JPH06241067A - Accessory control device for gas turbine engine - Google Patents

Abstract

PURPOSE:To greatly shorten the rising time of an engine having an accessory driven by a gas turbine engine in a system using a gas turbine engine. CONSTITUTION:A gas turbine engine is equipped with an auxiliary unit 13 driven by the rotary shaft of gas turbine engine 10 and an engine revolving speed control means 19 which accelerates the speed to the rated value, and an auxiliary unit control device is provided for decreasing the drive load of the auxiliary unit during the engine in acceleration and increasing the drive load of the accessory when the engine revolving speed attains the rated value.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an auxiliary machine controller for a gas turbine engine, and more particularly to an auxiliary machine controller for a single-shaft gas turbine engine in a gas turbine engine utilization system such as a gas turbine power generator.

[0002]

2. Description of the Related Art Conventionally, an auxiliary power supply is used.
Driven by a single-shaft gas turbine engine as an electric power system
Generator (hereinafter simply referred to as gas turbine generator)
There is known a system for generating electric power by using. Figure 8
Is directly connected to such a conventional single-shaft gas turbine engine GT.
Combined gas turbine generator G₁Power generation system with
Shows an example of the general configuration of the. Uniaxial gas turbine
In the engine GT, the intake air (intake) is compressed.
It is compressed in the fuel cell C and compressed in the combustor B.
Mixed with fuel Gf supplied by an eater (not shown)
Burned and burned.
After rotating the bin T, it becomes exhaust gas and is discharged to the atmosphere.
Will be issued. This turbine T has a main generator G₁Is that coaxial
It is directly connected to the top and has the same speed as the turbine T
And the main generator G₁Rotates to generate electricity. Main generator G
₁Field coil Fc ₁There is this field coil Fc₁
Field current If flowing in₁Adjustment of the main generator G₁Out of
Power can be controlled. Main generator G₁Power generation at
The generated AC power is the original purpose of the gas turbine generator.
Acts as a power supply
It

[0003] The combustor fuel flow rate Gf and the field field current the If ₁ supplied to the magnetic coil Fc ₁ supplied to B, the control circuit
It is controlled by Cont according to the operating condition of the engine. Therefore, the operating condition parameters such as the engine speed N ₁ , the discharge force P ₃ of the compressor C, and the outlet temperature Tc of the turbine T are input to the control circuit Cont from the gas turbine engine GT.

On the other hand, a reducer R / G is provided on the shaft of the gas turbine engine GT, and an auxiliary generator G ₂ is provided on the shaft reduced by the reducer R / G. Auxiliary generator G
₂ is provided to supplement the consumption of the system power supply which is the power supply of the control circuit Cont and the like, and normally, the battery voltage is monitored and the amount of power generation is controlled according to the battery capacity. The amount of power generation is usually controlled by the voltage regulator R so that the battery voltage becomes the specified voltage.

The operations of the gas turbine engine GT, the main generator G ₁ and the auxiliary generator G ₂ configured as described above are
This will be described below. First, when the gas turbine engine GT is started and reaches a rotational speed at which load operation is possible, a field current If ₁ is passed through the field coil Fc ₁ of the main generator G ₁ to generate power. On the other hand, the auxiliary generator G ₂ generates electric power for charging the auxiliary battery, and normally this kind of auxiliary generator G ₂ is supplied with power to the voltage regulator via the key switch. Moreover, when the number of revolutions of the power generator exceeds the power generation speed, the power is generated to charge the auxiliary battery. And the amount of power generation is
Depending on the battery discharge status, the control circuit Cont
Is controlled by the voltage regulator R independently of.

The provision of an auxiliary machine driven by a gas turbine engine is disclosed in Japanese Utility Model Publication No. 2-92039.

