CN102953835B - Control device and control method for stable running of gas turbine - Google Patents
Control device and control method for stable running of gas turbine Download PDFInfo
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- CN102953835B CN102953835B CN201210445651.2A CN201210445651A CN102953835B CN 102953835 B CN102953835 B CN 102953835B CN 201210445651 A CN201210445651 A CN 201210445651A CN 102953835 B CN102953835 B CN 102953835B
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Abstract
The invention provides a control device a control method for the stable running of a gas turbine, belonging to the technical field of the control of the gas turbine. The device comprises a start control module, a revolving speed control module, a revolving speed load control module, an acceleration control module, a temperature control module, a load shedding control module, a maximum value control module, a minimum value control module, a minimum value selector and a maximum value selector. According to the invention, the safety and the stability of the running process of the gas turbine can be guaranteed, the joint debug time of the gas turbine can be shortened, and the gas turbine debugging cost for the debug control system can be reduced; and a master control system is designed by the method adopting the minimum value selector, and the control system is debugged in cooperation with a simulated mathematical model, so that the rationality and the safety of the control system can be guaranteed.
Description
Technical field
The invention belongs to combustion machine control technique field, be specifically related to a kind of stable operation control gear and controlling method of gas turbine.
Background technique
Turbine control system is generally divided into successive control system, protective system and master control system; and master control system is the core that combustion machine is controlled, combustion machine is the adjusting to fuel quantity by the master control system control of controlling the start-stop process of combustion machine and the whole process of operation.Thereby the algorithm of master control system plays conclusive effect to controlling the safe and stable operation of combustion machine, and algorithm rationally whether with whether stablize and can only just can be verified during with combustion machine cooperation in control system, thereby the test run expense that has greatly extended combustion machine debug time and therefore produced.
Summary of the invention
For the deficiencies in the prior art, the present invention proposes a kind of stable operation control gear and controlling method of gas turbine, to reach, improves system run all right and reliability, saving adjusting time and cost-saving object.
A kind of stable operation control gear of gas turbine, comprise starting control module, rotational speed control module, rotating speed load control module, accelerate control module, temperature control modules and removal of load control module, also comprise maximum value limiting module, minimum value limiting module, minimum value selector and maximum-value selector, wherein
Maximum value limiting module: be for setting the peaked device of output fuel quantity;
Minimum value limiting module: be for setting the device of output fuel quantity minimum value;
Minimum value selector: be for from starting control module, rotational speed control module, rotating speed load control module, accelerate the fuel quantity signal that control module, temperature control modules and six modules of removal of load control module export and select minimum value, avoid protecting unit under normal operation, to occur the device of overtemperature, overspeed situation;
Maximum-value selector: be for selecting maximum value between the fuel quantity signal from minimum value selector output and the fuel quantity minimum value signal of setting, avoid finally exporting fuel quantity too low, causing the flame-out device of gas turbine.
The controlling method that adopts the stable operation control gear of gas turbine, comprises the following steps:
Step 1, obtain the data of gas turbine steady operational status, comprise rotor speed, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity;
Step 2, according to the constraint of the rotor speed of gas turbine steady operational status and atmospheric temperature, relation between rotor speed described in determining step 1, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity, specific as follows:
Step 2-1, the rotor speed during by a certain atmospheric temperature, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power and combustion machine unit efficiency are made as reference point, and the parameter during to other temperature is carried out zero dimension processing according to said reference point;
Step 2-2: adopt least square fitting to go out the function relation between rotor speed, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity at each temperature;
Step 2-3: the function curve of adjacent two temperature is made to interpolated value and process, obtain the function relation of rotor speed, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity, atmospheric temperature;
Step 2-4, definite control parameter that affects gas turbine stable operation; Above-mentioned key control parameter comprises: speed/load, combustion machine turbine inlet temperature, rotor speed acceleration and fuel quantity, and wherein, speed/load is the corresponding rotor speed reference value of each load value of gas turbine; The value of combustion machine turbine inlet temperature can not surpass the protection temperature of gas turbine; Rotor speed acceleration reference value value standard depends on the performance of unit, by the relation in rotor speed and cycle being obtained to the reference value of stable operation rotor speed acceleration; Fuel quantity minimum value depends on the flame-out fuel delivery of main frame, and maximum value depends on the fuel quantity that the maximum opening of fuel control valve is exported;
Step 3, startup gas turbine, by rotor speed raising speed to idling rating rated speed, starting control module is according to the fuel regulation signal of the variation adjustment output of rotor speed, and minimum value selector is according to selecting fuel quantity minimum value principle to monitor in real time the output value of fuel quantity;
Step 4, gas turbine rotor rotating speed are promoted to the rotating speed reference value of Gas Turbine Power turbine, now rotor and turbine reach sync state, rotating speed load control module is according to above-mentioned rotating speed reference value according to the control signal of indifference control mode output fuel quantity, and minimum value selector is according to selecting fuel quantity minimum value principle to monitor in real time the output value of fuel quantity simultaneously;
Step 5, gas turbine are connected to the grid; Rotating speed load control module gathers the actual rotor rotating speed under a certain load, and actual rotor rotating speed and rotor speed reference value are done poor, above-mentioned difference, as the input that has poor control system, has poor revolution speed control system output fuel regulation signal to minimum value selector; Accelerate control module and gather actual rotor rotating speed accekeration, and with acceleration reference value do poor, the input using above-mentioned acceleration difference as Acceleration Control link, acceleration control system output fuel regulation signal is to minimum value selector; Temperature control modules gathers actual turbine outlet stagnation temperature, and above-mentioned actual turbine outlet stagnation temperature and combustion machine turbine inlet temperature are done poor, and the input using said temperature difference as temperature control system, temperature control system output fuel regulation signal is to minimum value selector;
Step 6, minimum value selector are according to the fuel regulation signal of selecting fuel quantity minimum value principle real-time selection step 3, step 4, step 5, removal of load control module and minimum value limiting module to export;
Step 7, according to the fuel quantity minimum value signal of minimum value selector output and the fuel quantity minimum value signal limiting, maximum-value selector is selected the above-mentioned fuel regulation signal of higher value in both;
Step 8, according to the fuel quantity signal of selected higher value in step 7, control fuel valve position, realize the output that changes in real time fuel quantity, control gas turbine operation in steady state.
In described step 5, having poor control system is a ratio inertial element.
In described step 5, Acceleration Control link is a proportional integral link.
In described step 5, temperature control system is an integration proportional component.
Advantage of the present invention:
Stable operation control gear and the controlling method of a kind of gas turbine of the present invention, guaranteed the safety and stability of combustion machine running, shortened the combustion machine combined debugging time, reduced the combustion machine debugging cost occurring for debugging control system, adopt the method design master control system of minimum value selector, and be aided with simulation mathematical model control system is debugged, thereby the rationality of Guarantee control system and Security.
Accompanying drawing explanation
Fig. 1 is the stable operation control gear structured flowchart of an embodiment of the present invention gas turbine;
Fig. 2 is the stable operation control block diagram of an embodiment of the present invention gas turbine;
Fig. 3 is an embodiment of the present invention liquid fuel servo system control block diagram;
Fig. 4 is the controlling method flow chart of the stable operation control gear of an embodiment of the present invention gas turbine;
Fig. 5 is that an embodiment of the present invention is with the method flow diagram of the contact between each parameter of formal description of mathematical model;
Fig. 6 is an embodiment of the present invention compressor pressure ratio analogous diagram;
Fig. 7 is an embodiment of the present invention gas compressor delivery temperature analogous diagram;
Fig. 8 is an embodiment of the present invention turbine outlet delivery temperature analogous diagram.
Embodiment
Below in conjunction with accompanying drawing, the embodiment of the present invention is described further.
As shown in Figure 1, a kind of stable operation control gear of gas turbine, comprise starting control module, rotational speed control module, rotating speed load control module, accelerate control module, temperature control modules and removal of load control module, also comprise maximum value limiting module, minimum value limiting module, minimum value selector and maximum-value selector, wherein, maximum value limiting module is for setting the peaked device of output fuel quantity; Minimum value limiting module is for setting the device of output fuel quantity minimum value; Minimum value selector is that the fuel quantity signal for exporting from starting control module, rotational speed control module, rotating speed load control module, acceleration control module, temperature control modules and six modules of removal of load control module is selected minimum value, avoids protecting unit under normal operation, to occur the device of overtemperature, overspeed situation; Maximum-value selector is for selecting maximum value between the fuel quantity signal from minimum value selector output and the fuel quantity minimum value signal of setting, avoid finally exporting fuel quantity too low, causing the flame-out device of gas turbine.
Starting control module, for by motor raising speed to rated condition; When gas turbine enters after idling rating, in boosting velocity procedure according to the rotating speed benchmark N1 of rotational speed control module to fuel valve position signal FSR_N1, now starting process module output fuel regulation signal FSR_STRMP constantly increases, until rotor speed reaches the rotating speed reference value N1 that rotational speed control module sets, minimum value selector is according to selecting fuel quantity minimum value principle to monitor in real time the output value of fuel quantity.
Rotational speed control module, take N1 as rotating speed raising speed desired value for setting, and in present embodiment, desired value is N1.
Rotating speed load control module, mainly realizes the constant of rotating speed, and it comprises that droop control is controlled and non differential regulation is controlled.When unit not grid-connected, combustion machine raising speed is to rated speed, it is the rotating speed reference value of Gas Turbine Power turbine, now rotor and turbine reach sync state, and rotating speed load control module provides corresponding fuel valve position signal FSR_SPL according to the rotating speed benchmark N3 of Gas Turbine Power turbine by indifference mode.As shown in Figure 2, after grid-connected breaker closing, rotating speed load control module has poor control mode by employing, rotating speed load control module gathers the actual rotor rotating speed under a certain load, and actual rotor rotating speed TNH and rotor speed reference value TNR are done poor, above-mentioned difference is as there being the poor input of controlling, and this fuel regulation signal of controlling output is to minimum value selector, having poor control is a ratio inertial element, proportional control factor W is the inverse of diversity factor, by removal of load or drop load test in electric, the parameter of this part is carried out to verification.
Temperature control modules, combustion machine turbine inlet temperature is the important parameter of weighing gas turbine performance, owing to being difficult to measure temperature, therefore by controlling delivery temperature restriction combustion machine turbine inlet temperature, when combustion machine turbine inlet temperature reference value TTRX is greater than combustion machine turbine outlet stagnation temperature TTXM, the output of minimum value selector locking temperature control modules; When combustion machine turbine inlet temperature reference value TTRX is less than combustion machine turbine outlet stagnation temperature TTXM, temperature control modules starts, temperature control modules output signal FSR_TMP monitors the fuel gas temperature of the front import of power turbine in real time, the temperature trend in this cross section can represent the temperature trend of turbine entrance, and its limit value is determined by the performance of unit.And by minimum value selector, the fuel gas temperature of import before power turbine is limited in below controlling value.
When combustion machine is in removal of load or start-up course, in order to suppress the hypervelocity of rotor, be provided with acceleration control module, accelerate control module by actual rotor Differential of Speed being obtained to the acceleration of rotor, it is poor that above-mentioned acceleration and acceleration reference value are done, and adopts a proportional integral link to realize.Accelerate the acceleration of three rotors of control module output signal FSR_ACC real time monitoring, and by minimum value selector, rotor acceleration is limited in below controlling value.
Removal of load control module for when unit under larger load suddenly from guaranteeing when (being called removal of load) that with grid disconnection unit is not occurring to get back to synchronous speed excess revolutions and flame-out prerequisite.
Maximum value limiting module and minimum value limiting module for unit raising speed, synchronous and generate electricity by way of merging two or more grid systems during, the significantly variation of fuel limitation amount, steady to guarantee unit operation.
As shown in Figure 1, the output signal of seven modules except minimum value limiting module FSR_MIN enters MIN minimum value selector simultaneously, at this, select fuel quantity minimum value person in eight input signals, enter MAX maximum-value selector with the output signal of minimum value limiting module FSR_MIN more simultaneously, at this, select in two input signals fuel quantity higher value as the actual execution fuel control command signal FSR in this moment.Therefore in fact in eight modules of synchronization, only have a module really working.
As shown in Figure 3, model for fuel system, what adopt is the thought of theoretical modeling, the 1907 large flow fuel metering valves of take are core, this metering valve mainly contains two-part and forms, equal differential pressure valve and metering valve, the characteristic of last comprehensive equal differential pressure valve and metering valve, the model of the final fuel servovalve forming.
For the foundation of the model of combustion machine body, employing be the method for laboratory data modeling.According to laboratory data, the indivedual important parameters of combustion machine are carried out to static characteristic simulation, be then aided with Dynamic mode.
The controlling method that adopts the stable operation control gear of gas turbine, as shown in Figure 4, comprises the following steps:
Step 1, obtain the data of gas turbine steady operational status, comprise rotor speed N, blower outlet stagnation temperature T2, blower outlet stagnation pressure P2, gas compressor consumed power NK, turbine outlet stagnation temperature T4, turbine output power NT, combustion machine unit efficiency KPD and fuel quantity X;
Step 2, according to the constraint of the rotor speed of gas turbine steady operational status and atmospheric temperature, relation between rotor speed described in determining step 1, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity, specific as follows:
Step 2-1, the rotor speed of selecting Ta=15 ℃ of atmospheric temperature, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power and combustion machine unit efficiency are made as reference point (reference value by user from setting), and the parameter that to other temperature is according to said reference point is carried out zero dimension processing;
Step 2-2: adopt least square fitting to go out the function relation between rotor speed, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity at each temperature;
In the embodiment of the present invention, select-40 ℃ ,-30 ℃ ,-15 ℃, 0 ℃, 15 ℃, 30 ℃ ,-45 ℃ seven temperature to set up the function relation between each parameter and fuel quantity at each temperature, concrete formula is as follows:
When temperature is-40 ℃:
F(N)=1.5609X-0.5412;
F(T2)=0.0638X+0.819
F(P2)=0.2995X+0.8447
F(NK)=0.1395X+1.0021
F(T4)=0.3687X+0.4632
F(NT)=0.7767X+0.3105
F(KPD)=-3.3696X4+13.219X3-19.963X2+14.174X-3.0533
Wherein: X represents fuel quantity; F (N) represents that rotating speed is about the function of fuel quantity; F (T2) represents that blower outlet stagnation temperature is about the function of fuel quantity; F (P2) represents that blower outlet stagnation pressure is about the function of fuel quantity; F (NK) represents that gas compressor consumed power is about the function of fuel quantity; F (T4) represents that turbine outlet stagnation temperature is about the function of fuel quantity; F (NT) represents that turbine output power is about the function of fuel quantity; F (KPD) represents that combustion machine unit efficiency is about the function of fuel quantity;
When temperature is-30 ℃:
F(N)=1.514X-0.4786
F(T2)=0.0583X+0.8438
F(P2)=0.2941X+0.8304
F(NK)=0.1237X+0.9967
F(T4)=0.378X+0.4707
F(NT)=0.747X+0.3355
F(KPD)=-3.5725X4+13.594X3-19.872X2+13.621X-2.749
When temperature is-15 ℃:
F(N)=1.4562X-0.4207
F(T2)=0.0585X+0.8803
F(P2)=0.2898X+0.808
F(NK)=0.1192X+0.9861
F(T4)=0.4125X+0.475
F(NT)=0.7186X+0.3556
F(KPD)=-3.4374X4+13.103X3-19.059X2+12.879X-2.4651
When temperature is 0 ℃:
F(N)=1.5012X-0.4867
F(T2)=0.0528X+0.9159
F(P2)=0.2763X+0.7681
F(NK)=0.0979X+0.9467
F(T4)=0.412X+0.536
F(NT)=0.727X+0.3043
F(KPD)=-4.4613X4+16.297X3-22.869X2+15.071X-3.0341
When temperature is 15 ℃:
F(N)=1.4702X-0.4515
F(T2)=0.0614X+0.9382
F(P2)=0.2755X+0.7292
F(NK)=0.1076X+0.8921
F(T4)=0.4478X+0.5512
F(NT)=0.7181X+0.2901
F(KPD)=-4.0379X4+14.453X3-20.043X2+13.192X-2.5623
When temperature is 30 ℃:
F(N)=1.4646X-0.4338
F(T2)=0.0636X+0.9601
F(P2)=0.2766X+0.6903
F(NK)=0.1047X+0.8406
F(T4)=0.4799X+0.5717
F(NT)=0.714X+0.2696
F(KPD)=-6.6666X4+21.166X3-26.066X2+15.323X-2.7651
When temperature is 45 ℃:
F(N)=1.4641X-0.4205
F(T2)=0.0556X+0.9937
F(P2)=0.2762X+0.6541
F(NK)=0.0838X+0.8092
F(T4)=0.5216X+0.5906
F(NT)=0.7027X+0.258
F(KPD)=-8.6585X4+26.083X3-30.338X2+16.752X-2.8763
Step 2-3: the function curve of adjacent two temperature is made to interpolated value and process, obtain the function relation of each parameter and fuel quantity, atmospheric temperature;
A. rotating speed is about the function relation of fuel quantity, atmospheric temperature
-40℃～-15℃：F(N)=-0.004188Xt+1.39338X+0.00482t+0.1928
-15℃～0℃：F(N)=-0.003Xt+1.5012X-0.0044t-0.04867
0℃～30℃：F(N)=-0.00122Xt+1.5012X-0.001763333t-0.4867
30℃～45℃：F(N)=-0.0000333333Xt+1.4656X+0.000887t-0.4604
Wherein, t is atmospheric temperature;
B. blower outlet stagnation temperature is about the function relation of fuel quantity, atmospheric temperature
-40℃～45℃：F(T2)=-0.00002Xt+0.0592X+0.002t+0.9059
C. blower outlet stagnation pressure is about the function relation of fuel quantity, atmospheric temperature
-40℃～-15℃：F(P2)=-0.000388Xt+0.28398X-0.001468t+0.786
-15℃～0℃：F(P2)=-0.0009Xt+0.2763X-0.00266t+0.7681
0℃～45℃：F(P2)=-0.00000222222Xt+0.2763X-0.00253333t+0.7681
D. gas compressor consumed power is about the function relation of fuel quantity, atmospheric temperature
-40℃～-15℃：F(NK)=-0.000812Xt+0.10702X-0.00064t+0.9765
-15℃～0℃：F(NK)=-0.00142Xt+0.0979X-0.002626667t+0.9467
0℃～30℃：F(NK)=0.000226667Xt+0.0979X-0.003536667t+0.9467
30℃～45℃：F(NK)=-0.001393333Xt+0.1465X-0.00209t+0.9034
E. turbine outlet stagnation temperature is about the function relation of fuel quantity, atmospheric temperature
-40℃～-30℃：F(T4)=0.00093Xt+0.4059X+0.00075t+0.4932
-30℃～-15℃：F(T4)=0.0023Xt+0.447X+0.000286667t+0.4793
-15℃～0℃：F(T4)=-0.0000333333Xt+0.412X+0.004066667t+0.536
0℃～45℃：F(T4)=0.002435556Xt+0.412X+0.001213t+0.536
F. turbine output power is about the function relation of fuel quantity, atmospheric temperature
-40℃～-15℃：F(NT)=-0.002324Xt+0.68374X+0.001804t+0.3827
-15℃～0℃：F(NT)=0.00056Xt+0.727X-0.00342t+0.3043
0℃～45℃：F(NT)=-0.00054Xt+0.727X-0.001028889t+0.3043
G. fire machine unit efficiency about the function relation of fuel quantity, atmospheric temperature
-40℃～11℃：
F(KPD)=-0.002712X
4t-3.4781X
4-0.00464X
3t+13.033X
3+0.0362X
2t-18.5166X
2-0.0518Xt+12.10
2X+0.023528t-2.11218
11℃～45℃：
F(KPD)=-0.15402X
4t-1.7276X
4+0.387667X
3t+8.638X
3-0.343166667X
2t-14.8955X
2+0.118667Xt
+11.412X-0.01047t-2.4053
Step 2-4, definite control parameter that affects gas turbine stable operation; Above-mentioned key control parameter comprises: speed/load, combustion machine turbine inlet temperature, rotor speed acceleration and fuel quantity, and wherein, speed/load is the corresponding rotor speed reference value of each load value of gas turbine; The value of combustion machine turbine inlet temperature can not surpass the protection temperature of gas turbine; Rotor speed acceleration reference value value standard depends on the performance of unit, by the great many of experiments of the relation in rotor speed and cycle being obtained to the reference value of stable operation rotor speed acceleration; Fuel quantity minimum value depends on the flame-out fuel delivery of main frame, and maximum value depends on the fuel quantity that the maximum opening of fuel control valve is exported;
Above-mentioned value is generally according to the difference of unit and difference; protection temperature at example Middle combustion engine turbine inlet temperature of the present invention is 650 degrees Celsius; rotor speed acceleration reference value is 100rpm, and fuel quantity minimum value value is 1200 kgs/hour, and maximum value is 9000 kgs/hour.
Step 3, startup gas turbine, by rotor speed raising speed to idling rating rated speed, starting control module is according to the control signal of the variation adjustment output fuel quantity of rotor speed, and minimum value selector is according to selecting fuel quantity minimum value principle to monitor in real time the output value of fuel quantity;
Step 4, gas turbine rotor rotating speed are promoted to the rotating speed reference value of Gas Turbine Power turbine, now rotor and turbine reach sync state, rotating speed load control module is according to above-mentioned rotating speed reference value according to the control signal of indifference control mode output fuel quantity, and minimum value selector is according to selecting fuel quantity minimum value principle to monitor in real time the output value of fuel quantity simultaneously;
Step 5, gas turbine are connected to the grid; Rotating speed load control module gathers the actual rotor rotating speed under a certain load, and actual rotor rotating speed and rotor speed reference value are done poor, above-mentioned difference, as the input that has poor control system, has poor revolution speed control system output fuel regulation signal to minimum value selector; Accelerate control module and gather actual rotor rotating speed accekeration, and with acceleration reference value do poor, the input using above-mentioned acceleration difference as Acceleration Control link, acceleration control system output fuel regulation signal is to minimum value selector; Temperature control modules gathers actual turbine outlet stagnation temperature, and above-mentioned actual turbine outlet stagnation temperature and combustion machine turbine inlet temperature are done poor, and the input using said temperature difference as temperature control system, temperature control system output fuel regulation signal is to minimum value selector;
Step 6, minimum value selector are according to the fuel quantity signal of selecting fuel quantity minimum value principle real-time selection step 3, step 4, step 5, removal of load control module and minimum value limiting module to export;
Step 7, according to the fuel quantity minimum value signal of minimum value selector output and the fuel quantity minimum value signal limiting, maximum-value selector is selected the above-mentioned fuel quantity signal of higher value in both;
Step 8, according to the fuel quantity signal of selected higher value in step 7, control fuel valve position, realize the output that changes in real time fuel quantity, control gas turbine operation in steady state.
In described step 5, having poor control system is a ratio inertial element.In described step 5, Acceleration Control link is a proportional integral link.In described step 5, temperature control system is an integration proportional component.
In the embodiment of the present invention, remove atmospheric temperature Ta=301K; Pa=101.3kPa; Rotor speed n=3000r/min; As shown in Figure 6, as shown in Figure 7, turbine outlet delivery temperature simulation result as shown in Figure 8 for gas compressor delivery temperature simulation result for compressor pressure ratio simulation result.By the contrast of simulation result and laboratory data, show correctness and the validity of this control system, this kind of Control System Design method has been successfully applied in the control of QD128 combustion machine and R0110 heavy combustion engine, state of a control safety and stability.
Claims (4)
1. the control method for stably operating of a gas turbine, the method adopts the stable operation control gear of gas turbine, comprise starting control module, rotational speed control module, rotating speed load control module, accelerate control module, temperature control modules and removal of load control module, it is characterized in that: also comprise maximum value limiting module, minimum value limiting module, minimum value selector and maximum-value selector, wherein, maximum value limiting module: be for setting the peaked device of output fuel quantity; Minimum value limiting module: be for setting the device of output fuel quantity minimum value; Minimum value selector: be for from starting control module, rotational speed control module, rotating speed load control module, accelerate the fuel quantity signal that control module, temperature control modules and six modules of removal of load control module export and select minimum value, avoid protecting unit under normal operation, to occur the device of overtemperature, overspeed situation; Maximum-value selector: be for selecting maximum value between the fuel quantity signal from minimum value selector output and the fuel quantity minimum value signal of setting, avoid finally exporting fuel quantity too low, causing the flame-out device of gas turbine; It is characterized in that: method comprises the following steps:
Step 1, obtain the data of gas turbine steady operational status, comprise rotor speed, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity;
Step 2, according to the constraint of the rotor speed of gas turbine steady operational status and atmospheric temperature, relation between rotor speed described in determining step 1, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity, specific as follows:
Step 2-1, the rotor speed during by a certain atmospheric temperature, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power and combustion machine unit efficiency are made as reference point, and the parameter during to other temperature is carried out zero dimension processing according to said reference point;
Step 2-2: adopt least square fitting to go out the function relation between rotor speed, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity at each temperature;
Step 2-3: the function curve of adjacent two temperature is made to interpolated value and process, obtain the function relation of rotor speed, blower outlet stagnation temperature, blower outlet stagnation pressure, gas compressor consumed power, turbine outlet stagnation temperature, turbine output power, combustion machine unit efficiency and fuel quantity, atmospheric temperature;
Step 2-4, definite control parameter that affects gas turbine stable operation; Above-mentioned key control parameter comprises: speed/load, combustion machine turbine inlet temperature, rotor speed acceleration and fuel quantity, and wherein, speed/load is the corresponding rotor speed reference value of each load value of gas turbine; The value of combustion machine turbine inlet temperature can not surpass the protection temperature of gas turbine; Rotor speed acceleration reference value value standard depends on the performance of unit, by the relation in rotor speed and cycle being obtained to the reference value of stable operation rotor speed acceleration; Fuel quantity minimum value depends on the flame-out fuel delivery of main frame, and maximum value depends on the fuel quantity that the maximum opening of fuel control valve is exported;
Step 3, startup gas turbine, by rotor speed raising speed to idling rating rated speed, starting control module is according to the fuel regulation signal of the variation adjustment output of rotor speed, and minimum value selector is according to selecting fuel quantity minimum value principle to monitor in real time the output value of fuel quantity;
Step 4, gas turbine rotor rotating speed are promoted to the rotating speed reference value of Gas Turbine Power turbine, now rotor and turbine reach sync state, rotating speed load control module is according to above-mentioned rotating speed reference value according to the control signal of indifference control mode output fuel quantity, and minimum value selector is according to selecting fuel quantity minimum value principle to monitor in real time the output value of fuel quantity simultaneously;
Step 5, gas turbine are connected to the grid; Rotating speed load control module gathers the actual rotor rotating speed under a certain load, and actual rotor rotating speed and rotor speed reference value are done poor, above-mentioned difference, as the input that has poor control system, has poor revolution speed control system output fuel regulation signal to minimum value selector; Accelerate control module and gather actual rotor rotating speed accekeration, and with acceleration reference value do poor, the input using above-mentioned acceleration difference as Acceleration Control link, acceleration control system output fuel regulation signal is to minimum value selector; Temperature control modules gathers actual turbine outlet stagnation temperature, and above-mentioned actual turbine outlet stagnation temperature and combustion machine turbine inlet temperature are done poor, and the input using said temperature difference as temperature control system, temperature control system output fuel regulation signal is to minimum value selector;
Step 6, minimum value selector are according to the fuel regulation signal of selecting fuel quantity minimum value principle real-time selection step 3, step 4, step 5, removal of load control module and minimum value limiting module to export;
Step 7, according to the fuel quantity minimum value signal of minimum value selector output and the fuel quantity minimum value signal limiting, maximum-value selector is selected the above-mentioned fuel regulation signal of higher value in both;
Step 8, according to the fuel quantity signal of selected higher value in step 7, control fuel valve position, realize the output that changes in real time fuel quantity, control gas turbine operation in steady state.
2. the control method for stably operating of gas turbine according to claim 1, is characterized in that: in described step 5, having poor control system is a ratio inertial element.
3. the control method for stably operating of gas turbine according to claim 1, is characterized in that: in described step 5, Acceleration Control link is a proportional integral link.
4. the control method for stably operating of gas turbine according to claim 1, is characterized in that: in described step 5, temperature control system is an integration proportional component.
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| CN103557081A (en) * | 2013-11-18 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Lightweight gas turbine control system |
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| CN104590529B (en) * | 2014-12-09 | 2017-06-30 | 倪杰峰 | The control method and device of ship energy saving navigation |
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| CN111219258B (en) * | 2020-03-04 | 2021-12-28 | 中国科学院工程热物理研究所 | PI controller design method for preventing integral saturation in engine control strategy switching |
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