that the temperature of the fuel gas stored in the storage tank 41 is maintained in the target storage temperature region T1 to T2 based on the measurement results of the temperature sensors 62 and 63. The on-off valve 55 is controlled.
  • the control device 45 detects a decrease in the pressure of the fuel gas in the fuel gas supply line L3 from the measurement result of the pressure sensor 33, and starts supplying the fuel gas from the auxiliary fuel gas supply line L11 to the gas turbine 11. That is, the on-off valves 55 and 56 and the flow rate adjusting valve 42 are closed, the driving of the compressor 43 and the temperature controller 44 is stopped, and the pressure reducing valve 57 is opened. Then, the circulation of the fuel gas through the circulation line L12 is stopped, and the fuel gas stored in the storage tank 41 is supplied from the fuel gas supply line L3 to the gas turbine 11 through the auxiliary fuel gas supply line L11. At this time, since the fuel gas stored in the storage tank 41 is maintained in the target storage temperature region T1 to T2, even if the temperature is reduced during the pressure reduction by the pressure reducing valve 57, it is below the supply lower limit temperature T0. There is nothing.
  • the pressure reducing valve 57 is closed to supply fuel gas to the gas turbine 11 from the auxiliary fuel gas supply line L11. Stop.
  • the storage tank 41 that stores the fuel gas
  • the circulation line L12 that circulates the fuel gas stored in the storage tank 41 to the outside
  • a recirculation flow rate adjustment valve 42 provided in the line L12
  • a compressor 43 provided in the recirculation line L12 to boost the fuel gas
  • a temperature regulator 44 provided in the recirculation line L12 to adjust the temperature of the fuel gas
  • a storage tank There is provided a control device 45 that controls the temperature regulator 44 so that the temperature of the fuel gas stored in 41 is maintained within a preset target storage temperature region.
  • the fuel gas stored in the storage tank 41 is circulated outside by the circulation line L12 by opening the circulation flow rate adjusting valve 42 and driving the compressor 43 during normal operation of the gas pipeline L10 to the gas turbine 11.
  • the controller 45 controls the temperature regulator 44 so that the temperature of the fuel gas stored in the storage tank 41 is maintained within the target storage temperature region. Therefore, when the gas pipeline L10 to the gas turbine 11 is abnormal, the fuel gas stored in the storage tank 41 and maintained in the target storage temperature region can be supplied from the auxiliary fuel gas supply line L11 to the gas turbine 11.
  • the pressure reducing valve 57 is provided in the auxiliary fuel gas supply line L11, and the lower limit temperature in the target storage temperature region is set to the supply lower limit temperature of the fuel gas supplied to the gas turbine 11.
  • the temperature is equal to or higher than the sum of the temperature drop when the fuel gas passes through the pressure reducing valve 57. Therefore, when the gas pipeline L10 to the gas turbine 11 is abnormal, the fuel gas stored in the storage tank 41 is decompressed by the pressure reducing valve 57 and supplied to the gas turbine 11 from the auxiliary fuel gas supply line L11.
  • the lower limit temperature in the target storage temperature region is set to be equal to or higher than the temperature obtained by adding the drop temperature to the supply lower limit temperature, the fuel gas at an appropriate temperature can be supplied to the gas turbine 11.
  • the storage tank 41 is a tank body 51 of a hollow long tube having a predetermined length, and one end of the circulation line L12 is one side in the longitudinal direction of the tank body 51.
  • the other end of the tank main body 51 is connected to the other outlet 51b in the longitudinal direction.
  • the fuel gas circulates through a circulation line constituted by the storage tank 41 and the circulation line L12, and the gas property in the storage tank 41 is stabilized and uniform heating can be achieved, thereby suppressing the generation of drain. .
  • the outlet 51b is disposed so as to be inclined so that the position of the outlet 51b is lower than the position of the inlet 51a of the tank body 51 constituting the storage tank 41.
  • a drain line L13 is connected to the side. Accordingly, even if drain is generated in the storage tank 41, the drain flows to the outlet 51b side and is discharged to the outside from the drain line L13, so that the retention of the drain in the storage tank 41 can be suppressed.
  • the outlet 51b is disposed so as to be positioned higher than the inlet 51a of the tank body 51 constituting the storage tank 41, and the inlet You may connect the drain line L13 to the part 51a side. Even in this configuration, when the drain is generated in the storage tank 41, the drain flows to the inlet 51a side and is discharged to the outside from the drain line L13, so that the retention of the drain in the storage tank 41 is suppressed. be able to.
  • the gas pipeline L10 is connected to the gas turbine 11 via the fuel gas supply line L3, and the auxiliary fuel gas supply line L11 is connected to the flow rate adjusting valve 42, the compressor 43, and the temperature.
  • the regulator 44 is bypassed and connected to the fuel gas supply line L3. Therefore, when the gas pipeline L10 to the gas turbine 11 is abnormal, the fuel gas stored in the storage tank 41 is supplied from the auxiliary fuel gas supply line L11 regardless of the operation of the recirculation flow control valve 42, the compressor 43, and the temperature controller 44.
  • the gas turbine 11 can be supplied.
  • the auxiliary fuel gas supply line L11 also serves as at least a part of the circulation line L12. Accordingly, the length of the piping constituting the auxiliary fuel gas supply line L11 and the circulation line L12 can be shortened, the structure can be simplified, and an increase in equipment cost can be suppressed.
  • the gas pipeline L10 is connected to the gas turbine 11 via the fuel gas supply line L3, and the auxiliary fuel gas supply line L11 is connected from the storage tank 41 to the fuel gas supply line. You may connect with L3. With this configuration, since the auxiliary fuel gas supply line L11 is directly connected from the storage tank 41 to the fuel gas supply line L3, reliability can be improved.
  • the step of circulating the fuel gas stored in the storage tank 41 to the outside and returning it to the storage tank 41, and the fuel gas during the circulation of the fuel gas And adjusting the temperature so that the temperature of the fuel gas is maintained within a preset target storage temperature range, and when the gas pipeline L10 is abnormal, the circulation of the fuel gas is stopped and stored in the storage tank 41. And reducing the pressure of the fuel gas and supplying it to the gas turbine 11.
  • the fuel gas stored in the storage tank 41 is depressurized and supplied from the auxiliary fuel gas supply line L11 to the gas turbine 11, so the temperature of the fuel gas decreases. Since the temperature of the fuel gas is maintained within the target storage temperature region during the circulation of the fuel gas, the fuel gas having an appropriate temperature can be supplied to the gas turbine 11. As a result, when the gas pipeline L10 to the gas turbine 11 is abnormal, equipment on the downstream side of the storage tank 41 for heating the fuel gas stored in the storage tank 41 becomes unnecessary, and an increase in equipment cost and operation cost is suppressed. In addition, the fuel gas having the pressure and temperature necessary for the gas turbine 11 can be quickly supplied.
  • FIG. 5 is a schematic configuration diagram illustrating a fuel gas storage system of a gas turbine according to the second embodiment.
  • symbol is attached
  • the gas pipeline L10 is connected to the gas turbine 11 (combustor 22) via the fuel gas supply line L3.
  • the fuel gas supply line L3 is provided with a compressor 31, an on-off valve 32, a pressure sensor 33, and a temperature sensor 34.
  • the fuel gas storage system 40A of the gas turbine 11 can supply stored fuel gas from the auxiliary fuel gas supply line L21 to the gas turbine 11, and includes a storage tank 41, a circulation line L12, and a circulation flow rate adjustment valve 42. And a compressor 43, a temperature controller 44, and a control device 45.
  • the auxiliary fuel gas supply line L21 also serves as at least a part of the circulation line L12, and is connected to the fuel gas supply line L3, bypassing the circulation flow rate adjustment valve 42, the compressor 43, and the temperature regulator 44. That is, the auxiliary fuel gas supply line L21 is provided with a circulation line L12 that bypasses the pressure reducing valve 57, and a circulation flow rate adjustment valve 42 is provided in the circulation line L12.
  • the control device 45 controls the temperature regulator 44 so that the temperature of the fuel gas stored in the storage tank 41 is maintained within a preset target storage temperature region.
  • the lower limit temperature in the target storage temperature region is a temperature obtained by adding the lowering temperature of the fuel gas supplied to the gas turbine 11 to the lowering temperature at which the fuel gas drops when passing through the pressure reducing valve 57.
