CN104696078A - Method and device for controlling fuel quantity of gas turbine - Google Patents
Method and device for controlling fuel quantity of gas turbine Download PDFInfo
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- CN104696078A CN104696078A CN201510019469.4A CN201510019469A CN104696078A CN 104696078 A CN104696078 A CN 104696078A CN 201510019469 A CN201510019469 A CN 201510019469A CN 104696078 A CN104696078 A CN 104696078A
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Abstract
The invention discloses a method and a device for controlling the fuel quantity of a gas turbine. The accuracy of shifting time of a control logic in the prior art can be improved. The method comprises the following steps: determining a current control logic for performing fuel quantity control from a preset control logic; determining a fuel quantity signal according to the current control logic for performing the fuel quantity control, and filtering a fuel quantity signal; and transmitting the filtered fuel quantity signal to a preset fuel threshold control module. The device comprises a first determining unit, a second determining unit and a transmitting unit, wherein the first determining unit is used for determining the current control logic for performing the fuel quantity control from the preset control logic; the second determining unit is used for determining the fuel quantity signal according to the current control logic for performing the fuel quantity control and filtering the fuel quantity signal; and the transmitting unit is used for transmitting the filtered fuel quantity signal to the preset fuel threshold control module.
Description
Technical field
The present invention relates to automation field, be specifically related to a kind of controlling method and device of the fuel quantity for gas turbine.
Background technique
Heavy single shift gas turbine comprises the compositions such as gas compressor, firing chamber and combustion gas turbine, and the working procedure of gas turbine is, gas compressor sucks air continuously and compressed from air; Air after compression enters firing chamber, and the fuel mix after-combustion with spraying into, becomes high-temperature fuel gas, flows into expansion work in combustion gas turbine immediately, promotes turbo wheel and rotates together with compressor impeller.The control of heavy single shift gas turbine mainly comprises the control of fuel quantity and air mass flow, is wherein mainly the control of fuel quantity.Adopt the control logic of different control objectives to instruct the aperture of fuel valve in the different phase of gas turbine Start-up and operating performance; thus control the fuel quantity sending into gas turbine; such as; adopt in start-up course and start control logic; rotating speed control logic is adopted in on-load process; adopt in stopping process and shut down control logic, adopt temperature control logic when turbine exhaust temperature exceedes delivery temperature benchmark, adopt Acceleration Control logic when acceleration exceedes acceleration benchmark.The selection of the controller of modal heavy duty gas turbine selects door to realize by minimum value, under normal circumstances, minimum according to the fuel quantity that certain controller calculates, this control logic will be selected door to choose by minimum value, then fuel threshold control module will control the aperture of fuel valve according to this smallest amount of fuel, makes to enter the fuel quantity of firing chamber for this smallest amount of fuel.
And the fuel quantity that calculates of the prior art control logic different in the some and current control logic controlled minimum time just carry out the switching of control logic, and the product of deviation and proportional action coefficient and final fuel quantity feed back and the sum of products of first order inertial loop is the formula of control logic fuel quantity, this just makes prior art there will be currently should to select a certain control logic and be not minimum situation according to the fuel quantity that this control logic calculates, namely the switching time of existing control logic is inaccurate, thus can cause the instability of gas turbine.
Summary of the invention
Technical problem to be solved by this invention is the inaccurate problem of switching time of the control logic that prior art there will be.
For this purpose, the present invention proposes a kind of controlling method of the fuel quantity for gas turbine, comprising:
The current control logic will carrying out fuel regulation is determined from the control logic pre-set; Wherein, the control logic pre-set described in comprises: start control logic, rotating speed control logic, temperature control logic, Acceleration Control logic and shut down control logic;
Determine fuel quantity signal according to the described current control logic will carrying out fuel regulation, and filtering is carried out to described fuel quantity signal;
Described filtered fuel quantity signal is sent to the fuel threshold control module pre-set.
The embodiment of the present invention is used for the controlling method of the fuel quantity of gas turbine, first, the current control logic will carrying out fuel regulation is determined from the control logic pre-set, then, fuel quantity signal is determined according to the described current control logic will carrying out fuel regulation, and filtering is carried out to described fuel quantity signal, finally, described filtered fuel quantity signal is sent to the fuel threshold control module pre-set, this just makes the switching time of different control logic more accurate, simultaneously, the setting of filtering link, make the switching of different control logic more level and smooth, noise interference can be prevented.
On the other hand, the present invention proposes a kind of control gear of the fuel quantity for gas turbine, comprising:
First determining unit, for determining the current control logic will carrying out fuel regulation from the control logic pre-set; Wherein, the control logic pre-set described in comprises: start control logic, rotating speed control logic, temperature control logic, Acceleration Control logic and shut down control logic;
Second determining unit, for determining fuel quantity signal according to the described current control logic will carrying out fuel regulation, and carries out filtering to described fuel quantity signal;
Transmitting element, for sending to the fuel threshold control module pre-set by described filtered fuel quantity signal.
The embodiment of the present invention is used for the control gear of the fuel quantity of gas turbine, first, the current control logic will carrying out fuel regulation is determined from the control logic pre-set, then, fuel quantity signal is determined according to the described current control logic will carrying out fuel regulation, and filtering is carried out to described fuel quantity signal, finally, described filtered fuel quantity signal is sent to the fuel threshold control module pre-set, this just makes the switching time of different control logic more accurate, simultaneously, the setting of filtering link, make the switching of different control logic more level and smooth, noise interference can be prevented.
Accompanying drawing explanation
Figure 1 shows that the schematic flow sheet of controlling method one embodiment of a kind of fuel quantity for gas turbine of the present invention;
Fig. 2 is the schematic flow sheet of another embodiment of controlling method of a kind of fuel quantity for gas turbine of the present invention;
Fig. 3 is the part run schematic diagram of the another embodiment of controlling method of a kind of fuel quantity for gas turbine of the present invention;
Fig. 4 is the part run schematic diagram of the another embodiment of controlling method of a kind of fuel quantity for gas turbine of the present invention;
Fig. 5 is the part run schematic diagram of the another embodiment of controlling method of a kind of fuel quantity for gas turbine of the present invention;
Fig. 6 is the part run schematic diagram of the another embodiment of controlling method of a kind of fuel quantity for gas turbine of the present invention;
Fig. 7 is the schematic flow sheet of the another embodiment of controlling method of a kind of fuel quantity for gas turbine of the present invention;
Fig. 8 is the frame structure schematic diagram of a kind of control gear one embodiment of the fuel quantity for gas turbine.
Embodiment
For making the object of the embodiment of the present invention, technological scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technological scheme in the embodiment of the present invention is clearly described, obviously, described embodiment is the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
As shown in Figure 1, the present embodiment discloses a kind of controlling method of the fuel quantity for gas turbine, comprising:
S1, from the control logic pre-set, determine the current control logic will carrying out fuel regulation; Wherein, the control logic pre-set described in comprises: start control logic, rotating speed control logic, temperature control logic, Acceleration Control logic and shut down control logic;
S2, determine fuel quantity signal according to the described current control logic will carrying out fuel regulation, and filtering is carried out to described fuel quantity signal;
S3, described filtered fuel quantity signal is sent to the fuel threshold control module pre-set.
The embodiment of the present invention is used for the controlling method of the fuel quantity of gas turbine, first, the current control logic will carrying out fuel regulation is determined from the control logic pre-set, then, fuel quantity signal is determined according to the described current control logic will carrying out fuel regulation, and filtering is carried out to described fuel quantity signal, finally, described filtered fuel quantity signal is sent to the fuel threshold control module pre-set, this just makes the switching time of different control logic more accurate, simultaneously, the setting of filtering link, make the switching of different control logic more level and smooth, noise interference can be prevented.
