JP5208859B2 - Gas turbine engine - Google Patents

Description

  The present invention relates to a gas turbine engine.

  Conventionally, a turbine in a gas turbine engine is rotated by a combustion gas generated by burning an air-fuel mixture of fuel supplied from a fuel pump and compressed air supplied from a compressor in a combustor. If too much fuel is supplied, the temperature of the combustion gas exceeds the allowable temperature of the combustor and turbine blades, and there is a problem of damaging the combustor and turbine blades. In view of this, there is known a technique for appropriately supplying fuel by controlling the flow rate of fuel to a flow rate proportional to the discharge pressure of the compressor by a metering valve.

  However, the control by the metering valve is performed only based on the discharge pressure of the compressor, and the operation state of the gas turbine engine is not considered. That is, regardless of the exhaust temperature of the gas turbine engine, the metering valve controls the fuel to be supplied to the combustor in an amount proportional to the pressure of the compressed air supplied by the compressor that is linked to the turbine. Therefore, when starting from a state where the exhaust temperature of the gas turbine engine is high and the fuel is easily combusted, the fuel supply is excessive and a loud ignition sound is generated due to rapid combustion, or the combustion gas becomes hot and the combustor or turbine In some cases, the wings were damaged.

  Therefore, the metering valve is opened and closed by an actuator such as a motor, and equipped with an electronic fuel limit valve that can freely control the amount of fuel supplied, and is appropriate based on the rotational speed and exhaust temperature of the gas turbine engine. The technology of a fuel control device for a gas turbine engine that controls an electronic fuel limit valve so that a fresh fuel is supplied is well known. For example, it is like patent document 1.

  However, the control of the fuel supply amount by the electronic fuel limit valve described above has an excessive control accuracy in the fuel supply control of the gas turbine engine, and also requires an expensive actuator such as a motor. Since the fuel limiting valve is provided, there is a problem that the manufacturing cost of the gas turbine engine increases.

Japanese Patent No. 4169952

  The present invention has been made in view of such problems, and prevents rapid combustion of fuel with an inexpensive configuration that does not require an expensive actuator such as a motor, thereby reducing (or eliminating) the ignition sound of fuel, And it aims at suppressing the excessive temperature rise of combustion gas.

  The problem to be solved by the present invention is as described above. Next, means for solving the problem will be described.

  That is, in claim 1, a turbine, a combustor that generates combustion gas to be supplied to the turbine, a compressor that supplies compressed air to the combustor and a metering valve, and fuel that is supplied to the combustor Is adjusted to a flow rate proportional to the pressure of compressed air supplied from the compressor, a fuel limiting valve for cutting off compressed air supplied to the metering valve, and supplied to the combustor In a gas turbine engine, comprising: a fuel cutoff valve that shuts off fuel; a control means that controls the fuel limit valve and the fuel cutoff valve; and an exhaust temperature detection means that detects an exhaust temperature. When the gas turbine engine is restarted from a state in which the exhaust temperature detected by the exhaust temperature detecting means is equal to or higher than a reference temperature, the compressed air supplied to the metering valve is supplied to the metering valve for a predetermined time. The fuel supplied to the combustor is reduced to a predetermined amount for the predetermined time by shutting off or shutting off the fuel supplied to the combustor for a predetermined time by the fuel cutoff valve. .

  According to a second aspect of the present invention, the engine further includes a rotation speed detection unit that detects a rotation speed of the turbine, and the control unit restarts the gas turbine engine from a state where the exhaust temperature detected by the exhaust temperature detection unit is equal to or higher than a reference temperature. When activated, the fuel supplied to the combustor is shut off by the fuel shut-off valve until the rotational speed of the turbine detected by the rotational speed detection means reaches the first reference value, and the turbine Until the rotation speed reaches a second reference value that is larger than the first reference value, the compressed air supplied to the metering valve is shut off by the fuel limiting valve, and the atmosphere that is at atmospheric pressure in the metering valve It is characterized by supplying.

  As effects of the present invention, the following effects can be obtained.