  • control device 45 various controls by the control device 45 are substantially the same as those in the first embodiment, and thus description thereof is omitted.
  • the auxiliary fuel gas supply line L21 is provided with the circulation line L12 that bypasses the pressure reducing valve 57, and the circulation flow rate adjustment valve 42 is provided in the circulation line L12. Provided.
  • auxiliary fuel gas supply line L21 and the circulation line L12 can be rationalized, the structure can be simplified, and an increase in equipment cost can be suppressed.
  • the heater 53 and the cooler 54 are provided as the temperature controller 44, and the bypass line L14 and the open / close valve 55 are provided.
  • the heater 53 may be omitted.
  • the bypass line L14 and the on-off valve may be omitted, and an air-cooled cooler with variable output may be provided as the temperature regulator 44.

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  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

L'invention concerne un système de stockage de gaz combustible pour une turbine à gaz et un procédé d'alimentation de la turbine à gaz en gaz combustible, le système comportant: un réservoir (41) de stockage qui stocke du gaz combustible; une conduite (L12) d'écoulement à travers laquelle le gaz combustible stocké dans le réservoir (41) de stockage est amené à s'écouler vers l'extérieur; une vanne (42) de réglage de quantité d'écoulement équipant la conduite (L12) d'écoulement; un compresseur (43) équipant la conduite (L12) d'écoulement afin de renforcer le débit du gaz combustible; un régulateur (44) de température équipant la conduite (L12) d'écoulement afin de régler la température du gaz combustible; et un dispositif (45) de commande qui commande le régulateur (44) de température de telle façon que la température du gaz combustible stocké dans le réservoir (41) de stockage soit maintenue à l'intérieur d'une plage cible préétablie de température de stockage.
PCT/JP2018/008130 2018-03-02 2018-03-02 Système de stockage de gaz combustible pour turbine à gaz et procédé d'alimentation de turbine à gaz en gaz combustible WO2019167276A1 (fr)

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5774522A (en) * 1980-10-27 1982-05-10 Ishikawajima Harima Heavy Ind Co Ltd Combustion for gas turbine
JPS6113100A (ja) * 1984-06-20 1986-01-21 シーメンス、アクチエンゲゼルシヤフト 純ガス貫流中間貯蔵設備
JP2000038929A (ja) * 1998-07-23 2000-02-08 Hitachi Ltd ガスタービン燃料ガス減圧加温装置
JP2004185943A (ja) * 2002-12-02 2004-07-02 Sanyo Electric Co Ltd 燃料電池システム
CA2651619A1 (fr) * 2009-01-22 2010-07-22 Bart Toporowski Systeme antigel pour canalisation de carburant
JP2011033029A (ja) * 2009-07-30 2011-02-17 General Electric Co <Ge> ガスタービンに燃料を供給するためのシステム及び方法
EP2399973A1 (fr) * 2010-06-25 2011-12-28 Siemens Aktiengesellschaft Système de gazéification de biomasse et procédé de gazéification de biomasse
US20130283811A1 (en) * 2011-01-06 2013-10-31 Snecma Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5774522A (en) * 1980-10-27 1982-05-10 Ishikawajima Harima Heavy Ind Co Ltd Combustion for gas turbine
JPS6113100A (ja) * 1984-06-20 1986-01-21 シーメンス、アクチエンゲゼルシヤフト 純ガス貫流中間貯蔵設備
JP2000038929A (ja) * 1998-07-23 2000-02-08 Hitachi Ltd ガスタービン燃料ガス減圧加温装置
JP2004185943A (ja) * 2002-12-02 2004-07-02 Sanyo Electric Co Ltd 燃料電池システム
CA2651619A1 (fr) * 2009-01-22 2010-07-22 Bart Toporowski Systeme antigel pour canalisation de carburant
JP2011033029A (ja) * 2009-07-30 2011-02-17 General Electric Co <Ge> ガスタービンに燃料を供給するためのシステム及び方法
EP2399973A1 (fr) * 2010-06-25 2011-12-28 Siemens Aktiengesellschaft Système de gazéification de biomasse et procédé de gazéification de biomasse
US20130283811A1 (en) * 2011-01-06 2013-10-31 Snecma Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve

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