Alternatively, referring to Fig. 2, be used in the present invention, in another embodiment of the controlling method of the fuel quantity of gas turbine, determining the current control logic will carrying out fuel regulation the described control logic from pre-setting, comprising:
Judge described temperature control logic and described Acceleration Control logic whether effective;
If described temperature control logic and described Acceleration Control logical validity, then judge that the priority of described temperature control logic is whether higher than the priority of described Acceleration Control logic, if the priority of described temperature control logic is higher than the priority of described Acceleration Control logic, then determine that described temperature control logic is the current control logic will carrying out fuel regulation, otherwise, then determine that described Acceleration Control logic is the current control logic will carrying out fuel regulation; Or
If described temperature control logic is effective, described Acceleration Control logic is invalid, then determine that described temperature control logic is the current control logic will carrying out fuel regulation; Or
If described Acceleration Control logical validity, described temperature control logic is invalid, then determine that described Acceleration Control logic is the current control logic will carrying out fuel regulation; Or
If described temperature control logic and described Acceleration Control logic invalid, then judge that whether described shutdown control logic is effective, if described shutdown control logic is effective, then determine that described shutdown control logic is the current control logic will carrying out fuel regulation, or, if described shutdown control logic is invalid, then judge that whether described startup control logic is effective, if described startup control logic is effective, then determine that described startup control logic is the current control logic will carrying out fuel regulation, or, if described startup control logic is invalid, then determine that described rotating speed control logic is the current control logic will carrying out fuel regulation.
In the embodiment of the present invention, temperature control logic and Acceleration Control logic all effectively time consider the priority of control logic, make control logic that the two medium priority is higher grasp the control of fuel quantity, control procedure can be made more safe.
Alternatively, referring to Fig. 3, be used in another embodiment of the controlling method of the fuel quantity of gas turbine in the present invention, whether the described priority judging described temperature control logic higher than the priority of described Acceleration Control logic, comprising:
S10, the delivery temperature judging the combustion gas turbine of gas turbine and the deviation of the first delivery temperature preset, the deviation of the acceleration that the axle whether being greater than combustion gas turbine and the gas compressor being connected described gas turbine with the product of the first quantizing factor preset rotates and the first default acceleration, with the product of the second quantizing factor preset;
If the deviation of the delivery temperature of the described combustion gas turbine of S11 and described first delivery temperature, the deviation of the acceleration that the axle being greater than the described combustion gas turbine and gas compressor that are connected described gas turbine with the product of described first quantizing factor rotates and described first acceleration, with the product of described second quantizing factor, then determine the priority of the priority of described temperature control logic higher than described Acceleration Control logic, otherwise, then the priority of priority higher than described temperature control logic of described Acceleration Control logic is determined.
Alternatively, referring to Fig. 4 to Fig. 6, be used in the present invention in another embodiment of the controlling method of the fuel quantity of gas turbine, describedly judge that whether described temperature control logic and described Acceleration Control logic be effective, comprising:
S12, judge whether the delivery temperature of the combustion gas turbine of described gas turbine is greater than the second default delivery temperature, whether the acceleration that the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor rotate is greater than the second default acceleration;
If the delivery temperature of the combustion gas turbine of the described gas turbine of S13 is greater than described second delivery temperature, then determine that described temperature control logic is effective, otherwise, then determine that described temperature control logic is invalid, if the acceleration that the axle of the combustion gas turbine of the described gas turbine of described connection and gas compressor rotates is greater than described second acceleration, then determine described Acceleration Control logical validity, otherwise, then determine that described Acceleration Control logic is invalid;
Wherein, describedly judge that described shutdown control logic is whether effective, comprising:
S14, judge whether the stop botton of described gas turbine is pressed;
If the stop botton of the described gas turbine of S15 is pressed, then determine that described shutdown control logic is effective, otherwise, then determine that described shutdown control logic is invalid;
Whether the startup control logic that described judgement pre-sets is effective, comprising:
S16, judge whether the start button of described gas turbine is pressed;
If the start button of the described gas turbine of S17 is pressed, then judge whether the rotating speed of the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor is less than the first default rotating speed;
If the rotating speed of the combustion gas turbine of the described gas turbine of the described connection of S18 and the axle of gas compressor is less than described first rotating speed, then determine that described startup control logic is effective, otherwise, then determine that described startup control logic is invalid.
In the embodiment of the present invention, the first rotating speed preset can be 90% rated speed.
Alternatively, referring to Fig. 7, be used in the present invention, in another embodiment of the controlling method of the fuel quantity of gas turbine, describedly determining fuel quantity signal according to the described current control logic will carrying out fuel regulation, comprising:
If the current control logic will carrying out fuel regulation is described temperature control logic, described closed loop proportional-integral-derivative controller is then used to control fuel quantity according to the delivery temperature of the combustion gas turbine of described gas turbine and the deviation accounting temperature of the second delivery temperature preset, or, use described closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products accounting temperature of default first order inertial loop controls fuel quantity; Or
If the current control logic will carrying out fuel regulation is described Acceleration Control logic, the acceleration then using described closed loop proportional-integral-derivative controller to rotate according to the axle of the combustion gas turbine of the described gas turbine of described connection and gas compressor calculates Acceleration Control fuel quantity with the deviation of the second acceleration preset, or, use described closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products of default first order inertial loop calculates Acceleration Control fuel quantity; Or
If the current control logic will carrying out fuel regulation is described shutdown control logic, then shuts down according to current fuel quantity and default minimizing rate calculations and control fuel quantity; Or
If the current control logic will carrying out fuel regulation is described startup control logic, then starts according to the fuel quantity warming-up value preset and default calculating of advancing the speed and control fuel quantity; Or
If the current control logic will carrying out fuel regulation is described rotating speed control logic, then use closed loop proportional-integral-derivative controller to calculate rotating speed according to the rotating speed connecting the combustion gas turbine of gas turbine and the axle of gas compressor with the deviation of the second rotating speed preset and control fuel quantity, or, use closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products of default first order inertial loop calculates rotating speed and controls fuel quantity.
In the embodiment of the present invention, according to the gas turbine different control stage need different control logics is set, and the priority of different control logic is set, use multiple diverter switch to realize the selection of the control logic with different priorities, by output filtering link or arrange the no-harass switch that feedback filtering link realizes different control logic in control logic.
As shown in Figure 8, the present embodiment discloses a kind of control gear of the fuel quantity for gas turbine, comprising:
First determining unit 1, for determining the current control logic will carrying out fuel regulation from the control logic pre-set; Wherein, the control logic pre-set described in comprises: start control logic, rotating speed control logic, temperature control logic, Acceleration Control logic and shut down control logic;
Second determining unit 2, for determining fuel quantity signal according to the described current control logic will carrying out fuel regulation, and carries out filtering to described fuel quantity signal;
Transmitting element 3, for sending to the fuel threshold control module pre-set by described filtered fuel quantity signal.
The embodiment of the present invention is used for the control gear of the fuel quantity of gas turbine, first, the current control logic will carrying out fuel regulation is determined from the control logic pre-set, then, fuel quantity signal is determined according to the described current control logic will carrying out fuel regulation, and filtering is carried out to described fuel quantity signal, finally, described filtered fuel quantity signal is sent to the fuel threshold control module pre-set, this just makes the switching time of different control logic more accurate, simultaneously, the setting of filtering link, make the switching of different control logic more level and smooth, noise interference can be prevented.
Alternatively, be used in the present invention in another embodiment of the control gear of the fuel quantity of gas turbine, described first determining unit, comprising:
First judgment sub-unit, for judge described temperature control logic and described Acceleration Control logic whether effective;
First determines subelement, if for described temperature control logic and described Acceleration Control logical validity, then judge that the priority of described temperature control logic is whether higher than the priority of described Acceleration Control logic, if the priority of described temperature control logic is higher than the priority of described Acceleration Control logic, then determine that described temperature control logic is the current control logic will carrying out fuel regulation, otherwise, then determine that described Acceleration Control logic is the current control logic will carrying out fuel regulation; Or
Second determines subelement, if effective for described temperature control logic, described Acceleration Control logic is invalid, then determine that described temperature control logic is the current control logic will carrying out fuel regulation; Or
3rd determines subelement, if for described Acceleration Control logical validity, described temperature control logic is invalid, then determine that described Acceleration Control logic is the current control logic will carrying out fuel regulation; Or
4th determines subelement, if for described temperature control logic and described Acceleration Control logic invalid, then judge that whether described shutdown control logic is effective, if described shutdown control logic is effective, then determine that described shutdown control logic is the current control logic will carrying out fuel regulation, or, if described shutdown control logic is invalid, then judge that whether described startup control logic is effective, if described startup control logic is effective, then determine that described startup control logic is the current control logic will carrying out fuel regulation, or, if described startup control logic is invalid, then determine that described rotating speed control logic is the current control logic will carrying out fuel regulation.
In the embodiment of the present invention, temperature control logic and Acceleration Control logic all effectively time consider the priority of control logic, make control logic that the two medium priority is higher grasp the control of fuel quantity, control procedure can be made more safe.
Alternatively, be used in the present invention in another embodiment of the control gear of the fuel quantity of gas turbine, described first determines subelement, comprising:
First judge module, for the deviation of the delivery temperature judging the combustion gas turbine of gas turbine and the first delivery temperature preset, the deviation of the acceleration that the axle whether being greater than combustion gas turbine and the gas compressor being connected described gas turbine with the product of the first quantizing factor preset rotates and the first default acceleration, with the product of the second quantizing factor preset;
First determination module, if for the delivery temperature of described combustion gas turbine and the deviation of described first delivery temperature, the deviation of the acceleration that the axle being greater than the described combustion gas turbine and gas compressor that are connected described gas turbine with the product of described first quantizing factor rotates and described first acceleration, with the product of described second quantizing factor, then determine the priority of the priority of described temperature control logic higher than described Acceleration Control logic, otherwise, then the priority of priority higher than described temperature control logic of described Acceleration Control logic is determined.
Alternatively, be used in the present invention in another embodiment of the control gear of the fuel quantity of gas turbine, described first judgment sub-unit, comprising:
Second judge module, for judging whether the delivery temperature of the combustion gas turbine of described gas turbine is greater than the second default delivery temperature, whether the acceleration that the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor rotate is greater than the second default acceleration;
Second determination module, if the delivery temperature for the combustion gas turbine of described gas turbine is greater than described second delivery temperature, then determine that described temperature control logic is effective, otherwise, then determine that described temperature control logic is invalid, if the acceleration that the axle of the combustion gas turbine of the described gas turbine of described connection and gas compressor rotates is greater than described second acceleration, then determine described Acceleration Control logical validity, otherwise, then determine that described Acceleration Control logic is invalid;
Wherein, the described 4th determines subelement, comprising:
3rd judge module, for judging whether the stop botton of described gas turbine is pressed;
3rd determination module, if press for the stop botton of described gas turbine, then determines that described shutdown control logic is effective, otherwise, then determine that described shutdown control logic is invalid;
4th judge module, for judging whether the start button of described gas turbine is pressed;
5th judge module, if press for the start button of described gas turbine, then judges whether the rotating speed of the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor is less than the first default rotating speed;
4th determination module, if be less than described first rotating speed for the rotating speed of the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor, then determines that described startup control logic is effective, otherwise, then determine that described startup control logic is invalid.
In the embodiment of the present invention, the first rotating speed preset can be 90% rated speed.
Alternatively, be used in the present invention in another embodiment of the control gear of the fuel quantity of gas turbine, described second determining unit, comprising:
First computation subunit, if be described temperature control logic for the current control logic will carrying out fuel regulation, described closed loop proportional-integral-derivative controller is then used to control fuel quantity according to the delivery temperature of the combustion gas turbine of described gas turbine and the deviation accounting temperature of the second delivery temperature preset, or, use described closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products accounting temperature of default first order inertial loop controls fuel quantity; Or
Second computation subunit, if be described Acceleration Control logic for the current control logic will carrying out fuel regulation, the acceleration then using described closed loop proportional-integral-derivative controller to rotate according to the axle of the combustion gas turbine of the described gas turbine of described connection and gas compressor calculates Acceleration Control fuel quantity with the deviation of the second acceleration preset, or, use described closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products of default first order inertial loop calculates Acceleration Control fuel quantity, or
3rd computation subunit, if be described shutdown control logic for the current control logic will carrying out fuel regulation, then shut down according to current fuel quantity and default minimizing rate calculations and controls fuel quantity; Or
4th computation subunit, if be described startup control logic for the current control logic will carrying out fuel regulation, then start according to the fuel quantity warming-up value preset and default calculating of advancing the speed and controls fuel quantity; Or
5th computation subunit, if be described rotating speed control logic for the current control logic will carrying out fuel regulation, then use closed loop proportional-integral-derivative controller to calculate rotating speed according to the rotating speed connecting the combustion gas turbine of gas turbine and the axle of gas compressor with the deviation of the second rotating speed preset and control fuel quantity, or, use closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products of default first order inertial loop calculates rotating speed and controls fuel quantity.