  According to the present invention, there is provided a fuel limiting valve that performs only an operation of shutting off compressed air supplied to a metering valve and switching to an atmospheric pressure atmosphere, and a fuel cutoff valve that performs only an operation of shutting off the supply of fuel. By simply doing this, the fuel supplied to the combustor can be reduced to a predetermined amount for a certain period of time. This prevents rapid fuel combustion with an inexpensive configuration that does not require an expensive actuator such as a motor, reduces (or eliminates) the ignition sound of the fuel, and suppresses an excessive temperature rise of the combustion gas. There is an effect.

1 is a schematic diagram illustrating a configuration of a gas turbine engine according to an embodiment of the present invention. Schematic which shows the structure of the fuel metering valve in the gas turbine engine which concerns on one Embodiment of this invention. The flowchart figure which shows the restart control of the gas turbine engine which concerns on one Embodiment of this invention. The flowchart figure which shows the restart control of the gas turbine engine which concerns on one Embodiment of this invention. The flowchart figure which shows the restart control of the gas turbine engine which concerns on one Embodiment of this invention. The flowchart figure which shows the restart control of the gas turbine engine which concerns on one Embodiment of this invention. Compressed air pressure and fuel when the gas turbine engine is restarted from a state where the exhaust temperature of the gas turbine engine according to an embodiment of the present invention is equal to or higher than the reference temperature and the rotational speed of the turbine shaft is equal to or lower than the first reference value The figure which shows the graph of flow volume.

  Below, the gas turbine engine 1 which concerns on one Embodiment of this invention using FIG. 1 and FIG. 2 is demonstrated.

  The gas turbine engine 1 generates rotational power by rotating a turbine with high-pressure combustion gas. As shown in FIG. 1, the gas turbine engine 1 includes a turbine unit 10, a compressor 20, a reduction gear unit 30, a fuel control device 40, and the like.

  The turbine unit 10 generates high-temperature and high-pressure combustion gas and extracts the energy of the combustion gas as rotational power. The turbine unit 10 mainly includes a turbine 11, a combustor 12, an exhaust diffuser 13, and the like.

  The turbine 11 converts the energy of the high-temperature and high-pressure combustion gas into rotational power. The turbine 11 includes a turbine rotor 11a that is a rotating portion, a turbine nozzle 11b that is a stationary portion, and a turbine shaft 11c that is a rotating shaft. The turbine rotor 11a is configured such that a plurality of rotor blades are fixed on the outer periphery of a disk-shaped disk, and a turbine shaft 11c is fixed in the direction perpendicular to the disk at the center of the disk. The turbine nozzle 11b is configured by arranging a plurality of stationary blades on the circumference of a circle centering on the turbine shaft 11c from the wall surface in the turbine section 10. In the turbine 11, the rotor blades of the turbine rotor 11a and the stationary blades of the turbine nozzle 11b are alternately arranged in the axial direction of the turbine shaft 11c, and the turbine rotor 11a is rotatably supported using the turbine shaft 11c as a rotation shaft. The

  The combustor 12 burns fuel injected into compressed air and generates high-temperature and high-pressure combustion gas. The combustor 12 includes a substantially cylindrical combustion chamber 12a, a compressed air passage 12b formed around the combustion chamber 12a, a fuel injection nozzle 12c, and a spark plug 12d, and is disposed around the turbine 11. In the combustion chamber 12a, the combustor 12 injects fuel into the compressed air supplied from the compressor 20 via the compressed air passage 12b by the fuel injection nozzle 12c, and ignites the fuel by the spark plug 12d. High-temperature and high-pressure combustion gas generated by starting combustion of fuel is supplied to the turbine 11 and rotates the turbine rotor 11a.

  The exhaust diffuser 13 reduces the flow velocity by diffusing the flow of exhausted combustion gas. The exhaust diffuser 13 is formed in a substantially cylindrical shape in which the opening on one side is smaller in diameter than the opening on the other side. The exhaust diffuser 13 is disposed with the opening on one side facing the turbine 11 so that the combustion gas discharged through the turbine 11 passes through the interior of the exhaust diffuser 13. The combustion gas is diffused and discharged by the exhaust diffuser 13 after rotating the turbine 11. The exhaust diffuser 13 includes an exhaust temperature sensor 13a which is an exhaust temperature detection means for detecting the exhaust temperature TMP of the exhausted combustion gas.

  The compressor 20 generates compressed air. The compressor 20 mainly includes an impeller 21, a diffuser 22, and the like, and is disposed adjacent to the turbine unit 10.

  The impeller 21 sucks outside air and pressurizes it. In the impeller 21, a plurality of rotor blades 21b are integrally formed on a disk-shaped disk 21a radially from the center toward the outer periphery, and the disk 21a is fixed to the turbine shaft 11c in the direction perpendicular thereto. Is configured. That is, the impeller 21 is configured to be rotatable in conjunction with the rotation of the turbine 11. The impeller 21 rotates to suck the outside air from the central portion, and accelerates and discharges the sucked outside air in the outer peripheral direction, and supplies it to the diffuser 22.

  The diffuser 22 decelerates and boosts the accelerated outside air. The diffuser 22 is configured such that a plurality of passages having a substantially square cross section are arranged around the impeller 21 on the circumference of a circle centered on the turbine shaft 11c. The diffuser 22 decelerates and boosts the outside air supplied from the impeller 21 and sends it to the combustor 12, and also sends a part of the compressed air to the metering valve 41 through the compressed air passage 23.

  The reduction gear unit 30 decelerates and outputs the rotation of the turbine shaft 11c rotated at high speed. Moreover, when starting the gas turbine engine 1, the turbine shaft 11c is rotated. The reduction gear unit 30 mainly includes a reduction gear 31, a cell motor 32, a fuel pressurization pump 33, and the like, and is disposed adjacent to the compressor 20.

  The speed reducer 31 converts the input rotational speed into a low speed or a high speed and outputs it. The speed reducer 31 is configured by a combination of a plurality of gears, and converts the rotational speed R of the turbine shaft 11c, which is an input shaft, to a low rotational speed and transmits it to the output shaft 31a. When the gas turbine engine 1 is started, the rotational speed input from the cell motor 32 is converted into a high rotational speed and transmitted to the gas turbine shaft 11c. The speed reducer 31 includes a rotation speed sensor 31b that is a rotation speed detection unit that detects a rotation speed R of the turbine shaft 11c (the turbine 11).

  The cell motor 32 rotates the turbine shaft 11 c when starting the gas turbine engine 1. The cell motor 32 is connected to the turbine shaft 11 c via the speed reducer 31. The cell motor 32 rotates the turbine shaft 11c until the turbine shaft 11c reaches a predetermined rotational speed.

  The fuel pressurization pump 33 supplies fuel. The fuel pressurizing pump 33 is configured such that a drive shaft (not shown) is interlocked with the turbine shaft 11 c via the speed reducer 31. In the fuel pressurizing pump 33, a suction port (not shown) is connected to a fuel tank (not shown) via a pipe or the like, and a discharge port is connected to the fuel injection nozzle 12c via a fuel flow path 34. The fuel pressurization pump 33 supplies fuel from a fuel tank (not shown) to the fuel injection nozzle 12c as the turbine shaft 11c rotates.

  The fuel control device 40 controls the supply of fuel. The fuel control device 40 includes a metering valve 41, a fuel limiting valve 42, a fuel cutoff valve 43, an ECU 44 that is a control means, and the like.

  The metering valve 41 controls the flow rate of fuel. As shown in FIG. 2, the metering valve 41 includes a throttle valve 41a, an actuator 41b, a governor 41c, a constant differential pressure valve 41d, and the like. The metering valve 41 is disposed in the middle of the fuel flow path 34. The actuator 41 b is connected to the compressor 20 via the compressed air channel 23.

  The metering valve 41 adjusts the flow rate of the fuel supplied from the fuel flow path 34 by the throttle valve 41a. The throttle valve 41a has its valve opening changed by an actuator 41b and a mechanical hydraulic governor 41c. The actuator 41b is composed of an air cylinder. In the actuator 41b, compressed air from the compressor 20 is supplied to the cylinder chamber via the compressed air passage 23 and the fuel limiting valve 42, and the valve opening degree of the throttle valve 41a is changed in proportion to the pressure P of the compressed air. . The governor 41c changes the valve opening degree of the throttle valve 41a according to the target rotational speed R0 of the gas turbine engine 1 set by an instruction from an operator or the like. At this time, in order to keep the flow rate of the fuel corresponding to the valve opening of the throttle valve 41a constant, the fuel supply pressure upstream of the throttle valve 41a and the fuel supply pressure downstream of the throttle valve 41a by the constant differential pressure valve 41d. The differential pressure is constant. Thus, the metering valve 41 adjusts the fuel flow rate to a value proportional to the pressure P of the compressed air until the valve opening set by the governor 41c is reached.

  The fuel limit valve 42 reduces the fuel supplied to the combustor 12 to a predetermined amount by blocking the compressed air supplied from the compressor 20 to the metering valve 41. As shown in FIG. 1, the fuel limiting valve 42 is configured by an electromagnetic three-way valve, and is disposed in the middle of the compressed air passage 23. In the fuel limiting valve 42, the first input port 42 a is connected to the compressor 20, the second input port 42 b is opened to the atmosphere, and the output port 42 c is connected to the actuator 41 b of the metering valve 41. The fuel limiting valve 42 is connected to a solenoid that operates the valve body and the ECU 44, and is operated by a control signal from the ECU 44. When the fuel limiting valve 42 is closed by connecting the first input port 42a and the output port 42c, compressed air having a pressure P is supplied to the actuator 41b, and the fuel limiting valve 42 is connected to the second input port 42b and the output port. When the valve 42c is opened by communicating with 42c, the atmospheric pressure P0 atmosphere is supplied to the actuator 41b.

  The fuel shut-off valve 43 switches between fuel supply and shut-off. The fuel cutoff valve 43 is configured by an electromagnetic two-way valve, and is disposed in the middle of the fuel flow path 34 that connects the metering valve 41 and the combustor 12. In the fuel cutoff valve 43, a solenoid for operating the valve body is connected to the ECU 44.

  The ECU 44 as control means controls the gas turbine engine 1, the fuel limiting valve 42, the fuel cutoff valve 43, and the like. Specifically, the ECU 44 acquires the exhaust temperature by the exhaust temperature sensor 13a, acquires the rotational speed R of the gas turbine engine 1 by the rotational speed sensor 31b, and controls the fuel limiting valve 42 and the fuel cutoff valve 43. Further, the ECU 44 controls the gas turbine engine 1 by a signal from an operation panel (not shown) or the like. Specifically, the ECU 44 may be configured such that a CPU, a ROM, a RAM, an HDD, and the like are connected by a bus, or may be configured by a one-chip LSI or the like. The ECU 44 stores various programs and data for controlling the gas turbine engine 1, the fuel limiting valve 42, the fuel cutoff valve 43, and the like.

  The ECU 44 is connected to the spark plug 12d and can control starting and stopping of the gas turbine engine 1 by controlling ignition of the spark plug 12d.

  The ECU 44 is connected to the exhaust temperature sensor 13a and can acquire the exhaust temperature TMP detected by the exhaust temperature sensor 13a.

  The ECU 44 is connected to the rotational speed sensor 31b and can acquire the rotational speed R of the turbine shaft 11c detected by the rotational speed sensor 31b.

  The ECU 44 is connected to the cell motor 32, and can control the activation of the gas turbine engine 1 by controlling the operation of the cell motor 32.

  The ECU 44 is connected to the fuel limit valve 42 and controls the operation of the fuel limit valve 42 to limit the supply of compressed air to the metering valve 41 and reduce the flow rate of fuel supplied to the combustor 12. Is possible.

  The ECU 44 is connected to the fuel cutoff valve 43 and controls the operation of the fuel cutoff valve 43 so as to control the start and stop of the gas turbine engine 1.

  Next, using FIG. 3, FIG. 4, FIG. 5, and FIG. 6, the ignition noise of the fuel when the gas turbine engine 1 according to one embodiment of the present invention is restarted is reduced, and the excessive temperature of the combustion gas is reduced. The control which suppresses a raise is demonstrated.

  As shown in FIG. 3, when the gas turbine engine 1 is restarted, the ECU 44 determines whether or not the exhaust gas temperature TMP is equal to or lower than the reference temperature TMP1. The ECU 44 supplies the combustor 12 with an amount of fuel proportional to the pressure P of the compressed air generated by the compressor 20 when the exhaust temperature TMP is equal to or lower than the reference temperature TMP1. When the exhaust gas temperature TMP is higher than the reference temperature TMP1, the ECU 44 determines the fuel supply control mode by comparing the rotational speed R of the turbine shaft 11c with the first reference value R1 or the second reference value R2.

  Below, the control aspect by ECU44 is demonstrated concretely.

  In step S110, the ECU 44 acquires a restart signal from an operation panel (not shown) or the like, and then shifts the control stage to step S120.

In step S120, the ECU 44 acquires the exhaust gas temperature TMP from the exhaust gas temperature sensor 13a, and determines whether or not the exhaust gas temperature TMP is equal to or lower than the reference temperature TMP1.
As a result, when it is determined that the exhaust gas temperature TMP is equal to or lower than the reference temperature TMP1, the ECU 44 shifts the control stage to step S130.
If it is determined that the exhaust gas temperature TMP is higher than the reference temperature TMP1, the ECU 44 proceeds to step S230.

  In step S130, the ECU 44 closes the fuel limiting valve 42 so that the compressed air having the pressure P is supplied to the metering valve 41 by communicating the first input port 42a and the output port 42c of the fuel limiting valve 42. After that, the control stage shifts to step S140.

  In step S140, the ECU 44 opens the fuel cutoff valve 43 and starts supplying fuel to the combustor 12, and then controls the spark plug 12d and the cell motor 32 to restart the gas turbine engine 1. Thus, the gas turbine engine 1 starts normal operation.

In step S230 described above, the ECU 44 acquires the rotational speed R of the turbine shaft 11c from the rotational speed sensor 31b, and determines whether the rotational speed R of the turbine shaft 11c is equal to or less than the first reference value R1.
As a result, when it is determined that the rotational speed R of the turbine shaft 11c is equal to or less than the first reference value R1, the ECU 44 proceeds the control step to step S240.
If it is determined that the rotational speed R of the turbine shaft 11c is greater than the first reference value R1, the ECU 44 proceeds to step S340.

  In step S240, the ECU 44 starts the restart control A and shifts the control stage to step S241 (see FIG. 4).

  In step S241, as shown in FIG. 4, the ECU 44 causes the second input port 42b and the output port 42c of the fuel limiting valve 42 to communicate with each other so that the atmospheric pressure P0 is supplied to the metering valve 41. After the fuel limit valve 42 is opened, the control stage proceeds to step S242.

  In step S242, the ECU 44 controls the cell motor 32 to restart the gas turbine engine 1 in a state where the fuel cutoff valve 43 is closed and fuel is not supplied to the combustor 12, and then the control step is performed. The process proceeds to S243.

In step S243, the ECU 44 acquires the rotational speed R of the turbine shaft 11c from the rotational speed sensor 31b, and determines whether or not the rotational speed R of the turbine shaft 11c is greater than the first reference value R1.
As a result, when it is determined that the rotational speed R of the turbine shaft 11c is greater than the first reference value R1, the ECU 44 proceeds to a control step to step S244.
If it is determined that the rotational speed R of the turbine shaft 11c is equal to or less than the first reference value R1, the ECU 44 repeatedly shifts the control stage to step S243.

  In step S244, the ECU 44 opens the fuel shut-off valve 43 to start supplying fuel to the combustor 12, starts the combustion of fuel by controlling the spark plug 12d, and then shifts the control stage to step S245. To do.

In step S245, the ECU 44 determines whether or not a predetermined time has elapsed since the fuel cutoff valve 43 opened.
As a result, when it is determined that the predetermined time has elapsed since the fuel shut-off valve 43 opened, the ECU 44 proceeds to a control step to step S246.
If it is determined that the predetermined time has not elapsed since the fuel shut-off valve 43 is opened, the ECU 44 repeatedly shifts the control stage to step S245.

In step S246, the ECU 44 acquires the rotational speed R of the turbine shaft 11c from the rotational speed sensor 31b, and determines whether or not the rotational speed R of the turbine shaft 11c is greater than the second reference value R2.
As a result, if it is determined that the rotational speed R of the turbine shaft 11c is greater than the second reference value R2, the ECU 44 proceeds to step S247.
When it is determined that the rotational speed R of the turbine shaft 11c is equal to or less than the second reference value R2, the ECU 44 repeatedly shifts the control stage to step S246.

  In step S247, the ECU 44 causes the first input port 42a and the output port 42c of the fuel limiting valve 42 to communicate with each other and closes the fuel limiting valve 42 so that compressed air having the pressure P is supplied to the metering valve 41. To do. Thus, the gas turbine engine 1 shifts to normal operation.

In the aforementioned step S340, as shown in FIG. 3, the ECU 44 obtains the rotational speed R of the turbine shaft 11c from the rotational speed sensor 31b, and determines whether or not the rotational speed R of the turbine shaft 11c is equal to or less than the second reference value R2. To do.
As a result, when it is determined that the rotational speed R of the turbine shaft 11c is equal to or less than the second reference value R2, the ECU 44 proceeds the control step to step S350.
If it is determined that the rotational speed R of the turbine shaft 11c is greater than the second reference value R2, the ECU 44 proceeds to step S450.

  In step S350, the ECU 44 starts the restart control B and shifts the control stage to step S351 (see FIG. 5).

  In step S351, as shown in FIG. 5, the ECU 44 causes the second input port 42b and the output port 42c of the fuel limiting valve 42 to communicate with each other so that the atmospheric pressure P0 is supplied to the metering valve 41. After opening the fuel limiting valve 42, the control stage proceeds to step S352.

  In step S352, the ECU 44 opens the fuel cutoff valve 43 to supply fuel to the combustor 12, controls the cell motor 32 and the spark plug 12d to restart the gas turbine engine 1, and then performs the control stage. The process proceeds to step S353.

In step S353, the ECU 44 determines whether or not a predetermined time has elapsed since the fuel cutoff valve 43 opened.
As a result, when it is determined that the predetermined time has elapsed since the fuel shut-off valve 43 opened, the ECU 44 proceeds to the control step to step S354.
If it is determined that the predetermined time has not elapsed since the fuel shut-off valve 43 is opened, the ECU 44 repeatedly shifts the control step to step S353.

In step S354, the ECU 44 acquires the rotational speed R of the turbine shaft 11c from the rotational speed sensor 31b, and determines whether or not the rotational speed R of the turbine shaft 11c is greater than the second reference value R2.
As a result, when it is determined that the rotational speed R of the turbine shaft 11c is greater than the second reference value R2, the ECU 44 proceeds to a control step to step S355.
Further, when it is determined that the rotational speed R of the turbine shaft 11c is equal to or less than the second reference value R2, the ECU 44 repeats the control stage and proceeds to step S354.

  In step S355, the ECU 44 causes the first input port 42a and the output port 42c of the fuel limiting valve 42 to communicate with each other and closes the fuel limiting valve 42 so that compressed air having pressure P is supplied to the metering valve 41. To do. Thus, the gas turbine engine 1 shifts to normal operation.

  In the above-described step S450, as shown in FIG. 4, the ECU 44 starts the restart control C and shifts the control stage to step S451 (see FIG. 6).

  In step S451, as shown in FIG. 6, the ECU 44 causes the second input port 42b and the output port 42c of the fuel limiting valve 42 to communicate with each other so that the atmospheric pressure P0 is supplied to the metering valve 41. After the fuel limit valve 42 is opened, the control stage proceeds to step S452.

  In step S452, the ECU 44 opens the fuel cutoff valve 43 to supply fuel to the combustor 12, and controls the cell motor 32 and the spark plug 12d to restart the gas turbine engine 1, and then performs the control stage. The process proceeds to step S453.

In step S453, the ECU 44 determines whether or not a predetermined time has elapsed since the fuel cutoff valve 43 opened.
As a result, when it is determined that a predetermined time has elapsed since the fuel shut-off valve 43 opened, the ECU 44 shifts the control stage to step S454.
If it is determined that the predetermined time has not elapsed since the fuel shut-off valve 43 is opened, the ECU 44 repeatedly shifts the control step to step S453.

  In step S454, the ECU 44 closes the fuel limit valve 42 so that the compressed air having the pressure P is supplied to the metering valve 41 by connecting the first input port 42a and the output port 42c of the fuel limit valve 42. To do. Thus, the gas turbine engine 1 shifts to normal operation.

  With the above control mode, the exhaust gas temperature TMP is supplied to the metering valve 41 when the gas turbine engine 1 is restarted from the state where the exhaust gas temperature TMP is equal to or higher than the reference temperature TMP1 and the rotational speed R of the turbine shaft 11c is equal to or lower than the first reference value R1. The pressure P of the compressed air and the flow rate of the fuel supplied to the combustor 12 will be described with reference to FIG.

  At time T1, when the ECU 44 acquires a restart signal from an operation panel (not shown) or the like (when the restart operation is performed at time T1), the rotational speed R of the turbine shaft 11c rotated by the cell motor 32 is increased. The fuel limiting valve 42 is opened until the time T2 when the first reference value R1 is reached, and the fuel cutoff valve 43 is closed. Thereby, the atmospheric pressure P 0 is supplied to the metering valve 41, and no fuel is supplied to the combustor 12. At time T2, the ECU 44 opens the fuel cutoff valve 43 when the rotational speed R of the turbine shaft 11c rotated by the cell motor 32 reaches the first reference value R1. Thereby, the flow rate of the fuel supplied to the combustor 12 is adjusted to a value proportional to the atmospheric pressure P0 by the metering valve 41 to which the atmospheric pressure P0 is supplied. At time T3, the ECU 44 closes the fuel limiting valve 42 when the rotational speed R of the turbine shaft 11c rotated by the cell motor 32 reaches the second reference value R2. Thereby, compressed air as pressure P from the compressor 20 is supplied to the metering valve 41, and the flow rate of fuel supplied to the combustor 12 is adjusted to a value proportional to the pressure P of the compressed air by the metering valve 41. Is done.

  As described above, the turbine 11, the combustor 12 that generates combustion gas to be sent to the turbine 11, the compressor 20 that supplies compressed air to the combustor 12 and the metering valve 41, and the fuel that is supplied to the combustor 12. Is adjusted to a flow rate proportional to the pressure P of the compressed air supplied from the compressor 20, a fuel limiting valve 42 for cutting off the compressed air supplied to the metering valve 41, and supplied to the combustor 12. A fuel shutoff valve 43 that shuts off the fuel to be discharged, an ECU 44 that is a control means for controlling the fuel limit valve 42 and the fuel shutoff valve 43, an exhaust temperature sensor 13a that is an exhaust temperature detection means for detecting the exhaust temperature TMP, In the gas turbine engine 1 including the ECU 44, the ECU 44 restarts the gas turbine engine 1 from a state where the exhaust temperature TMP detected by the exhaust temperature sensor 13a is equal to or higher than the reference temperature TMP1. In this case, the compressed air supplied to the metering valve 41 is shut off for a predetermined time by the fuel limiting valve 42, or the fuel supplied to the combustor 12 is shut off by the fuel cutoff valve 43 for a predetermined time. The supplied fuel is reduced to a predetermined amount for a predetermined time.

  With this configuration, even when the gas turbine engine 1 is restarted from a state where the exhaust temperature TMP detected by the exhaust temperature sensor 13a is equal to or higher than the reference temperature TMP1, the rotational speed R of the turbine shaft 11c becomes a predetermined value. The fuel supplied by the fuel limiting valve 42 and the fuel shut-off valve 43 is limited until it reaches. As a result, fuel is not supplied excessively, thus preventing rapid fuel combustion with an inexpensive configuration that does not require an expensive actuator such as a motor, and reducing (or eliminating) the ignition sound of the fuel. And the excessive temperature rise of combustion gas can be suppressed.

  The ECU 44 further includes a rotation speed sensor 31b which is a rotation speed detection means for detecting the rotation speed R of the turbine 11. The ECU 44 detects the gas turbine engine 1 from a state where the exhaust gas temperature TMP detected by the exhaust gas temperature sensor 13a is equal to or higher than the reference temperature TMP1. Is restarted, the fuel supplied to the combustor 12 is shut off by the fuel cutoff valve 43 until the rotational speed R of the turbine 11 detected by the rotational speed sensor 31b reaches the first reference value R1, Until the rotational speed R of the turbine 11 reaches a second reference value R2 that is larger than the first reference value R1, the compressed air supplied to the metering valve 41 is shut off by the fuel limit valve 42, and the metering valve 41 The atmospheric pressure P0 is supplied.

  With this configuration, even when the gas turbine engine 1 is restarted from a state where the exhaust temperature TMP detected by the exhaust temperature sensor 13a is equal to or higher than the reference temperature TMP1, the high-temperature exhaust in the gas turbine engine 1 flows sufficiently. Until then, no fuel is supplied to the combustor 12, and even if the supply of fuel is started, only an amount of fuel proportional to the atmospheric pressure P0 is supplied. As a result, fuel is not supplied excessively, thus preventing rapid fuel combustion with an inexpensive configuration that does not require an expensive actuator such as a motor, and reducing (or eliminating) the ignition sound of the fuel. And the excessive temperature rise of combustion gas can be suppressed.

DESCRIPTION OF SYMBOLS 1 Gas turbine engine 11 Turbine 12 Combustor 13a Exhaust temperature sensor (exhaust temperature detection means)
20 Compressor 31b Rotational speed sensor (Rotational speed detection means)
41 Metering valve 42 Fuel limit valve 43 Fuel shut-off valve 44 ECU (control means)

Claims (2)

  A turbine, a combustor that generates combustion gas to be supplied to the turbine, a compressor that supplies compressed air to the combustor and a metering valve, and fuel that is supplied to the combustor are supplied from the compressor. The metering valve that adjusts the flow rate in proportion to the pressure of the compressed air, a fuel limit valve that shuts off the compressed air supplied to the metering valve, and a fuel shut-off valve that shuts off the fuel supplied to the combustor; In the gas turbine engine comprising: control means for controlling the fuel limit valve and the fuel cutoff valve; and exhaust temperature detection means for detecting the exhaust temperature, the control means is an exhaust gas detected by the exhaust temperature detection means. When the gas turbine engine is restarted from a state where the temperature is equal to or higher than a reference temperature, the compressed air supplied to the metering valve is shut off for a predetermined time by the fuel limit valve, or the combustor By blocking a predetermined time by the fuel supplied to said fuel cutoff valve, a gas turbine engine, characterized by reducing the fuel supplied to the combustor to said predetermined time a predetermined amount.   Rotational speed detection means for detecting the rotational speed of the turbine, and the control means, when the gas turbine engine is restarted from a state where the exhaust temperature detected by the exhaust temperature detection means is equal to or higher than a reference temperature, Until the rotational speed of the turbine detected by the rotational speed detection means reaches the first reference value, the fuel supplied to the combustor is shut off by the fuel cutoff valve, and the rotational speed of the turbine is set to the first reference value. The compressed air supplied to the metering valve is shut off by the fuel limiting valve until the second reference value larger than the value is reached, and the atmospheric pressure is supplied to the metering valve. The gas turbine engine according to claim 1.

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