JPH0518266A - Quick response improving device for gas turbine - Google Patents

Abstract

PURPOSE:To improve quick response of speed and turbine output by calculating a variable inlet guide vane angle according to a total sum of a reference value based on the speed target value of a variable inlet guide vane and respective correction amounts based on a speed control deviation and the control deviation of the number of revolutions of a turbine, respectively. CONSTITUTION:In the control system of a gas turbine, a variable inlet guide vane is located to the inlet part of a compressor. In this case, a quick response improving device calculates a reference value alphas of a guide vane by means of a function device 54 based on a speed target value Vr. Based on the control deviation DV of a speed, a first correction amount alphaA of the guide vane is calculated by means of a function device 56. Further, based on a control deviation DN of the number of revolutions of a turbine, a second correction amount alphaB of the guide vane is calculated by means of the function device 58. Meanwhile, a total sum S of the reference value alphas and the first and second correction values alphaA and alphaB is calculated by means of an adder 60. Based on the calculated total sum S, an angle (an angle in the direction of the flow of inflow air to the vane train of a compressor) alpha of a guide vane is calculated by means of a maximum value selector 64.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a quick response improving device applied to a control device of a gas turbine for driving a mechanical device such as an automobile.

[0002]

2. Description of the Related Art FIG. 7 shows a control system of a conventional automobile gas turbine. Conventionally, a variable inlet guide vane (hereinafter, abbreviated as VIGV as necessary) is not generally installed at the inlet of the compressor 3. Alternatively, VIGV
Even if installed, no effective control method was found.

Here, the gas turbine vehicle to be controlled will be described with reference to FIG. The compressor 3 and the turbine 5 are arranged coaxially with the rotating shaft 4 so as to rotate, and the compressor 3 sucks air from the intake passage 1 and compresses it to increase the pressure and burns it through the passage 6. Send to room 7. The fuel is sent out by the pump 8, is sent to the combustion chamber 7 through the pipe 10 while the flow rate is adjusted by the adjusting valve 9, is mixed with air in the combustion chamber 7 and burns, becomes a high temperature gas and flows into the turbine 5. To do. The turbine 5 takes out the heat drop caused by the expansion of the gas as energy and generates rotational power to rotate the rotating shaft 4. The exhaust gas of the turbine 5 is discharged into the atmosphere through the flow path 11. The compressor 3 receives a part of the rotational power of the turbine 5 and performs the work of compressing air. Most of the rotational power of the turbine 5 rotates the output shaft 13 via the speed reducer 12. Further, the rotational power of the output shaft 13 rotates the power transmission shaft 15 via the continuously variable transmission 14, and this rotational power rotates the axle shaft 17 via the differential gear 16,
Wheels 18 attached to this axle 17 are rotated.
As a result, the vehicle runs.

The control of the gas turbine is performed by the control device 25 as follows. The driver sets the target vehicle speed V
_{When r} is given as the depression angle of the accelerator pedal 26, this speed target value V _r is transmitted to the control device 25 through the transmission line 27. Further, the sensor 19 detects the rotation speed N of the turbine 5 and transmits it to the control device 25 through the transmission line 20. Furthermore,
The sensor 21 detects the gas temperature T at the turbine inlet, the sensor 23 detects the vehicle speed V, and the transmission line 22,
It is transmitted to the control device 25 through 24. The control device 25 calculates the opening degree F of the control valve 9 from these detected values V _r , N, T and V and transmits it to the control valve 9 through the transmission line 28 to control the fuel flow rate. Further, the control device 25 controls the continuously variable transmission 14
Of the gear ratio R of the continuously variable transmission 1 through the transmission line 29.
4 to control the gear ratio.

FIG. 8 shows a configuration example of the control device 25, which will be described. In FIG. 8, the speed target value V _r generated by the accelerator pedal 26 is transmitted to the subtractor 34, and the speed V detected by the sensor 23 is also transmitted to the subtractor 34, where the speed V is calculated by the following equation (1). The control deviation DV is calculated and transmitted to the controller 36 via the transmission line 35.

