CN103195730B - Compressor inlet adjustable guide vane is used to control the method for combustion turbine exhaustion temperature - Google Patents
Compressor inlet adjustable guide vane is used to control the method for combustion turbine exhaustion temperature Download PDFInfo
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- CN103195730B CN103195730B CN201310117901.4A CN201310117901A CN103195730B CN 103195730 B CN103195730 B CN 103195730B CN 201310117901 A CN201310117901 A CN 201310117901A CN 103195730 B CN103195730 B CN 103195730B
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Abstract
Compressor inlet adjustable guide vane is used to control the method for combustion turbine exhaustion temperature, relate to the method using gas turbine blower import adjustable guide vane to control delivery temperature, the method is on gas turbine, install exhaust gas temperature sensor and import adjustable guide vane angle measurement transmitter, the deviation of delivery temperature and setting value is sent into shift integral proportional plus integral controller, also can send into integration segregation ratio integral controller, the output of controller sends into compressor inlet adjustable guide vane actuator through amplitude limit.The method, by regulating compressor inlet adjustable guide vane angle, makes delivery temperature change by known rule.The present invention, relative to conventional method, improves the temperature controlled quality of gas turbine blower import adjustable guide vane, has less overshoot, improves the stable and whole efficiency of unit when Gas Turbine Combined-cycle runs.
Description
Technical field
The present invention relates to a kind of method that online use compressor inlet adjustable guide vane controls combustion turbine exhaustion temperature, relate to the temperature controlled shift integral proportional plus integral control of combustion turbine exhaustion and integration segregation ratio integral control.
Background technique
In Gas Turbine Combined-cycle, one of the effect of compressor inlet guide vane system is exactly raise the efficiency.Compressor inlet guide vane system can ensure that combustion turbine exhaustion temperature changes by known rule and meets the design intake temperature of exhaust heat boiler.When gas turbine band portion load, compressor inlet adjustable guide vane turns down in adjustable operating range, reduces air mass flow, makes air fuel ratio be unlikely to the too high of liter, to obtain the delivery temperature of maximum permission.Realize temperature by the adjustment of compressor inlet adjustable guide vane to control, the total efficiency of Gas Turbine Combined-cycle can be very significantly improved.
Compressor inlet adjustable guide vane control system plays very important effect in the control of gas turbine.Conventional compressor inlet adjustable guide vane temperature control system adopts traditional proportional plus integral controller, and input parameter is delivery temperature and delivery temperature benchmark, to its difference integration, until difference is zero.In real process, the transducible leaf divergence of compressor inlet is determined by the project organization of import adjustable guide vane, also needs a limiter to limit its regulation range.This method integral coefficient is constant, change, uncertainty etc. when industrial process due to reality exists, in regulating and controlling process, integral coefficient has been got greatly and can have been produced overshoot even saturation integral, having got little can not eliminate static deviation, affects Control platform to a certain extent.
Summary of the invention
The problems such as the overshoot that the object of the invention is not easily to determine to solve existing gas turbine blower import adjustable guide vane temperature controlled processes middle controller parameter, controlling to produce does not meet the demands, use integration segregation ratio integral control or shift integral proportional plus integral control, according to inclined extent determination integration amount, to avoid producing excessive overshoot, ensure the precision controlled, improve the efficiency of Gas Turbine Combined-cycle.
In order to realize above-mentioned object, technological scheme of the present invention is as follows:
Use compressor inlet adjustable guide vane to control a method for combustion turbine exhaustion temperature, it is characterized in that the method comprises the following steps:
A1). at the N number of delivery temperature thermocouple of combustion turbine exhaustion chamber indoor location, N is the number of delivery temperature thermocouple, calculates delivery temperature mean value T according to the measured value of this N number of delivery temperature thermocouple
flat, outlet air temperature set value is designated as T
if, the delivery temperature mean value T in kth moment
flatwith outlet air temperature set value T
ifdeviation be designated as e (k), as the input of controller;
B1). the temperature controlled proportional plus integral controller parameter of compressor inlet adjustable guide vane of adjusting, wherein proportional action constant is designated as K
p, integral action constant is designated as K
i; Then integration segregation ratio integral controller is designed, with the proportional action constant K of proportional plus integral controller
pas the proportional action constant of integration segregation ratio integral controller, the integration segregation ratio integral controller kth moment integral action coefficient be designated as f
be separated[e (k)], obtains the integral action constant f in kth moment
be separated[e (k)] × K
i; Or design shift integral proportional plus integral controller, with the proportional action constant K of proportional plus integral controller
pas the proportional action constant of shift integral proportional plus integral controller, the integral action coefficient in shift integral proportional plus integral controller kth moment is designated as f
speed change[e (k)]; Obtain the integral action constant f in kth moment
speed change[e (k)] × K
i;
C1). by delivery temperature mean value T
flatwith outlet air temperature set value T
ifdeviation, send into shift integral proportional plus integral controller, or send into integration segregation ratio integral controller; By the output of shift integral proportional plus integral controller or integration segregation ratio integral controller through compressor inlet adjustable guide vane mechanical trip amplitude limit, send into actuator and regulate the transducible leaf divergence of compressor inlet, finally realize temperature and control.
In technique scheme, for B1) the integral action coefficient f in integration segregation ratio integral controller kth moment
be separated[e (k)]:
Wherein, Δ T is that gas turbine enters the exhaust temperature using compressor inlet adjustable guide vane to control combustion turbine exhaustion temperature stage
The width of degree span; The integral action coefficient f in shift integral proportional plus integral controller kth moment
speed change[e (k)]:
Wherein, Δ T is that gas turbine enters the width using compressor inlet adjustable guide vane to control the delivery temperature span of combustion turbine exhaustion temperature stage.
The present invention compared with prior art, have the following advantages and the technique effect of high-lighting: use integration segregation ratio integral control or shift integral proportional plus integral control, according to the size of the deviation adjustment integral action of delivery temperature and setting value, prevent because the large vibration that causes of saturation integral and overshoot, make controller have higher quality, stability and the working efficiency of gas turbine operation can be improved.In addition, this method does not eliminate integral action completely, can eliminate delivery temperature static deviation, ensures control accuracy.
Accompanying drawing explanation
Fig. 1 uses compressor inlet adjustable guide vane to control the hardware pipeline block diagram of combustion turbine exhaustion temperature.
Fig. 2 uses compressor inlet adjustable guide vane to control the FB(flow block) of combustion turbine exhaustion temperature.
The step response curve of several different controlling method of Fig. 3.
Fig. 4 integration separation integral function coefficient curve.
Fig. 5 shift integral integral action coefficient curve.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described further.
Fig. 1 uses compressor inlet adjustable guide vane to control the hardware pipeline block diagram of combustion turbine exhaustion temperature, and Fig. 2 uses compressor inlet adjustable guide vane to control the FB(flow block) of combustion turbine exhaustion temperature, and its specific implementation method comprises the following steps:
1). at the N number of delivery temperature thermocouple of combustion turbine exhaustion chamber indoor location, N is the number of delivery temperature thermocouple, calculates delivery temperature mean value T according to the measured value of this N number of delivery temperature thermocouple
flat, outlet air temperature set value is designated as T
if;
T
MAX＝max(T
1+T
2+...+T
N)
T
MIN＝min(T
1+T
2+...+T
N)
Wherein, T
1, T
2..., T
nbe respectively the 1st, 2 ..., the measured value of N number of delivery temperature thermocouple, T
mAXfor the maximum value of this N number of delivery temperature thermocouple, T
mINfor the minimum value of this N number of delivery temperature thermocouple.T
flatfor N number of delivery temperature thermocouple measurements removes the later mean value of max min.
E (k)=T
flat-T
if
Wherein, e (k) deviation that is kth moment delivery temperature mean value and outlet air temperature set value;
2). use experience gathers method conventional in the engineerings such as examination method, decay curve method or response-curve method, the temperature controlled proportional plus integral controller parameter of gas turbine inlet adjustable guide vane of adjusting.Proportional action constant is designated as K
p, integral action constant is designated as K
i.
Design integration segregation ratio integral controller, with the proportional action constant K of proportional plus integral controller
pas the proportional action constant of integration segregation ratio integral controller, the integral action coefficient in integration segregation ratio integral controller kth moment is designated as f
be separated[e (k)], obtains the integral action constant f in kth moment
be separated[e (k)] × K
i.When kth Time of day offsets is less, integral action is strengthened, and value is K
i; When kth Time of day offsets is larger, integral action weakens, and value is the K of 0.5 times
i, delivery temperature static deviation can be eliminated, it also avoid because large integral action makes gas turbine blower import adjustable guide vane temperature control system stability reduce.
Wherein, Δ T is that gas turbine enters the width using compressor inlet adjustable guide vane to control the delivery temperature span of combustion turbine exhaustion temperature stage.
Integration segregation ratio integral control algorithm can be expressed as:
Wherein, T is the sampling time.
Design shift integral proportional plus integral controller, with the proportional action constant K of proportional plus integral controller
pas the proportional action constant of shift integral proportional plus integral controller, the integral action coefficient in shift integral proportional plus integral controller kth moment is designated as f
speed change[e (k)], obtains the integral action constant f in kth moment
speed change[e (k)] × K
i.Can change the progressive rate of integration item, make it corresponding with deviation size, the larger integration of deviation is slower.The integral action coefficient value in kth moment between 0.5-1 in change, when e (k) is greater than between separation zone after Δ T, integration item
the cumulative of e (k) is weakened; When | e (k) | when being less than 60% Δ T, add currency e (k), integration item becomes
integral action is the strongest; As | e (k) | time between 60% Δ T-Δ T, cumulative evaluation is at 0.5|e (k) |-| e (k) | between with | e (k) | size variation, integration item u (k) exists
Between.
Wherein, Δ T is that gas turbine enters the width using compressor inlet adjustable guide vane to control the delivery temperature span of combustion turbine exhaustion temperature stage.
Shift integral proportional plus integral control algorithm can be expressed as
Wherein, T is the sampling time.
3). the stroke of gas turbine blower import adjustable guide vane has certain restriction, by the output of shift integral proportional plus integral controller or integration segregation ratio integral controller through compressor inlet adjustable guide vane mechanical trip amplitude limit, send into actuator and regulate the transducible leaf divergence of compressor inlet, finally realize temperature and control.
Embodiment:
With reference to certain Gas Turbine Simulation mathematical model
Compressor inlet adjustable guide vane actuator is an inertial element, and its transfer function is
s is complex variable.Controller exports an import adjustable guide vane angle signal, is input to actuator, completes the task of changing import adjustable guide vane angle.
Delivery temperature mathematical model
Wherein, w
ffor fuel flow signal, during use compressor inlet adjustable guide vane controls combustion turbine exhaustion temperature, be approximately 1; N is tach signal, during use compressor inlet adjustable guide vane controls combustion turbine exhaustion temperature, be approximately 1; T
iffor outlet air temperature set value, be set to 538 DEG C; T
afor ambient temperature; L
iGVrepresent the stroke of compressor inlet adjustable guide vane actuator.
Use MATLAB/SIMULINK to set up above-mentioned compressor inlet adjustable guide vane Temperature Control Model, simulate the temperature signal T that 18 thermocouples record
1, T
2..., T
18, remove maximum value wherein and minimum value gets its mean value, obtain T
flat, the deviation of delivery temperature mean value and setting value, sends into integration segregation ratio integral controller or sends into shift integral proportional plus integral controller, and controller exports sends into above-mentioned actuator model, finally sends into plant model.
Use the parameter tuning function of the proportional plus integral controller of MATLAB/SIMULINK, the controller parameter K of proportional plus integral controller of adjusting out
p=0.24, K
i=0.28.
Outlet air temperature set value does step response test from 538 DEG C to 548 DEG C, Δ T value 10.
Deviation according to kth moment delivery temperature mean value and setting value calculates the integral action coefficient of the shift integral proportional plus integral controller in kth moment and the integral action coefficient of integration segregation ratio integral controller, design shift integral proportional plus integral controller and integration segregation ratio integral controller.
The integration segregation ratio integral controller parameter in kth moment: proportional action constant 0.24, integral action constant f
be separated[e (k)] × 0.28.The shift integral proportional plus integral controller parameter in kth moment: proportional action constant 0.24, integral action constant f
speed change[e (k)] × 0.28.
The output of above-mentioned controller sends into actuator's object through the stroke amplitude limit of 28.5 °-89.5 °.
The step response curve obtained as shown in Figure 3, integration segregation ratio integral control and shift integral proportional plus integral control have less overshoot compared with controlling with conventional proportional integral, make the process of compressor inlet adjustable guide vane control combustion turbine exhaustion temperature more steady.Integration segregation ratio integral controller integral action coefficient curve adopts switch control rule, as shown in Figure 4.The linear change in step response of shift integral proportional plus integral controller integral action coefficient, as shown in Figure 5.
Claims (2)
1. use compressor inlet adjustable guide vane to control a method for combustion turbine exhaustion temperature, it is characterized in that the method bag
Draw together following steps:
A1). at the N number of delivery temperature thermocouple of combustion turbine exhaustion chamber indoor location, N is the number of delivery temperature thermocouple, calculates delivery temperature mean value T according to the measured value of this N number of delivery temperature thermocouple
flat, outlet air temperature set value is designated as T
if, the delivery temperature mean value T in kth moment
flatwith outlet air temperature set value T
ifdeviation be designated as e (k), as the input of controller;
B1). the temperature controlled proportional plus integral controller parameter of compressor inlet adjustable guide vane of adjusting, wherein proportional action constant is designated as K
p, integral action constant is designated as K
i; Then integration segregation ratio integral controller is designed, with the proportional action constant K of proportional plus integral controller
pas the proportional action constant of integration segregation ratio integral controller, the integration segregation ratio integral controller kth moment integral action coefficient be designated as f
be separated[e (k)], obtains the integral action constant f in kth moment
be separated[e (k)] × K
i; Or design shift integral proportional plus integral controller, with the proportional action constant K of proportional plus integral controller
pas the proportional action constant of shift integral proportional plus integral controller, the integral action coefficient in shift integral proportional plus integral controller kth moment is designated as f
speed change[e (k)]; Obtain the integral action constant f in kth moment
speed change[e (k)] × K
i;
C1). by delivery temperature mean value T
flatwith outlet air temperature set value T
ifdeviation, send into shift integral proportional plus integral controller, or send into integration segregation ratio integral controller; By the output of shift integral proportional plus integral controller or integration segregation ratio integral controller through compressor inlet adjustable guide vane mechanical trip amplitude limit, send into actuator and regulate the transducible leaf divergence of compressor inlet, finally realize temperature and control.
2. the as claimed in claim 1 method using compressor inlet adjustable guide vane to control combustion turbine exhaustion temperature, is characterized in that: for B1) the integral action coefficient f in integration segregation ratio integral controller kth moment
be separated[e (k)]:
Wherein, Δ T is that gas turbine enters the width using compressor inlet adjustable guide vane to control the delivery temperature span of combustion turbine exhaustion temperature stage;
The integral action coefficient f in shift integral proportional plus integral controller kth moment
speed change[e (k)]:
Wherein, Δ T is that gas turbine enters the width using compressor inlet adjustable guide vane to control the delivery temperature span of combustion turbine exhaustion temperature stage.
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| CN103543763B (en) * | 2013-10-28 | 2016-01-20 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Based on the heavy duty gas turbine temperature-controlled process of fuzzy immunization proportional plus integral control |
| WO2015078014A1 (en) * | 2013-11-29 | 2015-06-04 | 西门子公司 | Measurement method for rotation of guide vane in gas turbine |
| CN104696253A (en) * | 2015-02-16 | 2015-06-10 | 溧阳市超强链条制造有限公司 | Adjustment and control method of inlet guide blade of air compressor |
| CN104990326B (en) * | 2015-06-26 | 2018-02-02 | 青岛海尔股份有限公司 | Refrigerator and the thermometry based on infrared sensor |
| CN105115239B (en) * | 2015-06-26 | 2018-03-23 | 青岛海尔股份有限公司 | The method for sensing of refrigerator and refrigerator compartment internal temperature |
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| CN107304716A (en) * | 2016-04-22 | 2017-10-31 | 北京澳尔金石油技术开发有限公司 | A kind of turbine engine failure monitoring method and device |
| CN114576012B (en) * | 2022-03-29 | 2023-09-26 | 华北电力科学研究院有限责任公司 | Gas turbine inlet guide vane adjusting method and device |
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