In the embodiment of the present invention, according to the gas turbine different control stage need different control logics is set, and the priority of different control logic is set, use multiple diverter switch to realize the selection of the control logic with different priorities, by output filtering link or arrange the no-harass switch that feedback filtering link realizes different control logic in control logic.
Although describe embodiments of the present invention by reference to the accompanying drawings, but those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, such amendment and modification all fall into by within claims limited range.
Claims (10)
1. for a controlling method for the fuel quantity of gas turbine, it is characterized in that, comprising:
The current control logic will carrying out fuel regulation is determined from the control logic pre-set; Wherein, the control logic pre-set described in comprises: start control logic, rotating speed control logic, temperature control logic, Acceleration Control logic and shut down control logic;
Determine fuel quantity signal according to the described current control logic will carrying out fuel regulation, and filtering is carried out to described fuel quantity signal;
Described filtered fuel quantity signal is sent to the fuel threshold control module pre-set.
2. the controlling method of the fuel quantity for gas turbine according to claim 1, is characterized in that, determining the current control logic will carrying out fuel regulation, comprising the described control logic from pre-setting:
Judge described temperature control logic and described Acceleration Control logic whether effective;
If described temperature control logic and described Acceleration Control logical validity, then judge that the priority of described temperature control logic is whether higher than the priority of described Acceleration Control logic, if the priority of described temperature control logic is higher than the priority of described Acceleration Control logic, then determine that described temperature control logic is the current control logic will carrying out fuel regulation, otherwise, then determine that described Acceleration Control logic is the current control logic will carrying out fuel regulation; Or
If described temperature control logic is effective, described Acceleration Control logic is invalid, then determine that described temperature control logic is the current control logic will carrying out fuel regulation; Or
If described Acceleration Control logical validity, described temperature control logic is invalid, then determine that described Acceleration Control logic is the current control logic will carrying out fuel regulation; Or
If described temperature control logic and described Acceleration Control logic invalid, then judge that whether described shutdown control logic is effective, if described shutdown control logic is effective, then determine that described shutdown control logic is the current control logic will carrying out fuel regulation, or, if described shutdown control logic is invalid, then judge that whether described startup control logic is effective, if described startup control logic is effective, then determine that described startup control logic is the current control logic will carrying out fuel regulation, or, if described startup control logic is invalid, then determine that described rotating speed control logic is the current control logic will carrying out fuel regulation.
3. the controlling method of the fuel quantity for gas turbine according to claim 2, is characterized in that, whether the described priority judging described temperature control logic higher than the priority of described Acceleration Control logic, comprising:
Judge the delivery temperature of the combustion gas turbine of gas turbine and the deviation of the first default delivery temperature, the deviation of the acceleration that the axle whether being greater than combustion gas turbine and the gas compressor being connected described gas turbine with the product of the first quantizing factor preset rotates and the first default acceleration, with the product of the second quantizing factor preset;
If the deviation of the delivery temperature of described combustion gas turbine and described first delivery temperature, the deviation of the acceleration that the axle being greater than the described combustion gas turbine and gas compressor that are connected described gas turbine with the product of described first quantizing factor rotates and described first acceleration, with the product of described second quantizing factor, then determine the priority of the priority of described temperature control logic higher than described Acceleration Control logic, otherwise, then the priority of priority higher than described temperature control logic of described Acceleration Control logic is determined.
4. the controlling method of the fuel quantity for gas turbine according to Claims 2 or 3, is characterized in that, describedly judges that whether described temperature control logic and described Acceleration Control logic be effective, comprising:
Judge whether the delivery temperature of the combustion gas turbine of described gas turbine is greater than the second default delivery temperature, whether the acceleration that the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor rotate is greater than the second default acceleration;
If the delivery temperature of the combustion gas turbine of described gas turbine is greater than described second delivery temperature, then determine that described temperature control logic is effective, otherwise, then determine that described temperature control logic is invalid, if the acceleration that the axle of the combustion gas turbine of the described gas turbine of described connection and gas compressor rotates is greater than described second acceleration, then determine described Acceleration Control logical validity, otherwise, then determine that described Acceleration Control logic is invalid;
Wherein, describedly judge that described shutdown control logic is whether effective, comprising:
Judge whether the stop botton of described gas turbine is pressed;
If the stop botton of described gas turbine is pressed, then determine that described shutdown control logic is effective, otherwise, then determine that described shutdown control logic is invalid;
Whether the startup control logic that described judgement pre-sets is effective, comprising:
Judge whether the start button of described gas turbine is pressed;
If the start button of described gas turbine is pressed, then judge whether the rotating speed of the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor is less than the first default rotating speed;
If the rotating speed of the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor is less than described first rotating speed, then determine that described startup control logic is effective, otherwise, then determine that described startup control logic is invalid.
5. the controlling method of the fuel quantity for gas turbine according to claim 1, is characterized in that, describedly determines fuel quantity signal according to the described current control logic will carrying out fuel regulation, comprising:
If the current control logic will carrying out fuel regulation is described temperature control logic, described closed loop proportional-integral-derivative controller is then used to control fuel quantity according to the delivery temperature of the combustion gas turbine of described gas turbine and the deviation accounting temperature of the second delivery temperature preset, or, use described closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products accounting temperature of default first order inertial loop controls fuel quantity; Or
If the current control logic will carrying out fuel regulation is described Acceleration Control logic, the acceleration then using described closed loop proportional-integral-derivative controller to rotate according to the axle of the combustion gas turbine of the described gas turbine of described connection and gas compressor calculates Acceleration Control fuel quantity with the deviation of the second acceleration preset, or, use described closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products of default first order inertial loop calculates Acceleration Control fuel quantity; Or
If the current control logic will carrying out fuel regulation is described shutdown control logic, then shuts down according to current fuel quantity and default minimizing rate calculations and control fuel quantity; Or
If the current control logic will carrying out fuel regulation is described startup control logic, then starts according to the fuel quantity warming-up value preset and default calculating of advancing the speed and control fuel quantity; Or
If the current control logic will carrying out fuel regulation is described rotating speed control logic, then use closed loop proportional-integral-derivative controller to calculate rotating speed according to the rotating speed connecting the combustion gas turbine of gas turbine and the axle of gas compressor with the deviation of the second rotating speed preset and control fuel quantity, or, use closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products of default first order inertial loop calculates rotating speed and controls fuel quantity.
6. for a control gear for the fuel quantity of gas turbine, it is characterized in that, comprising:
First determining unit, for determining the current control logic will carrying out fuel regulation from the control logic pre-set; Wherein, the control logic pre-set described in comprises: start control logic, rotating speed control logic, temperature control logic, Acceleration Control logic and shut down control logic;
Second determining unit, for determining fuel quantity signal according to the described current control logic will carrying out fuel regulation, and carries out filtering to described fuel quantity signal;
Transmitting element, for sending to the fuel threshold control module pre-set by described filtered fuel quantity signal.
7. the control gear of the fuel quantity for gas turbine according to claim 6, is characterized in that, described first determining unit, comprising:
First judgment sub-unit, for judge described temperature control logic and described Acceleration Control logic whether effective;
First determines subelement, if for described temperature control logic and described Acceleration Control logical validity, then judge that the priority of described temperature control logic is whether higher than the priority of described Acceleration Control logic, if the priority of described temperature control logic is higher than the priority of described Acceleration Control logic, then determine that described temperature control logic is the current control logic will carrying out fuel regulation, otherwise, then determine that described Acceleration Control logic is the current control logic will carrying out fuel regulation; Or
Second determines subelement, if effective for described temperature control logic, described Acceleration Control logic is invalid, then determine that described temperature control logic is the current control logic will carrying out fuel regulation; Or
3rd determines subelement, if for described Acceleration Control logical validity, described temperature control logic is invalid, then determine that described Acceleration Control logic is the current control logic will carrying out fuel regulation; Or
4th determines subelement, if for described temperature control logic and described Acceleration Control logic invalid, then judge that whether described shutdown control logic is effective, if described shutdown control logic is effective, then determine that described shutdown control logic is the current control logic will carrying out fuel regulation, or, if described shutdown control logic is invalid, then judge that whether described startup control logic is effective, if described startup control logic is effective, then determine that described startup control logic is the current control logic will carrying out fuel regulation, or, if described startup control logic is invalid, then determine that described rotating speed control logic is the current control logic will carrying out fuel regulation.
8. the control gear of the fuel quantity for gas turbine according to claim 7, is characterized in that, described first determines subelement, comprising:
First judge module, for the deviation of the delivery temperature judging the combustion gas turbine of gas turbine and the first delivery temperature preset, the deviation of the acceleration that the axle whether being greater than combustion gas turbine and the gas compressor being connected described gas turbine with the product of the first quantizing factor preset rotates and the first default acceleration, with the product of the second quantizing factor preset;
First determination module, if for the delivery temperature of described combustion gas turbine and the deviation of described first delivery temperature, the deviation of the acceleration that the axle being greater than the described combustion gas turbine and gas compressor that are connected described gas turbine with the product of described first quantizing factor rotates and described first acceleration, with the product of described second quantizing factor, then determine the priority of the priority of described temperature control logic higher than described Acceleration Control logic, otherwise, then the priority of priority higher than described temperature control logic of described Acceleration Control logic is determined.
9. the control gear of the fuel quantity for gas turbine according to claim 7 or 8, is characterized in that, described first judgment sub-unit, comprising:
Second judge module, for judging whether the delivery temperature of the combustion gas turbine of described gas turbine is greater than the second default delivery temperature, whether the acceleration that the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor rotate is greater than the second default acceleration;
Second determination module, if the delivery temperature for the combustion gas turbine of described gas turbine is greater than described second delivery temperature, then determine that described temperature control logic is effective, otherwise, then determine that described temperature control logic is invalid, if the acceleration that the axle of the combustion gas turbine of the described gas turbine of described connection and gas compressor rotates is greater than described second acceleration, then determine described Acceleration Control logical validity, otherwise, then determine that described Acceleration Control logic is invalid;
Wherein, the described 4th determines subelement, comprising:
3rd judge module, for judging whether the stop botton of described gas turbine is pressed;
3rd determination module, if press for the stop botton of described gas turbine, then determines that described shutdown control logic is effective, otherwise, then determine that described shutdown control logic is invalid;
4th judge module, for judging whether the start button of described gas turbine is pressed;
5th judge module, if press for the start button of described gas turbine, then judges whether the rotating speed of the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor is less than the first default rotating speed;
4th determination module, if be less than described first rotating speed for the rotating speed of the combustion gas turbine of the described gas turbine of described connection and the axle of gas compressor, then determines that described startup control logic is effective, otherwise, then determine that described startup control logic is invalid.
10. the control gear of the fuel quantity for gas turbine according to claim 6, is characterized in that, described second determining unit, comprising:
First computation subunit, if be described temperature control logic for the current control logic will carrying out fuel regulation, described closed loop proportional-integral-derivative controller is then used to control fuel quantity according to the delivery temperature of the combustion gas turbine of described gas turbine and the deviation accounting temperature of the second delivery temperature preset, or, use described closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products accounting temperature of default first order inertial loop controls fuel quantity; Or
Second computation subunit, if be described Acceleration Control logic for the current control logic will carrying out fuel regulation, the acceleration then using described closed loop proportional-integral-derivative controller to rotate according to the axle of the combustion gas turbine of the described gas turbine of described connection and gas compressor calculates Acceleration Control fuel quantity with the deviation of the second acceleration preset, or, use described closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products of default first order inertial loop calculates Acceleration Control fuel quantity, or
3rd computation subunit, if be described shutdown control logic for the current control logic will carrying out fuel regulation, then shut down according to current fuel quantity and default minimizing rate calculations and controls fuel quantity; Or
4th computation subunit, if be described startup control logic for the current control logic will carrying out fuel regulation, then start according to the fuel quantity warming-up value preset and default calculating of advancing the speed and controls fuel quantity; Or
5th computation subunit, if be described rotating speed control logic for the current control logic will carrying out fuel regulation, then use closed loop proportional-integral-derivative controller to calculate rotating speed according to the rotating speed connecting the combustion gas turbine of gas turbine and the axle of gas compressor with the deviation of the second rotating speed preset and control fuel quantity, or, use closed loop proportional-integral-derivative controller according to described deviation and the product of proportional action coefficient preset with final fuel quantity feeds back and the sum of products of default first order inertial loop calculates rotating speed and controls fuel quantity.
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