[0006]

## EQU1 ## DV = V _r −V Equation (1)

The controller 36 calculates the target rotational speed value N _r of the turbine 5 by the proportional-plus-integral calculation according to the following equation (2) and transmits it to the subtractor 38 via the transmission line 37. However,
In equation (2), K _N is a proportional gain, T _N is an integration time constant,
t is time.

[0008]

[Equation 2]

Further, the rotation speed N from the sensor 19 is transmitted to the subtractor 38, where the control deviation DN of the turbine rotation speed is calculated by the following equation (3) and transmitted to the controller 40 through the transmission line 39.

[0010]

[Equation 3] DN = N _r −N (3)

In the controller 40, the valve opening required value F _r for the control valve 9 is calculated by the proportional-plus-integral calculation according to the following equation (4).
Is calculated and transmitted to the subtractor 48 via the transmission line 41. However, in the equation (4), K _F is a proportional gain, T _F is an integration time constant, and t is time.

[0012]

[Equation 4]

On the other hand, the constant device 42 corresponds to the turbine inlet temperature.
Temperature control value T_LGenerate and subtract through transmission line 43
Tell the vessel 44. This subtractor 44 outputs from the sensor 21
The turbine inlet temperature T is transmitted, and here, according to the following equation (5),
Turbine inlet temperature deviation DT _FIs calculated and the transmission line 45
Through the controller 46.

[0014]

[Equation 5] DT _F = _TL −T Equation (5)

The controller 46 calculates the valve opening correction amount DF according to the following equation (6) and sends it to the subtractor 48 via the transmission line 47. However, in the equation (6), K _L is a proportional gain.

[0016]

[Equation 6]

In the subtractor 48, the above-mentioned required valve opening degree F _r
And the valve opening correction value DF, the valve opening F is calculated by the following equation (7).
Is calculated and transmitted to the control valve 9 through the transmission line 28 to determine the valve opening.

[0018]

F = F _r −DF (7)

Next, the function unit 49 determines the temperature target value T of the turbine 5 which is determined corresponding to the speed, based on the speed target value V _r.
r is generated and transmitted to the subtractor 51 through the transmission line 50.
The turbine inlet temperature T from the sensor 21 is also transmitted to the subtractor 51, where the temperature deviation DT _R is calculated by the following equation (8).
Is calculated and transmitted to the controller 53 through the transmission line 52.

[0020]

DT _R = T−T _r (8)

The controller 53 calculates the gear ratio R by the proportional-plus-integral calculation according to the following equation (9) and transmits it to the continuously variable transmission 14 through the transmission line 29 to determine the gear ratio. However, in the equation (9), K _R is a proportional gain, T _R is an integration time constant, and t
Is time.

[0022]

[Equation 9]

According to the above-described gas turbine control device 25, the target value T _r of the turbine inlet temperature is set according to the speed target value V _r by the accelerator pedal 26, and the measured turbine inlet temperature T is the target value T _r. The gear ratio R of the continuously variable transmission 14 is adjusted to increase or decrease so as to match. Continuously variable transmission 1
As 4, a variable pulley ratio belt transmission or the like can be applied.

Further, as the actual velocity V measured the velocity target value V _r is matched, the rotation speed target value N _r of the turbine 5
Is increased or decreased to control the speed.

Further, the fuel control valve 9 is adjusted so that the actual turbine rotation speed N measured matches the rotation speed target value N _r.
The valve opening required value F _r is adjusted up and down to control the turbine speed. When the measured turbine inlet temperature T exceeds the limit value T _L , the valve opening correction value DF of the control valve 9
Is calculated, and the valve opening degree F is set by making a correction to reduce the required valve opening degree F _r .

Thus, the combustion flow rate is adjusted to a value corresponding to the valve opening, and the turbine speed is controlled while limiting the turbine temperature so that the temperature limit value is not significantly exceeded.

FIG. 9 shows an example of traveling characteristics under the control of the above-mentioned automobile and gas turbine.

[0028]

As can be seen from 21 seconds to 25 seconds in the running characteristic example shown in FIG. 9, in the conventional technique, the actual speed follows the increase of the speed target value. There is a problem that is delayed.

In this case, even if an attempt is made to increase the turbine rotation speed by increasing the fuel flow rate, the turbine inlet temperature is limited, so that the fuel injection is insufficient and the rotation speed is not rapidly increased. Therefore, it was not possible to increase the output by increasing the turbine speed and maintain good speed responsiveness.

In view of the above-mentioned conventional technique, it is an object of the present invention to provide a device for improving speed and turbine output responsiveness.

[0031]

The structure of the gas turbine speed response improving device according to the present invention is variable based on a target speed value V _r in a control system of a gas turbine having a variable inlet guide vane at an inlet portion of a compressor. Means for calculating a reference value α _S of the inlet guide vane angle, means for calculating a first correction amount α _A of the variable inlet guide vane angle based on the control deviation DV of the speed,
Means for calculating a second correction amount α _B of the variable inlet guide vane angle based on the control deviation DN of the turbine speed, and the reference value α
_A means for calculating the sum of _S , the first correction amount α _A, and the second correction amount α _B, and calculating the variable inlet guide vane angle α based on this sum is provided.

[0032]

As shown in FIG. 2, the variable inlet guide vanes (hereinafter referred to as V
IGV) 2 is a guide vane capable of changing the angle α of the flow direction of the inflowing air with respect to the blade row 3A of the compressor. Hereinafter, this angle α will be referred to as a VIGV angle. VI
When GV2 is provided at the inlet of the compressor, as shown in FIG. 3, when α = 0 degree is used as a reference, the intake air amount of the compressor decreases as α increases.

Therefore, by utilizing the above-mentioned characteristics of VIGV, the operation for increasing the air flow rate can be performed without increasing the turbine rotation speed, and the responsiveness is improved.
That is, the following methods are adopted. Initially VIG
It is assumed that the vehicle is operating with a large V angle α. When the speed increases, the VIGV angle α is changed from large to small.
As a result, the air flow rate to the compressor increases from the characteristic of FIG.

As the air flow rate increases, the gas flow rate through the turbine also increases, thus increasing turbine output. Therefore, without waiting for the increase in turbine speed, VIG
The operation of increasing the turbine output, that is, increasing the speed is possible only by decreasing the V angle α.

In the configuration of the device of the present invention, first, the speed target value V
V that can keep the efficiency of the gas turbine high corresponding to _r
Set the reference value α _S of the IGV angle. The tracking of the actual speed with respect to the increase of the target speed value V _r is delayed, and the speed limit deviation D
When V occurs, the first correction angle α _A is changed to the negative side with respect to DV, and this is added to the reference value α _S to decrease the VIGV angle α. As a result, the intake air flow rate of the compressor is increased, the gas flow rate of the turbine is increased, the output is increased in a responsive manner, and the speed is increased. Further, when the control of the actual rotation speed with respect to the increase of the target value of the turbine rotation speed is delayed and a control deviation DN of the turbine rotation speed occurs, the second correction angle α _B is changed to the negative side in accordance with DN, This is the reference value α
_In addition to _S , VIGV angle α is decreased. Also in this case, the intake air flow rate of the compressor is increased, the gas flow rate of the turbine is increased, the output is increased in a responsive manner, and the turbine rotational speed and thus the speed are increased. Thus, by the sum of the reference value α _S , the first correction amount α _A, and the second correction amount α _B ,
By correcting the reference value α _S , the quickness of following the increase in the target value of the speed and the turbine speed is improved, and
The obtained VIGV angle α becomes suitable.

[0036]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to FIGS. FIG. 1 shows a quick response improving device 32 according to the present invention.
An example in which is added to the control system of the conventional automobile gas turbine shown in FIG. Therefore, in FIG. 1, the same functional portions as those in FIG.

In FIG. 1, a VIGV (variable inlet guide vane) 2 as shown in FIG. 2 is installed at the inlet portion of the compressor 3, and an accelerator pedal 26 is connected to a speed response improving device 32 by a transmission line 27 to set a speed target. The value V _r is input, and the control deviation DN of the turbine speed from the control device 25 is transmitted to the transmission line 30.
Further, the speed control deviation DV is input through the transmission line 31. And this quick response improving device 3
2 calculates the VIGV angle α and transmits VI through the transmission line 33.
Report to GV2 and set VIGV angle to α. VIGV2
Uses a known servo mechanism to set the flow direction of the inflowing air with respect to the blade row of the compressor 3 at the set angle α. Note that DV is obtained from the output of the subtractor 34 in FIG. 8, and DN is obtained from the output of the subtractor 38 in FIG.

Next, referring to FIG. 4, an embodiment of an arithmetic circuit for realizing the quick response improving device 32 will be described. In this example,
The quick response improving device 32 is composed of function units 54, 56, 58, an adder 60, a constant unit 62, and a maximum value selector 64.

The function unit 54 outputs the velocity target value V _r to the transmission line 27.
Via the transmission line 55, and the reference value α _S of the VIGV angle is calculated by the following equation (10) and transmitted to the adder 60 via the transmission line 55. In the formula (10), a and b are constants.

[0040]

[Mathematical formula-see original document] [alpha] _S = -a * _Vr + b (10)

The reference value α _S is usually set to a large value at low speed to obtain a high thermal efficiency by setting a low air flow rate, and set to a small value at high speed to obtain a large output by increasing the air flow rate. To set. Expression (10) is a function selected with such an intention.

The function unit 56 inputs the speed control deviation DV through the transmission line 31, calculates the first correction value α _A from the following equation (11), and transmits it to the adder 60 through the transmission line 57. In the following equation (11), c is a positive coefficient, and the correction value α _A changes to the negative side as DV increases.

[0043]

[Formula 11] α _A = −c · DV Equation (11)

The function unit 58 is a control deviation D of the turbine speed.
N is input through the transmission line 30, the second correction value α _B is calculated by the following equation (12), and the adder 6 is input through the transmission line 59.
Tell 0. In Expression (12), d is a positive coefficient, and DN
Becomes larger, α _B changes to the negative side.

[0045]

[Formula 12] α _B = −d · DN Equation (12)

The adder 60 calculates the sum _S of the reference value α _S , the first correction value α _A and the second correction value α _{B from the} following equation (13).
Is calculated and transmitted to the maximum value selector 64 through the transmission line 61.

[0047]

[Equation 13] S = α _S + α _A + α _B Equation (13)

The constant unit 62 generates the numerical value 0 (zero) and transmits it to the maximum value selector 64 via the transmission line 63.

The maximum value selector 64 selects the maximum value of the sum S and zero according to the following equation (14), and this is selected as VIGV.
It is transmitted to the VIGV 2 through the transmission line 33 as the set value α of the angle. Accordingly, in this embodiment, the VIGV angle is α ≧ 0.
Is limited to.

[0050]

Α = Max (S, 0) Equation (14)

In the embodiment described above, the quick response improving device 32
First, the target velocity value V_rCorresponding to Gaster
Reference value α of VIGV angle that can keep bin efficiency high_S
Is set. Velocity target value V_rThe actual speed against the increase of
If the control deviation DV of the speed occurs due to the delay of the tracking of the degree V, D
The larger V is, the first correction value α_ATo the negative side,
This is the reference value α_SIn addition, the VIGV angle α is decreased. This
This increases the intake air flow rate of the compressor 3,
As a result, the gas flow rate of the turbine 5 increases and the output increases promptly.
Then, the speed V increases. Also, the turbine speed target
Value N_rOf the actual rotation speed N with respect to the increase of
If the control deviation DN of the bin rotation speed occurs, DN becomes large.
Second correction value α_BIs changed to the negative side, and this is the reference value
α_SIn addition, the VIGV angle α is decreased. Also in this case,
The intake air flow rate of the compressor 3 increases, so that the turbine
The gas flow rate of the engine 5 increases, and the output increases rapidly.
The bottle rotation speed N and thus the speed V increase. Like this
Quasi value α_SAnd the first correction amount α _AAnd the second correction amount α_BAnd total
Based on the sum, the reference value α_SBy modifying the speed and
Improving the quick response of the turbine speed to the target value increase
In addition, the obtained VIGV angle α becomes suitable.

5 and 6 show examples of running characteristics in which the operational effects of the quick response improving device 32 are shown in a typical form. In these figures, when accelerating from 20 to 27 seconds,
Since both the correction values α _A and α _B are decreased (negative), the set value α of the VIGV angle is decreased, which causes the turbine output to increase promptly, so that the speed V follows the target value V _r well. is made of. Further, for that reason, the turbine rotation speed does not have to be greatly increased, and the result is that the turbine inlet temperature does not rise extremely.

[0053]

According to the speed responsiveness improving apparatus of the present invention, when the speed control deviation DV is generated when the speed target value V _r is increased, the VIGV angle α is changed according to the DV and the turbine output is speedily changed. Is increased and acts so as to cancel the DV, so that there is an effect that the tracking delay of the speed is reduced. Further, even when the target value of the turbine speed is increased, if the control deviation DN of the speed occurs, the VIGV angle α changes according to the DN, and the turbine output increases in a speedy manner to cancel the DV. Therefore, there is an effect that the delay in following the turbine speed is reduced, which in turn reduces the delay in following the speed. This improvement in speed followability improves the operating performance of various machines powered by a gas turbine, such as the operating performance of a gas turbine automobile.

[Brief description of drawings]

FIG. 1 is a diagram showing a control system of a gas turbine for an automobile equipped with a rapid response improving device of the present invention.

FIG. 2 is an explanatory view of a variable inlet guide vane (VIGV).

FIG. 3 is a principle diagram of increasing the air flow rate by decreasing the variable inlet guide vane angle.

FIG. 4 is an arithmetic circuit diagram showing an embodiment of a rapid response improving device.

FIG. 5 is a transient response diagram of running characteristics showing an example of the action and effect of the present invention.

FIG. 6 is a transient response diagram of running characteristics showing an example of the action and effect of the present invention.

FIG. 7 is a diagram showing a control system of a conventional automobile gas turbine.

FIG. 8 is an arithmetic circuit diagram of an example of a control device conventionally used in a control system.

FIG. 9 is a transient response diagram showing an example of conventional running characteristics.

[Explanation of symbols]

 2 Variable inlet guide vanes (VIGV) 3 Compressor 4 Rotating shaft 5 Turbine 7 Combustor 8 Pump 9 Control valve 12 Reducer 14 Continuously variable transmission 16 Differential gear 17 Axle 19 Rotation speed detection sensor 21 Temperature detection sensor 23 Vehicle speed detection Sensor 25 Control device 26 Accelerator pedal 32 Speed response improving device 34, 38, 44, 48, 51 Subtractor 36, 40, 53 Proportional integral controller 42, 62 Constant device 46 Proportional controller 49, 54, 56, 58 Function unit 60 Adder 64 Maximum value selector

─────────────────────────────────────────────────── ─── Continuation of the front page (51) Int.Cl. ⁵ Identification code Internal reference number FI technical display location G05D 13/62 G 7361-3H

Claims (1)

Claim: What is claimed is: 1. A control system for a gas turbine having a variable inlet guide vane at an inlet portion of a compressor, wherein a reference value α _S of the variable inlet guide vane angle is calculated based on a target velocity value V _r. Means, a means for calculating a first correction amount α _A of the variable inlet guide vane angle based on the speed control deviation DV, and a second correction amount α of the variable inlet guide vane angle based on the turbine speed control deviation DN. Means for calculating _B , means for calculating the sum of the reference value α _S , the first correction amount α _A, and the second correction amount α _B, and calculating the variable inlet guide vane angle α based on this sum. An apparatus for improving the quick response of a gas turbine, comprising: