CN116696560A - Performance optimization method, system, device and medium for improving gas unit - Google Patents
Performance optimization method, system, device and medium for improving gas unit Download PDFInfo
- Publication number
- CN116696560A CN116696560A CN202310953692.0A CN202310953692A CN116696560A CN 116696560 A CN116696560 A CN 116696560A CN 202310953692 A CN202310953692 A CN 202310953692A CN 116696560 A CN116696560 A CN 116696560A
- Authority
- CN
- China
- Prior art keywords
- pressure ratio
- ratio limit
- limit value
- igv opening
- determining
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 52
- 238000005457 optimization Methods 0.000 title claims abstract description 26
- 239000000779 smoke Substances 0.000 claims description 20
- 230000008569 process Effects 0.000 claims description 12
- 238000003860 storage Methods 0.000 claims description 9
- 230000004044 response Effects 0.000 claims description 8
- 238000010248 power generation Methods 0.000 abstract description 9
- 230000009467 reduction Effects 0.000 abstract description 4
- 230000002829 reductive effect Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 121
- 238000004590 computer program Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
- 230000007423 decrease Effects 0.000 description 7
- 238000012937 correction Methods 0.000 description 5
- 230000036961 partial effect Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000001687 destabilization Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000000670 limiting effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 230000002441 reversible effect Effects 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000001960 triggered effect Effects 0.000 description 2
- 108010001267 Protein Subunits Proteins 0.000 description 1
- 239000003034 coal gas Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 239000004973 liquid crystal related substance Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
Abstract
The application discloses a performance optimization method, a system, a device and a medium for improving a gas unit, which comprise the steps of determining a surge pressure ratio limit value; adjusting an IGV opening based on the surge pressure ratio limit, and determining a target IGV opening based on the unit load; determining a first pressure ratio limit; acquiring a first fitting curve and a second fitting curve of the pressure ratio limit value relative to the exhaust gas temperature, and determining a second pressure ratio limit value based on the intersection point of the first fitting curve and the second fitting curve; and determining a target pressure ratio limit value according to the comparison of the first pressure ratio limit value and the second pressure ratio limit value. According to the application, through adjusting the IGV opening and the exhaust gas temperature of the gas compressor, the operation performance of the gas compressor in a high-temperature environment in summer is optimized, so that the condition of full-load output reduction is reduced, the problem of rapid output reduction of the gas turbine unit in full-load power generation in summer is solved, the power generation efficiency and the equipment reliability are improved, and the normal operation of the unit in the high-temperature environment in summer is ensured.
Description
Technical Field
The application relates to the technical field of power systems, in particular to a performance optimization method, system, device and medium for improving a gas turbine unit.
Background
The Gas Turbine (Gas Turbine) mainly comprises a Compressor, a combustion chamber and a Gas Turbine (Turbine), wherein the Compressor sucks air from the outside, pressurizes and heats the air, high-pressure air and fuel (natural Gas, coal Gas and the like) are mixed and combusted in the combustion chamber to form high-pressure high-temperature Gas, the Gas expands and works in the Gas Turbine, and heat energy of the Gas is converted into mechanical energy of the Turbine rotor, so that the external load rotor is driven to rotate at a high speed.
Gas turbines are very sensitive power plants to the atmospheric environment, and changes in environmental parameters can have a significant impact on the performance of the gas turbine and the combined cycle unit. In a Guangdong fuel cell power plant, two 9FB units have the phenomenon of fast output drop in the process of generating power in summer. For the early version of the 9FB unit, the rapid decrease in summer full load output is mainly affected by the compressor characteristics. The characteristics of the compressor refer to the variation of the performance parameters of the compressor with the variation of the operating conditions of the compressor under different operating conditions.
How to perform proper parameter adjustment according to the characteristics of the air compressor, and optimizing the operation performance of the air compressor in a high-temperature environment in summer by adjusting the related parameters of the air compressor, so as to ensure the normal operation of the unit in the high-temperature environment in summer is a problem to be solved at present.
Disclosure of Invention
The application aims to provide a performance optimization method, system, device and medium for improving a gas unit, which at least solve the problems of properly adjusting parameters according to the characteristics of a gas compressor, optimizing the operation performance of the gas compressor in a high-temperature environment in summer by adjusting related parameters of the gas compressor, improving the power generation load of the gas unit and ensuring the normal operation of the gas turbine in the high-temperature environment in summer.
The first aspect of the application provides a performance optimization method for improving a gas turbine unit, which comprises the following steps:
acquiring current working condition data of a gas unit to determine a surge pressure ratio limit value;
adjusting the IGV opening based on the surge pressure ratio limit value until a first preset condition is met, recording the IGV opening and corresponding unit load in the adjustment process, and determining a target IGV opening based on the unit load;
determining a first pressure ratio limit value according to the target IGV opening by utilizing a preset IGV opening-pressure ratio limit value curve;
acquiring a first fitting curve and a second fitting curve of the pressure ratio limit value relative to the exhaust gas temperature, and determining a second pressure ratio limit value based on the first fitting curve and the second fitting curve;
and determining a target pressure ratio limit value according to the comparison of the first pressure ratio limit value and the second pressure ratio limit value.
In one embodiment, adjusting the IGV opening based on the surge-to-pressure ratio limit includes:
determining a corresponding IGV opening reference value according to the surge pressure ratio limit value;
and gradually reducing the IGV opening by adopting a preset step length by taking the IGV opening reference value as a reference.
In one embodiment, the first preset condition is that the emission concentration of NOx and CO exceeds a preset concentration value, and the adjustment of the IGV opening is stopped.