[0007]

In the above conventional technique, the control of the auxiliary generator G ₂ is independently performed independently of the control of the gas turbine engine GT and the main generator G ₁ side. Therefore, in an application such as an emergency generator, it is necessary to quickly raise the engine speed to a speed at which the main generator G ₁ can be operated under load, but the auxiliary generator G ₂ is generating power. In that case, there is a problem that the acceleration of the engine is extremely bad, which hinders the start of load operation of the main generator G ₁ .

Therefore, the present invention uses a gas turbine engine utilization system such as a gas turbine generator using a gas turbine engine, in which an auxiliary machine driven by a gas turbine engine such as the above-mentioned auxiliary generator G ₂ is operated as a gas. The purpose is to control the start-up of the turbine engine so as to be good.

[0009]

According to the present invention, there is provided a gas turbine engine having an auxiliary machine driven by a rotary shaft of the gas turbine engine and an engine speed control means for accelerating the engine speed to a rated speed. In a gas turbine engine accessory control device for reducing the drive load of the accessory during engine acceleration, and increasing the drive load of the accessory when the engine speed reaches the above rated speed. To be done.

[0010]

With the above-described structure, when the gas turbine engine needs to be accelerated, the drive load of the auxiliary machinery is reduced, and the necessary engine speed to start up to the rated speed is required. The time can be greatly reduced.
Further, when the engine speed reaches the rated speed, the auxiliary machine drive load is increased, so that the load on the engine is increased and the overshoot amount of the engine speed is reduced.

[0011]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of an auxiliary equipment control device for a gas turbine engine according to the present invention will be described below with reference to the drawings. FIG. 1 is a schematic configuration diagram showing a configuration of a gas turbine power generator that is an example of a gas turbine engine utilization system to which an auxiliary device control device for a gas turbine engine according to the present invention is applied,
Most of its components are equivalent to those in the conventional system shown in FIG. In the figure, 10 is a single-shaft gas turbine engine GT, which has a compressor 10 inside.
a, turbine 10b, speed reducer 10c, and combustor 10d
The has and 11 main generator G _1, 12 field coil Fc ₁ of the main generator G _1, 13 is an auxiliary generator G _2, 14 is a rectifier, 15 of the auxiliary generator G ₂ field coil Fc _2, 16 is a voltage regulator for the field current the If ₂ adjustment of auxiliary generator G _2, 17 is key switch, 18 a battery, 19 a field of the control circuit Cont, 20 is the main generator G ₁ It is a voltage regulator for adjusting the current If ₁ . Particularly, in the present embodiment, the voltage regulator 16 for the auxiliary power generator G ₂ 13 from the control circuit Cont19, ON / OFF control signal is supplied.

Single-shaft gas turbine engine GT and main generator G
Regarding the operation as the power supply device, which is the original purpose according to ₁ , the description in the above-mentioned conventional art can be referred to. Here, the control device of the auxiliary generator G ₂ to which the features of the present invention relate will be described. The auxiliary generator G ₂ 13 is a reduction gear, that is, a reduction gear 10c.
The field current If ₂ flowing through the field coil Fc ₂ 15 of the gas turbine engine GT is controlled by the voltage regulator 16. The voltage regulator 16 adjusts the field current If ₂ to control the output amount of the auxiliary generator G ₂ 13 so that the voltage of the battery 18 to be charged does not exceed a specified value. The AC output of the auxiliary generator G ₂ 13 is rectified by the rectifier 14 and converted into DC power, and the battery 18 is charged with the converted DC power.

The operation of the voltage regulator 16 is controlled by a control circuit.
It is on / off controlled by an on / off control signal from the Cont 19. That is, when the control signal from the control circuit Cont 19 is off, the voltage regulator 16 operates so that the field current If ₂ does not flow in the field coil Fc ₂ 15 of the auxiliary generator G ₂ 13, and thus the auxiliary generator is operated. G ₂ 13 does not generate power, but when the control signal from the control circuit Cont 19 is on, the voltage regulator 16 operates and the field current I flows to the field coil Fc ₂ 15 of the auxiliary generator G ₂ 13.
It is configured to flow f ₂ and cause the auxiliary generator G ₂ 13 to generate power for charging the battery 18. Further, the voltage regulator 16 detects and monitors the voltage of the battery 18, and also adjusts the field current If ₂ so that the battery voltage does not become an overvoltage exceeding a specified value. Incidentally, in the conventional technique shown in FIG.
Key the on / off control signal from this control circuit Cont19
It was taken out of the switch 17.

FIG. 2 is a block diagram showing the construction of an embodiment of the auxiliary equipment control device for a gas turbine engine according to the present invention. The construction of the control circuit Cont19 in FIG. 1, particularly the auxiliary generator G ₂ inside the control circuit Cont19. 13 for controlling whether to perform load operation, that is, the auxiliary generator G ₂
13 is a block diagram showing a configuration of a control unit for generating an on / off control signal to the control unit 13. FIG.

The control circuit Cont 19 is supplied with a rotational speed signal N ₁ of the gas turbine engine GT and a control signal Vacc for determining a target rotational speed of the gas turbine engine GT. In the control of the gas turbine engine GT by the control circuit Cont19, when the engine is started, the fuel is supplied via a fuel control system (not shown) so that the actual engine speed becomes the engine target speed determined by the Vacc signal. Flow rate Gf
Is adjusted.

That is, when the relationship between the target engine speed Ns and the measured engine speed N ₁ is Ns> N ₁ , the fuel flow rate Gf supplied to the engine is increased to accelerate the engine. Becomes When Ns <N ₁ , the fuel flow rate Gf decreases from that in the steady operation state, and the engine is decelerated. Further, in the case of Ns = N ₁ , it can be said that the engine is in a steady operation state because the measured rotation speed of the engine matches the target rotation speed Ns.

FIGS. 3 and 4 show examples of operation patterns of the emergency and general gas turbine generators, respectively, of which the engine speed N ₁ is in the idle state. In the rated state, it corresponds to this steady operation state. Here, the operation pattern of the gas turbine power generator of FIGS. 3 and 4 will be described. FIG. 3 shows an example of the operation pattern of the emergency power generator, and in applications such as the emergency power generator, it is necessary to start power generation immediately when it becomes necessary to generate power. Therefore, it is necessary to promptly accelerate the gas turbine engine to a rotational speed at which load operation for power generation can be performed. Therefore, the first pattern shown in FIG. 3 is that the load speed for power generation is quickly accelerated to a rotational speed at which load operation is possible,
I am trying to enable power generation. When the power generation is no longer necessary, the engine speed is once set to the idle state, the lubricating system oil temperature of the engine is lowered, and then the engine is stopped.

On the other hand, FIG. 4 shows an operation pattern of a general gas turbine power generator. Unlike the emergency generator, such a power generator first starts the engine and puts it in an idle state to stand by. And when you need to generate electricity,
The engine speed is raised to a speed at which power can be generated, and then load operation for power generation is performed. Further, if it is not necessary to carry out load operation for a long time, the engine speed is made to stand by in an idle state or the engine is stopped completely for the purpose of fuel saving, noise reduction and the like.

FIG. 5 shows that when the rotational speed of the gas turbine engine GT10 is accelerated from the idle state to the rated rotational speed at which the main generator G ₁ 11 can generate electric power, the auxiliary generator G ₂ 13 operates. The characteristics of the engine are shown when the engine is operating and when it is not operating. In order to accelerate the gas turbine engine GT10 is output horse power consumption and an external output horsepower of the compressor C (which is the turbine T, when the auxiliary generator G ₂ is operating, the output of the auxiliary generator G ₂ And that will be the horsepower consumed) and horsepower added. In the vicinity of the idle of the gas turbine engine GT10, since the output of the turbine T is very small, when the auxiliary generator G ₂ 13 is operating, it is not possible to take a large horsepower for accelerating the engine. , Especially near the idle, the acceleration is getting worse.

Therefore, when it is necessary to accelerate the engine, if the power generation function of the auxiliary generator G ₂ 13 is stopped, the time required to start the power generation by the main generator G ₁ 11 can be greatly shortened. it can. The control unit shown in FIG.
Therefore, the auxiliary generator G ₂ 13 has a configuration for determining whether to perform load operation and generating an ON / OFF control signal to the auxiliary generator G ₂ 13 and the control in FIG. Its function is realized by means of the input parameters N ₁ and Vacc to the circuit Cont 19. In FIG. 2, 21 is
Reference numeral 22 denotes an engine target rotation speed setting means for setting a target value Ns of the rotation speed when the gas turbine engine GT is operated by receiving the control signal Vacc, and 22 is an actual engine of the gas turbine engine GT receiving the rotation speed signal N _1. This is an engine speed detecting means for detecting the engine speed Nm.

The engine acceleration state detecting means 23 is for detecting whether or not the gas turbine engine GT is in an accelerating state. Under the condition that the target rotation speed Ns is larger than the measured rotation speed Nm (Ns> Nm), the control circuit Cont19
However, it controls to accelerate the engine by increasing the fuel flow rate Gf via a fuel control system (not shown) so that the measured rotation speed Nm approaches the target rotation speed Ns. Detects this state of (Ns> Nm).

The engine steady state detecting means 24 is for detecting whether or not the gas turbine engine GT is in a steady state, and under the condition that the target rotation speed Ns is equal to the measured rotation speed Nm (Ns = Nm). Indicates that the engine is in a steady state, and the engine steady state detection means 24 detects this (Ns = Nm) state. The engine deceleration state detection means 25 is for detecting whether or not the gas turbine engine GT is in a deceleration state. Under the condition that the target rotation speed Ns is smaller than the measured rotation speed Nm (Ns <Nm), the control circuit Cont1
9 controls to reduce the fuel flow rate Gf and decelerate the engine via a fuel control system (not shown) so that the measured revolution speed Nm approaches the target revolution speed Ns. 25 detects this state of (Ns <Nm).

The load operation area detection means 26 is for determining whether or not the rotation speed is such that the auxiliary generator G ₂ 13 can be operated under load. Generally, when starting a gas turbine engine, it is necessary to drive it by a starter (not shown) to a rotational speed at which the output of the turbine exceeds the horsepower consumed by the compressor. However, even at such a start, the auxiliary generator G ₂ The starting characteristics are improved when the load operation is not performed. Therefore, in the load operation area detection means 26, the engine speed at which the drive by the starter at the time of starting is finished is added to the engine speed with some margin, and the engine speed Nm is larger than the constant Nb. The state of (Nm> Nb) is detected. It should be noted that this constant Nb is set to a value of the rotational speed lower than the rotational speed of the engine at idle.

The generator on / off detecting means 27 is supplied with the detection output signals of the above-mentioned detecting means 23 to 26, and on / off controls the power generating function of the auxiliary generator G ₂ 13 based on these signals. It is for. Generator on /
The off detection means 27 is in a state where the signal from the load operation area detection means 26 is on, that is, (Nm> Nb), and the signal from the engine acceleration state detection means 23 is on, that is, (Ns> Nm). At some point, the auxiliary generator G ₂ 1
It controls so that the power generation function of 3 may be stopped. Then, in the other conditions, by driving an auxiliary generator G ₂ 13, to charge the auxiliary battery in a gas turbine power generation system by the power generating function. As a result, the time required from the start of the gas turbine power generator to the start of power generation of the main generator G ₁ 11 can be significantly shortened.

The control operation of the accessory control device for a gas turbine engine according to the present invention will be described with reference to the characteristic diagrams of FIGS. 6 and 7. First, in the case of accelerating the gas turbine engine GT10 and converging it to the specified rotation speed, only by adjusting the fuel flow rate Gf, as shown by the broken line in FIG. 6, when the rated rotation speed is reached, the engine rotation speed is exceeded. You can see the shoot,
According to the accessory control device of the gas turbine engine according to the present invention, the function of the auxiliary generator G ₂ 13 for charging the battery during engine acceleration is stopped, and the engine speed Nm is lower than the engine target speed Ns. By turning on the function of the auxiliary generator G ₂ 13 when Nm = Ns,
As shown by the solid line characteristic of, the braking action can be realized. This is because when the function of the auxiliary generator G ₂ 13 is always on, the auxiliary generator G ₂ is used when Nm = Ns.
Immediately after that the turn on the function of ₂ 13, in order to first auxiliary generator G ₂ 13 to cover the battery consumption is activated, because the braking action is exerted large relative acceleration of the engine speed.

Next, when decelerating the gas turbine engine GT10, as shown in FIG. 7, it is advantageous to decelerate the engine early in terms of noise when decelerating the gas turbine engine GT. When the function of the auxiliary generator G ₂ 13 is turned on, it is possible to decelerate faster than when the function is turned off. According to the accessory control device for the gas turbine engine of the present invention, the auxiliary generator G ₂ 13 is provided only when the engine is accelerated.
Since the function of is deactivated, there will be no hindrance to the characteristics during deceleration of the engine.

[0027]

As described above, according to the accessory control device for a gas turbine engine of the present invention, the drive load of the accessory is reduced during acceleration of the gas turbine engine, so that the load on the engine is reduced. The time required for the engine speed to reach the rated speed is shortened. Furthermore, when the number of revolutions of the gas turbine engine reaches the rated number of revolutions, the drive load of the auxiliary machine is increased,
The load on the engine is increased, and the overshoot amount of the engine speed can be reduced.

[Brief description of drawings]

FIG. 1 is a schematic configuration diagram showing a configuration of a gas turbine power generator which is an example of a gas turbine engine utilization system to which an auxiliary device control device for a gas turbine engine according to the present invention is applied.

FIG. 2 is a block diagram showing a configuration of an embodiment of a gas turbine engine accessory control device according to the present invention.

FIG. 3 is a characteristic diagram showing an example of an operation pattern of the emergency gas turbine power generator.

FIG. 4 is a characteristic diagram showing an example of an operation pattern of a general gas turbine power generator.

FIG. 5 is a characteristic diagram showing acceleration characteristics of a gas turbine engine.

FIG. 6 is a characteristic diagram illustrating a control operation of the accessory control device for the gas turbine engine according to the present invention.

FIG. 7 is a characteristic diagram illustrating the control operation of the accessory control device for a gas turbine engine according to the present invention.

FIG. 8 is a schematic configuration diagram showing an example of a general configuration of a conventional single-shaft gas turbine power generation system.

[Explanation of symbols]

10 ... Gas turbine engine GT 11 ... Main generator G ₁ 12 ... Field coil Fc ₁ 13 ... Auxiliary generator G ₂ 14 ... Rectifier 15 ... Field coil Fc ₂ 16 ... Voltage regulator R 17 ... Key switch 18 ... Battery 19 ... Control circuit Cont 21 ... Engine target speed setting means 22 ... Engine speed detecting means 23 ... Engine acceleration state detecting means 24 ... Engine steady state detecting means 25 ... Engine deceleration state detecting means 26 ... Load operating area detecting means 27 ... Power generation Machine on / off control means

Claims (1)

[Claims] 1. A gas turbine engine accessory control device for a gas turbine engine having an accessory driven by a rotary shaft of the gas turbine engine and an engine speed control means for accelerating the engine speed to a rated speed. In addition, it is characterized by comprising drive load control means for reducing the drive load of the auxiliary machine during engine acceleration and increasing the drive load of the auxiliary machine when the engine speed reaches the rated speed. Auxiliary equipment control device for gas turbine engine.