In one embodiment, obtaining a first fitted curve of the pressure ratio limit with respect to the exhaust gas temperature comprises:
and according to the non-triggering state of the peak load mode of the gas unit, calculating a smoke discharge temperature control reference value through a pressure ratio limit value, and determining a first fitting curve.
In one embodiment, obtaining a second fitted curve of the pressure ratio limit with respect to the exhaust gas temperature comprises:
and calculating a smoke discharge temperature control reference value through a pressure ratio limit value according to the peak load mode triggering state of the gas turbine unit, and determining a second fitting curve.
In one embodiment, determining the target pressure ratio limit based on a comparison of the first pressure ratio limit and the second pressure ratio limit includes:
and in response to the first pressure ratio limit being less than or equal to the second pressure ratio limit, taking the second pressure ratio limit as the target pressure ratio limit.
In one embodiment, determining the target pressure ratio limit based on a comparison of the first pressure ratio limit and the second pressure ratio limit includes:
and in response to the first pressure ratio limit being greater than the second pressure ratio limit, adjusting the second pressure ratio limit with a preset step length by taking the second pressure ratio limit as a starting point, and determining the target pressure ratio limit when the pressure ratio limit meets a second preset condition.
A second aspect of the present application provides a performance optimization system for a gas turbine, the system comprising:
the surge pressure ratio limit value acquisition module is used for acquiring current working condition data of the gas turbine unit and determining a surge pressure ratio limit value;
the target IGV opening acquisition module is used for adjusting the IGV opening based on the surge voltage ratio limit value until a first preset condition is met, recording the IGV opening and corresponding unit load in the adjustment process, and determining the target IGV opening based on the unit load;
the first pressure ratio limit value acquisition module is used for determining a first pressure ratio limit value according to the target IGV opening by utilizing a preset IGV opening-pressure ratio limit value curve;
the second pressure ratio limit value acquisition module is used for acquiring a first fitting curve and a second fitting curve of the pressure ratio limit value relative to the exhaust gas temperature, and determining the second pressure ratio limit value based on the first fitting curve and the second fitting curve;
and the target pressure ratio limit value acquisition module is used for determining the target pressure ratio limit value according to the comparison of the first pressure ratio limit value and the second pressure ratio limit value.
The third aspect of the present application provides a performance optimization apparatus for a gas turbine, including a memory and one or more processors, where the memory stores executable codes, and the one or more processors are configured to implement the performance optimization method for a gas turbine of any one of the above-mentioned aspects when executing the executable codes.
A fourth aspect of the present application provides a computer readable storage medium having stored thereon a program which, when executed by a processor, implements the method of optimizing performance of a gas turbine unit of any one of the above.
The performance optimization method, system, device and medium for improving the gas unit provided by the embodiment of the application have at least the following technical effects.
By adjusting the IGV opening and the exhaust gas temperature of the gas compressor, the operation performance of the gas compressor in a high-temperature environment in summer is optimized, so that the condition of full-load output reduction is reduced, the problem of rapid output reduction of a gas turbine unit in full-load power generation in summer is solved, the power generation efficiency and the equipment reliability are improved, and the normal operation of the unit in the high-temperature environment in summer is ensured.
The details of one or more embodiments of the application are set forth in the accompanying drawings and the description below to provide a more thorough understanding of the other features, objects, and advantages of the application.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute a limitation on the application. In the drawings:
FIG. 1 is a schematic flow chart of a method for optimizing performance of a gas turbine set according to an embodiment of the present application;
fig. 2 is a schematic flow chart of adjusting an IGV opening according to an embodiment of the present application;
FIG. 3 is a schematic flow chart of a first fitted curve and a second fitted curve according to an embodiment of the present application;
FIG. 4 is a block diagram of a performance optimization system for a lift gas turbine unit provided by an embodiment of the present application;
fig. 5 is a schematic diagram of an internal structure of an electronic device according to an embodiment of the present application.
Detailed Description
The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is apparent that the drawings in the following description are only some examples or embodiments of the present application, and it is possible for those of ordinary skill in the art to apply the present application to other similar situations according to these drawings without inventive effort. Moreover, it should be appreciated that while such a development effort might be complex and lengthy, it would nevertheless be a routine undertaking of design, fabrication, or manufacture for those of ordinary skill having the benefit of this disclosure, and thus should not be construed as having the benefit of this disclosure.
Reference in the specification to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. It is to be expressly and implicitly understood by those of ordinary skill in the art that the described embodiments of the application can be combined with other embodiments without conflict.
Unless defined otherwise, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "a," "an," "the," and similar referents in the context of the application are not to be construed as limiting the quantity, but rather as singular or plural. The terms "comprising," "including," "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, article, or apparatus that comprises a list of steps or modules (elements) is not limited to only those steps or elements but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus. The terms "connected," "coupled," and the like in connection with the present application are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The term "plurality" as used herein means two or more. "and/or" describes an association relationship of an association object, meaning that there may be three relationships, e.g., "a and/or B" may mean: a exists alone, A and B exist together, and B exists alone. The character "/" generally indicates that the context-dependent object is an "or" relationship. The terms "first," "second," "third," and the like, as used herein, are merely distinguishing between similar objects and not representing a particular ordering of objects.
The embodiment of the application provides a performance optimization method, a system, a device and a medium for improving a gas unit.
In a first aspect, an embodiment of the present application provides a method for optimizing performance of a gas turbine unit, and fig. 1 is a schematic flow chart of the method for optimizing performance of a gas turbine unit, as shown in fig. 1, where the method includes the following steps:
and step S101, acquiring current working condition data of the gas turbine unit to determine a surge pressure ratio limit value.
In step S101, the gas unit may be a 9 FB-type gas unit, and the corresponding current working condition data is the working data of the 9 FB-type gas unit in the actual application process. Further, the 9FB type unit design working condition is: turbine inlet temperature 1371 ℃, combined cycle maximum power 450MW, using a standard DLN2.6+ combustor. Surging (charge) is a dynamic destabilization phenomenon in a gas turbine unit, which is represented by a gas flow countercurrent phenomenon occurring at the inlet of a compressor or between the compressor and a gas turbine. When surge occurs, the reverse flow of the gas flow can cause a dramatic drop in compressor performance, cause oscillations and noise, and can adversely affect the gas turbine or even cause equipment damage. The surge pressure ratio limit is a critical value of the compression ratio of the compressor for surging, and it is understood that the surge pressure ratio limit is determined according to the actual working condition in the field.
And step S102, adjusting the IGV opening based on the surge pressure ratio limit value until a first preset condition is met, recording the IGV opening and corresponding unit load in the adjustment process, and determining the target IGV opening based on the unit load.
The IGV opening is the degree of adjusting the position of an air inlet guide vane, and is used for controlling the air inlet flow and the aerodynamic characteristics of the gas turbine. By varying the IGV opening, the intake flow and speed of the gas turbine may be adjusted. A smaller IGV opening will restrict the intake air flow, while a larger IGV opening allows more intake air flow. By controlling the IGV opening, load regulation and performance optimization of the gas turbine may be achieved.
In operation, gas turbines typically perform an IGV opening adjustment based on load demand. Higher load demands typically require a greater IGV opening to increase intake air flow and provide adequate pneumatic pressure. Conversely, a lower load may require a decrease in IGV opening to reduce intake air flow and maintain proper operating conditions. Therefore, when the IGV opening is adjusted, the IGV opening and the corresponding unit load in the adjustment process are recorded in real time, and the target IGV opening is determined according to the unit load under the condition that the first preset condition is met, namely the optimized IGV opening.
In one embodiment, the first preset condition is NO x And the emission concentration of CO exceeds a preset concentration value, and the adjustment of the IGV opening is stopped.
Wherein NO x And the emission concentration of CO exceeds the standard of 30mg/m 3 At this time, the adjustment of the IGV opening degree is stopped.
Fig. 2 is a schematic flow chart of adjusting an IGV opening according to an embodiment of the present application, as shown in fig. 2, based on the flow chart shown in fig. 1, the adjusting the IGV opening based on a surge pressure ratio limit value includes the following steps:
step S201, determining a corresponding IGV opening reference value according to the surge pressure ratio limit value. In the actual operation of the gas turbine, the corresponding IGV opening reference value can be determined from the surge pressure ratio limit.
Step S202, the IGV opening is gradually reduced by adopting a preset step length by taking the IGV opening reference value as a reference.
In one embodiment, toGradually reducing the IGV opening for the step length, and calculating the influence of the IGV opening on the full load output and the heat consumption of the gas turbine and the combined cycle.
With continued reference to fig. 1, step S103 is performed after step S102, as follows.
Step S103, determining a first pressure ratio limit value according to the target IGV opening by utilizing a preset IGV opening-pressure ratio limit value curve.
In step S103, the predetermined IGV opening-pressure ratio limit curve may be referred to a technical manual, an operation manual, or other related documents of the apparatus, or may be acquired from a history database established by each electric power unit. And finding a corresponding first pressure ratio limit value from the curve through the target IGV opening and the IGV opening-pressure ratio limit value curve, wherein the first pressure ratio limit value is a new pressure ratio limit value after the IGV opening is optimized.
And S104, acquiring a first fitting curve and a second fitting curve of the pressure ratio limit value relative to the exhaust gas temperature, and determining a second pressure ratio limit value based on the first fitting curve and the second fitting curve.
Fig. 3 is a schematic flow chart of a first fitted curve and a second fitted curve provided by an embodiment of the present application, as shown in fig. 3, wherein an abscissa is a pressure ratio limit value, and an ordinate is a smoke exhaust temperature:
in one embodiment, obtaining a first fitted curve of the pressure ratio limit with respect to the exhaust gas temperature comprises:
and according to the non-triggering state of the peak load mode of the gas unit, calculating a smoke discharge temperature control reference value through a pressure ratio limit value, and determining a first fitting curve. The first fitted curve is the lower line in fig. 3.
The peak load mode of the gas turbine unit is in a state that the load of the current gas turbine unit is stable and the high load state requiring energy output increase is not achieved, in the state, a smoke exhaust temperature control reference value is calculated through a pressure ratio limit value and full load output data of the gas turbine unit by using a linear interpolation method, and then a first fitting curve is obtained through fitting according to a plurality of groups of pressure ratio limit values and the calculated smoke exhaust temperature control reference value.
Illustratively, the first fitted curve is characterized by F1 (X), the spike (Peak) load pattern described above is not triggered (l83pk=0), the exhaust temperature control reference value calculated by the pressure ratio (TTRXCPR) =f1 (CPR); f1 (X) = { (6, 1197.30004882813); (11.5485000610352, 1053.28002929688); (12.1082000732422, 1038.67004394531); (12.6969003677368, 1023.23999023438); (13.236499786377, 1014.88000488281); (13.7994003295898, 1006.15997314453); (17, 956.580017089844) };
illustratively, the partial discrete points formed by the pressure ratio and the exhaust gas temperature control reference value are expressed as:
X：6，11.5485000610352，12.1082000732422，12.6969003677368，13.236499786377，13.7994003295898，17；
Y：1197.30004882813，1053.28002929688，1038.67004394531，1023.23999023438，1014.88000488281，1006.15997314453，956.580017089844。
in one embodiment, obtaining a second fitted curve of the pressure ratio limit with respect to the exhaust gas temperature comprises:
and calculating a smoke discharge temperature control reference value through a pressure ratio limit value according to the peak load mode triggering state of the gas turbine unit, and determining a second fitting curve. The second fitted curve is the upper line in fig. 3.
According to the peak load mode triggering state of the gas turbine unit, the corrected smoke exhaust temperature control reference value is calculated through the pressure ratio limit value and the full load output data of the gas turbine unit by using a linear interpolation method, and then a second fitting curve is obtained through fitting by using a fitting method based on a plurality of groups of pressure ratio limit values and the calculated corrected smoke exhaust temperature control reference value.
First, a middle fitting curve F2 (X) is acquired, and, illustratively, the Peak load mode described above triggers a smoke temperature control reference value (TTRXCPR) =f2 (CPR) calculated by a pressure ratio;
F2(X)={(0，1489.02001953125)；(10.1174001693726，1088.40002441406)；(12.6969003677368，1033.23999023438)；(20，974.380004882813)}；
wherein, the partial discrete points formed by the pressure ratio and the exhaust gas temperature control reference value are expressed as:
X：0，10.1174001693726，12.6969003677368，20；
Y：1489.02001953125，1088.40002441406，1033.23999023438，974.380004882813。
further, a second fitted curve is determined based on the intermediate fitted curve F2 (X). Alternatively, the second fitted curve is expressed as: f2 (X) + (671.16 °f-compressor outlet temperature (CTD)). Wherein the compressor outlet temperature corresponds to the combustor inlet temperature.
After the first fitted curve and the second fitted curve are obtained, the intersection pressure ratio of the first fitted curve and the second fitted curve is determined as a second pressure ratio limit value. Specifically, if there is a single intersection point, the pressure ratio value corresponding to the intersection point is used as a second pressure ratio limit value; if at least two intersection points exist, the pressure ratio value corresponding to the intersection point with the smallest exhaust gas temperature is taken as a second pressure ratio limit value.
And the pressure ratio value corresponding to the lowest point of the exhaust gas temperature is selected as the second pressure ratio limit value, so that the influence of the operation parameters on the exhaust gas temperature is ensured, and the exhaust gas temperature is prevented from exceeding the standard so as to meet the optimization requirement.
Step S105, determining a target pressure ratio limit value according to the comparison of the first pressure ratio limit value and the second pressure ratio limit value.
In one embodiment, the second pressure ratio limit is taken as the target pressure ratio limit in response to the first pressure ratio limit being less than or equal to the second pressure ratio limit.
In another embodiment, in response to the first pressure ratio limit being greater than the second pressure ratio limit, the second pressure ratio limit is adjusted in a preset step size starting from the second pressure ratio limit to the pressure ratio limit at which the second preset condition is met to determine the target pressure ratio limit.
In summary, the performance optimization method for improving the gas turbine set provided by the embodiment of the application optimizes the operation performance of the gas turbine set in a high-temperature environment in summer by adjusting the IGV opening and the exhaust temperature of the gas turbine set, thereby reducing the condition of the decline of the full load output, solving the problem of the rapid decline of the output of the gas turbine set in the full load power generation in summer, realizing the improvement of the power generation efficiency and the equipment reliability, ensuring the normal operation of the set in the high-temperature condition in summer, improving the load of the set from the original 380MW to 400MW, increasing the output by 1.5%, and reducing the heat consumption by 0.15%.
It should be noted that the steps illustrated in the above-described flow or flow diagrams of the figures may be performed in a computer system, such as a set of computer-executable instructions, and that, although a logical order is illustrated in the flow diagrams, in some cases, the steps illustrated or described may be performed in an order other than that illustrated herein.
The embodiment also provides a performance optimization system for improving the gas turbine unit, which is used for realizing the above embodiment and the preferred embodiment, and is not described again. As used below, the terms "module," "unit," "sub-unit," and the like may be a combination of software and/or hardware that implements a predetermined function. While the means described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware, is also possible and contemplated.
FIG. 4 is a block diagram of a performance optimization system for a gas turbine engine, according to an embodiment of the present application, as shown in FIG. 4, the system includes:
the surge pressure ratio limit value acquisition module 301 is configured to acquire current working condition data of the gas turbine unit and determine a surge pressure ratio limit value.
The gas unit can be a 9FB type gas unit, and the corresponding current working condition data is the operation data of the 9FB type gas unit in the actual application process. Further, the 9FB type unit design working condition is: turbine inlet temperature 1371 ℃, combined cycle maximum power 450MW, using a standard DLN2.6+ combustor. Surging (charge) is a dynamic destabilization phenomenon in a gas turbine unit, which is represented by a gas flow countercurrent phenomenon occurring at the inlet of a compressor or between the compressor and a gas turbine. When surge occurs, the reverse flow of the gas flow can cause a dramatic drop in compressor performance, cause oscillations and noise, and can adversely affect the gas turbine or even cause equipment damage. The surge pressure ratio limit is a critical value of the compression ratio of the compressor for surging, and it is understood that the surge pressure ratio limit is determined according to the actual working condition in the field.
The target IGV opening obtaining module 302 is configured to adjust the IGV opening based on the surge pressure ratio limit value until a first preset condition is satisfied, record the IGV opening and a corresponding unit load during adjustment, and determine the target IGV opening based on the unit load.
The IGV opening is referred to as an inlet guide vane opening (IGV opening), which refers to the degree of adjustment of the position of the inlet guide vanes for controlling the inlet flow and the aerodynamic characteristics of the gas turbine. By varying the IGV opening, the intake flow and speed of the gas turbine may be adjusted. A smaller IGV opening will restrict the intake air flow, while a larger IGV opening allows more intake air flow. By controlling the IGV opening, load regulation and performance optimization of the gas turbine may be achieved.
In operation, gas turbines typically perform an IGV opening adjustment based on load demand. Higher load demands typically require a greater IGV opening to increase intake air flow and provide adequate pneumatic pressure. Conversely, a lower load may require a decrease in IGV opening to reduce intake air flow and maintain proper operating conditions. Therefore, when the IGV opening is adjusted, the IGV opening and the corresponding unit load in the adjustment process are recorded in real time, and the target IGV opening is determined according to the unit load under the condition that the first preset condition is met, namely the optimized IGV opening.
In one embodiment, the first preset condition is NO x And the emission concentration of CO exceeds a preset concentration value, and the adjustment of the IGV opening is stopped.
Wherein NO x And the emission concentration of CO exceeds the standard of 30mg/m 3 At this time, the adjustment of the IGV opening degree is stopped.
In one embodiment, adjusting the IGV opening based on the surge-to-pressure ratio limit includes performing the steps of:
and determining a corresponding IGV opening reference value according to the surge pressure ratio limit value. In the actual operation of the gas turbine, the corresponding IGV opening reference value can be determined from the surge pressure ratio limit.
And gradually reducing the IGV opening by adopting a preset step length by taking the IGV opening reference value as a reference. In particular, toGradually reducing the IGV opening for the step length, and calculating the influence of the IGV opening on the full load output and the heat consumption of the gas turbine and the combined cycle.
The first pressure ratio limit value obtaining module 303 is configured to determine a first pressure ratio limit value according to the target IGV opening degree by using a predetermined IGV opening degree-pressure ratio limit value curve.
The predetermined IGV opening-pressure ratio limit curve may be referred to a technical manual, an operation manual, or other related documents of the apparatus, or may be obtained from a history database self-formulated by each electric power unit. And finding a corresponding first pressure ratio limit value from the curve through the target IGV opening and the IGV opening-pressure ratio limit value curve, wherein the first pressure ratio limit value is a new pressure ratio limit value after the IGV opening is optimized.
The second pressure ratio limit value obtaining module 304 is configured to obtain a first fitted curve and a second fitted curve of the pressure ratio limit value with respect to the exhaust gas temperature, and determine the second pressure ratio limit value based on the first fitted curve and the second fitted curve.
The second pressure ratio limit acquisition module 304 further includes performing the steps of:
and according to the non-triggering state of the peak load mode of the gas unit, calculating a smoke discharge temperature control reference value through a pressure ratio limit value, and determining a first fitting curve.
The peak load mode of the gas turbine unit is in a state that the load of the current gas turbine unit is stable and the high load state requiring energy output increase is not achieved, in the state, a smoke exhaust temperature control reference value is calculated through a pressure ratio limit value and full load output data of the gas turbine unit by using a linear interpolation method, and then a first fitting curve is obtained through fitting according to a plurality of groups of pressure ratio limit values and the calculated smoke exhaust temperature control reference value.
Illustratively, the first fitted curve is characterized by F1 (X), the spike (Peak) load pattern described above is not triggered (l83pk=0), the exhaust temperature control reference value calculated by the pressure ratio (TTRXCPR) =f1 (CPR); f1 (X) = { (6, 1197.30004882813); (11.5485000610352, 1053.28002929688); (12.1082000732422, 1038.67004394531); (12.6969003677368, 1023.23999023438); (13.236499786377, 1014.88000488281); (13.7994003295898, 1006.15997314453); (17, 956.580017089844) };
illustratively, the partial discrete points formed by the pressure ratio and the exhaust gas temperature control reference value are expressed as:
X：6，11.5485000610352，12.1082000732422，12.6969003677368，13.236499786377，13.7994003295898，17；
Y：1197.30004882813，1053.28002929688，1038.67004394531，1023.23999023438，1014.88000488281，1006.15997314453，956.580017089844。
and calculating a smoke discharge temperature control reference value through a pressure ratio limit value according to the peak load mode triggering state of the gas turbine unit, and determining a second fitting curve.
According to the peak load mode triggering state of the gas turbine unit, the corrected smoke exhaust temperature control reference value is calculated through the pressure ratio limit value and the full load output data of the gas turbine unit by using a linear interpolation method, and then a second fitting curve is obtained through fitting by using a fitting method based on a plurality of groups of pressure ratio limit values and the calculated corrected smoke exhaust temperature control reference value.
First, a middle fitting curve F2 (X) is acquired, and, illustratively, the Peak load mode described above triggers a smoke temperature control reference value (TTRXCPR) =f2 (CPR) calculated by a pressure ratio;
F2(X)={(0，1489.02001953125)；(10.1174001693726，1088.40002441406)；(12.6969003677368，1033.23999023438)；(20，974.380004882813)}；
wherein, the partial discrete points formed by the pressure ratio and the exhaust gas temperature control reference value are expressed as:
X：0，10.1174001693726，12.6969003677368，20；
Y：1489.02001953125，1088.40002441406，1033.23999023438，974.380004882813。
further, a second fitted curve is determined based on the intermediate fitted curve F2 (X). Alternatively, the second fitted curve is expressed as: f2 (X) + (671.16 °f-compressor outlet temperature (CTD)). Wherein the compressor outlet temperature corresponds to the combustor inlet temperature.
After the first fitted curve and the second fitted curve are obtained, the intersection pressure ratio of the first fitted curve and the second fitted curve is determined as a second pressure ratio limit value. Specifically, if there is a single intersection point, the pressure ratio value corresponding to the intersection point is used as a second pressure ratio limit value; if at least two intersection points exist, the pressure ratio value corresponding to the intersection point with the smallest exhaust gas temperature is taken as a second pressure ratio limit value.
And the pressure ratio value corresponding to the lowest point of the exhaust gas temperature is selected as the second pressure ratio limit value, so that the influence of the operation parameters on the exhaust gas temperature is ensured, and the exhaust gas temperature is prevented from exceeding the standard so as to meet the optimization requirement.
Wherein, the exhaust gas temperature control reference value (TTRXB) after the IGV opening degree correction
Smoke temperature control setting reference value (TTRXSP): a temperature control minimum reference value (ttr_mina) for combustion adjustment bias correction;
the exhaust gas temperature control setting reference value (TTRXSP) outputs an exhaust gas temperature control reference value (TTRX) after passing through a rate limit (1.5 DEG F/s) and an upper and lower limit (0, 2048);
exhaust gas temperature control reference value (TTRXB) after IGV opening correction: a correction value (CSRGVTXB) of the exhaust gas temperature control reference value (TTRX) +IGV opening degree to temperature bias;
description: correction value of IGV opening to temperature bias (CSRGVTXB): after the IGV opening margin (85-IGV opening) is 3, the output is obtained after the rate limitation (2°f/s) and the upper and lower limits (0, 30).
The target pressure ratio limit value obtaining module 305 is configured to determine a target pressure ratio limit value according to a comparison between the first pressure ratio limit value and the second pressure ratio limit value.
The target pressure ratio limit value acquisition module 305 further includes performing the steps of:
and in response to the first pressure ratio limit being less than or equal to the second pressure ratio limit, taking the second pressure ratio limit as the target pressure ratio limit.
And in response to the first pressure ratio limit being greater than the second pressure ratio limit, adjusting the second pressure ratio limit with a preset step length by taking the second pressure ratio limit as a starting point, and determining the target pressure ratio limit when the pressure ratio limit meets a second preset condition.
In summary, the performance optimization system for improving the gas turbine set provided by the embodiment of the application optimizes the operation performance of the gas turbine set in a high-temperature environment in summer by adjusting the IGV opening and the exhaust temperature of the gas turbine set, thereby reducing the condition of the decline of the full load output, solving the problem of the rapid decline of the output of the gas turbine set in the full load power generation in summer, realizing the improvement of the power generation efficiency and the equipment reliability, ensuring the normal operation of the set in the high-temperature condition in summer, improving the load of the set from the original 380MW to 400MW, increasing the output by 1.5%, and reducing the heat consumption by 0.15%.
The above-described respective modules may be functional modules or program modules, and may be implemented by software or hardware. For modules implemented in hardware, the various modules described above may be located in the same processor; or the above modules may be located in different processors in any combination.
The embodiment also provides a performance optimizing device for improving the gas unit, which comprises a memory and one or more processors, wherein executable codes are stored in the memory, and the one or more processors are used for realizing the steps in any one of the method embodiments when executing the executable codes.
Optionally, the performance optimizing device of the lifting gas unit may further include a transmission device and an input/output device, where the transmission device is connected to the processor, and the input/output device is connected to the processor.
It should be noted that, specific examples in this embodiment may refer to examples described in the foregoing embodiments and alternative implementations, and this embodiment is not repeated herein.
In addition, in combination with the performance optimization method of the gas turbine unit in the above embodiment, the embodiment of the application may provide a storage medium for implementation. The storage medium has a computer program stored thereon; the computer program, when executed by the processor, implements the performance optimization method of any of the enhanced gas turbine sets in the above embodiments.
In one embodiment, a computer device is provided, which may be a terminal. The computer device includes a processor, a memory, a network interface, a display screen, and an input device connected by a system bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage media. The network interface of the computer device is used for communicating with an external terminal through a network connection. The computer program, when executed by the processor, implements a method of optimizing performance of the enhanced gas turbine unit. The display screen of the computer equipment can be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer equipment can be a touch layer covered on the display screen, can also be keys, a track ball or a touch pad arranged on the shell of the computer equipment, and can also be an external keyboard, a touch pad or a mouse and the like.
In an embodiment, fig. 5 is a schematic diagram of an internal structure of an electronic device according to an embodiment of the present application, as shown in fig. 5, and an electronic device is provided, where the electronic device may be a server, and an internal structure diagram of the electronic device may be shown in fig. 5. The electronic device includes a processor, a network interface, an internal memory, and a non-volatile memory connected by an internal bus, where the non-volatile memory stores an operating system, computer programs, and a database. The processor is used for providing computing and control capability, the network interface is used for communicating with an external terminal through network connection, the internal memory is used for providing environment for the operation of an operating system and a computer program, the computer program is executed by the processor to realize the performance optimization method for improving the gas turbine set, and the database is used for storing data.
It will be appreciated by those skilled in the art that the structure shown in fig. 5 is merely a block diagram of a portion of the structure associated with the present inventive arrangements and is not limiting of the electronic device to which the present inventive arrangements are applied, and that a particular electronic device may include more or fewer components than shown, or may combine certain components, or have a different arrangement of components.
Those skilled in the art will appreciate that implementing all or part of the above described methods may be accomplished by way of a computer program stored on a non-transitory computer readable storage medium, which when executed, may comprise the steps of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in embodiments provided herein may include non-volatile and/or volatile memory. The nonvolatile memory can include Read Only Memory (ROM), programmable ROM (PROM), electrically Programmable ROM (EPROM), electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double Data Rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous Link DRAM (SLDRAM), memory bus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), among others.
It should be understood by those skilled in the art that the technical features of the above-described embodiments may be combined in any manner, and for brevity, all of the possible combinations of the technical features of the above-described embodiments are not described, however, they should be considered as being within the scope of the description provided herein, as long as there is no contradiction between the combinations of the technical features.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (10)
1. A method of optimizing performance of a lift gas turbine unit, the method comprising:
acquiring current working condition data of a gas unit to determine a surge pressure ratio limit value;
adjusting the IGV opening based on the surge pressure ratio limit value until a first preset condition is met, recording the IGV opening and corresponding unit load in the adjustment process, and determining a target IGV opening based on the unit load;
determining a first pressure ratio limit value according to the target IGV opening by utilizing a preset IGV opening-pressure ratio limit value curve;
acquiring a first fitting curve and a second fitting curve of the pressure ratio limit value relative to the exhaust gas temperature, and determining a second pressure ratio limit value based on the first fitting curve and the second fitting curve;
and determining a target pressure ratio limit value according to the comparison of the first pressure ratio limit value and the second pressure ratio limit value.
2. The method of optimizing performance of a lifting gas turbine unit of claim 1, wherein said adjusting IGV opening based on said surge pressure ratio limit comprises:
determining a corresponding IGV opening reference value according to the surge pressure ratio limit value;
and taking the IGV opening reference value as a reference, and gradually reducing the IGV opening by adopting a preset step length.
3. The method of optimizing performance of a lift gas turbine unit of claim 1, wherein the first preset condition is that the emission concentration of NOx and CO exceeds a preset concentration value, and the adjustment of the IGV opening is stopped.
4. The method of optimizing performance of a lift gas turbine unit of claim 1, wherein said obtaining a first fitted curve of pressure ratio limits with respect to exhaust gas temperature comprises:
and according to the non-triggering state of the peak load mode of the gas turbine unit, calculating a smoke discharge temperature control reference value through a pressure ratio limit value, and determining the first fitting curve.
5. The method of optimizing performance of a lift gas turbine unit of claim 1, wherein said obtaining a second fitted curve of pressure ratio limits with respect to exhaust gas temperature comprises:
and calculating a smoke exhaust temperature control reference value through a pressure ratio limit value according to the peak load mode triggering state of the gas turbine unit, and determining the second fitting curve.
6. The method of optimizing performance of a lift gas turbine unit of claim 1, wherein said determining a target pressure ratio limit based on a comparison of said first pressure ratio limit and said second pressure ratio limit comprises:
and in response to the first pressure ratio limit being less than or equal to the second pressure ratio limit, taking the second pressure ratio limit as the target pressure ratio limit.
7. The method of optimizing performance of a lift gas turbine unit of claim 1, wherein said determining a target pressure ratio limit based on a comparison of said first pressure ratio limit and said second pressure ratio limit comprises:
and in response to the first pressure ratio limit being greater than the second pressure ratio limit, adjusting the second pressure ratio limit with a preset step length by taking the second pressure ratio limit as a starting point, and determining the target pressure ratio limit by the pressure ratio limit when a second preset condition is met.
8. A performance optimization system for a lift gas turbine unit, the system comprising:
the surge pressure ratio limit value acquisition module is used for acquiring current working condition data of the gas turbine unit and determining a surge pressure ratio limit value;
the target IGV opening acquisition module is used for adjusting the IGV opening based on the surge pressure ratio limit value until a first preset condition is met, recording the IGV opening and corresponding unit load in the adjustment process, and determining the target IGV opening based on the unit load;
the first pressure ratio limit value acquisition module is used for determining a first pressure ratio limit value according to the target IGV opening by utilizing a preset IGV opening-pressure ratio limit value curve;
the second pressure ratio limit value acquisition module is used for acquiring a first fitting curve and a second fitting curve of the pressure ratio limit value relative to the exhaust gas temperature, and determining a second pressure ratio limit value based on the first fitting curve and the second fitting curve;
and the target pressure ratio limit value acquisition module is used for determining a target pressure ratio limit value according to the comparison of the first pressure ratio limit value and the second pressure ratio limit value.
9. A performance optimization apparatus for a gas turbine unit, comprising a memory and one or more processors, the memory having executable code stored therein, the one or more processors configured to implement the performance optimization method for a gas turbine unit of any one of claims 1-7 when executing the executable code.
10. A computer readable storage medium, having stored thereon a program which, when executed by a processor, implements the method of optimizing the performance of a gas turbine engine unit according to any one of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310953692.0A CN116696560B (en) | 2023-08-01 | 2023-08-01 | Performance optimization method, system, device and medium for improving gas unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310953692.0A CN116696560B (en) | 2023-08-01 | 2023-08-01 | Performance optimization method, system, device and medium for improving gas unit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116696560A true CN116696560A (en) | 2023-09-05 |
| CN116696560B CN116696560B (en) | 2024-01-02 |
Family
ID=87824249
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310953692.0A Active CN116696560B (en) | 2023-08-01 | 2023-08-01 | Performance optimization method, system, device and medium for improving gas unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116696560B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001123852A (en) * | 1999-10-27 | 2001-05-08 | Hitachi Ltd | Gas turbine power generation control device |
| US20090113896A1 (en) * | 2006-12-12 | 2009-05-07 | Toyota Jidosha Kabushiki Kaisha | Control apparatus and method for gas-turbine engine |
| CN107035537A (en) * | 2017-04-28 | 2017-08-11 | 申能股份有限公司 | A kind of combined cycle warming-up load dynamic matching method |
| US20170254282A1 (en) * | 2014-09-02 | 2017-09-07 | Mitsubishi Hitachi Power Systems, Ltd. | Control device, system, control method, power control device, gas turbine, and power control method |
| CN107849981A (en) * | 2015-09-24 | 2018-03-27 | 三菱日立电力系统株式会社 | The control device and method of gas turbine, the control program of gas turbine, gas turbine |
| CN110107407A (en) * | 2019-04-19 | 2019-08-09 | 江苏国信淮安第二燃气发电有限责任公司 | A method of optimization combustion engine IGV control promotes Gas-steam Combined Cycle efficiency |
| JP2021193282A (en) * | 2020-06-08 | 2021-12-23 | 三菱パワー株式会社 | Gas turbine control device, method and gas turbine |
| CN115929677A (en) * | 2023-01-17 | 2023-04-07 | 上海电气燃气轮机有限公司 | Modification method of gas turbine compressor in high-temperature environment |
| CN116241496A (en) * | 2023-02-15 | 2023-06-09 | 华电湖北发电有限公司武昌热电分公司 | Supercharger anti-surge valve control method, device, equipment and storage medium |
-
2023
- 2023-08-01 CN CN202310953692.0A patent/CN116696560B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001123852A (en) * | 1999-10-27 | 2001-05-08 | Hitachi Ltd | Gas turbine power generation control device |
| US20090113896A1 (en) * | 2006-12-12 | 2009-05-07 | Toyota Jidosha Kabushiki Kaisha | Control apparatus and method for gas-turbine engine |
| US20170254282A1 (en) * | 2014-09-02 | 2017-09-07 | Mitsubishi Hitachi Power Systems, Ltd. | Control device, system, control method, power control device, gas turbine, and power control method |
| CN107849981A (en) * | 2015-09-24 | 2018-03-27 | 三菱日立电力系统株式会社 | The control device and method of gas turbine, the control program of gas turbine, gas turbine |
| CN107035537A (en) * | 2017-04-28 | 2017-08-11 | 申能股份有限公司 | A kind of combined cycle warming-up load dynamic matching method |
| CN110107407A (en) * | 2019-04-19 | 2019-08-09 | 江苏国信淮安第二燃气发电有限责任公司 | A method of optimization combustion engine IGV control promotes Gas-steam Combined Cycle efficiency |
| JP2021193282A (en) * | 2020-06-08 | 2021-12-23 | 三菱パワー株式会社 | Gas turbine control device, method and gas turbine |
| CN115929677A (en) * | 2023-01-17 | 2023-04-07 | 上海电气燃气轮机有限公司 | Modification method of gas turbine compressor in high-temperature environment |
| CN116241496A (en) * | 2023-02-15 | 2023-06-09 | 华电湖北发电有限公司武昌热电分公司 | Supercharger anti-surge valve control method, device, equipment and storage medium |
Non-Patent Citations (1)
| Title |
|---|
| 孙鹏: "燃气轮机联合循环机组一次调频能力分析与优化方法研究", 《节能技术》, vol. 37, no. 6, pages 493 - 498 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116696560B (en) | 2024-01-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8307645B2 (en) | Apparatus and method for avoidance of turbocharger surge on locomotive diesel engines | |
| EP2823168B1 (en) | Method to control gas turbine engine power output | |
| US20090056342A1 (en) | Methods and Systems for Gas Turbine Part-Load Operating Conditions | |
| JP5460990B2 (en) | How to control a turbocharger using a physical model of turbocharger speed | |
| EP2600063A2 (en) | Method of operating a gas turbine with staged and/or sequential combustion | |
| EP2418368A2 (en) | Method for compensating for combustion efficiency in fuel control system | |
| CN113357017B (en) | Method for controlling rotating speed of aircraft engine in acceleration process | |
| EP3048280B1 (en) | Systems and methods for control of turbocharger wastegate | |
| KR20180040105A (en) | Systems and methods to control performance via control of compressor oll protection actions | |
| US9726085B2 (en) | Method for controlling a gas turbine group | |
| CN116696560B (en) | Performance optimization method, system, device and medium for improving gas unit | |
| US11092085B2 (en) | Method and system for controlling a sequential gas turbine engine | |
| CN114893305B (en) | Control method and system of gas unit | |
| CN110925106A (en) | Control method and device of throttle valve of engine, electronic equipment and engine | |
| BR102013002451A2 (en) | OXYGEN CONCENTRATION ADJUSTMENT POINT MODIFICATION | |
| JP6907207B2 (en) | Gas turbine combustion temperature control using air injection system | |
| CN101187317B (en) | Corrected parameter control method for a two-shaft gas turbine | |
| CN112761794B (en) | Method for checking ground starting stability margin of aircraft engine | |
| US20180306111A1 (en) | Gas turbine system and control apparatus and method thereof | |
| RU2665011C2 (en) | Method and system for controlling operating temperature of vehicle boost pressure device and vehicle comprising temperature control system | |
| CN117432540B (en) | Supercharger surge control method and device | |
| CN115034083B (en) | Induced draft fan power consumption correction calculation method in station service power consumption calculation of thermal power generating unit | |
| CN114033555B (en) | Method for reducing yellow smoke discharge time | |
| US20230086029A1 (en) | System and method for non-model based control utilizing turbine exit mach number surrogate | |
| CN116255249A (en) | Design method for ground starting ignition oil supply of aviation gas turbine engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |