CN114592973A - Method, system, equipment and medium for controlling angle of adjustable stator blade of gas turbine - Google Patents
Method, system, equipment and medium for controlling angle of adjustable stator blade of gas turbine Download PDFInfo
- Publication number
- CN114592973A CN114592973A CN202210260923.5A CN202210260923A CN114592973A CN 114592973 A CN114592973 A CN 114592973A CN 202210260923 A CN202210260923 A CN 202210260923A CN 114592973 A CN114592973 A CN 114592973A
- Authority
- CN
- China
- Prior art keywords
- value
- angle
- gas turbine
- adjustable stator
- stator blade
- 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
Images
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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/60—Control system actuates means
- F05D2270/64—Hydraulic actuators
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Geometry (AREA)
- Fluid Mechanics (AREA)
- Control Of Turbines (AREA)
Abstract
The invention provides a method, a system, equipment and a medium for controlling the angle of an adjustable stator blade of a gas turbine. The method comprises the following steps: acquiring a reliable measurement value of each gas turbine parameter of the gas turbine parameters, wherein the parameters comprise the rotating speed of the gas turbine, the inlet temperature of a gas compressor and the position of an actuating cylinder; obtaining a corrected gas turbine rotating speed according to the gas turbine rotating speed and the reliable measurement value of the inlet temperature of the gas compressor; obtaining an angle requirement value by using the corrected rotating speed of the gas turbine and a first preset rule; obtaining a required value of the position of the actuating cylinder by utilizing the required value of the angle of the adjustable stator blade and a second preset rule; adjusting hydraulic oil supplied to the actuator cylinder by using the deviation between the required value of the position of the actuator cylinder and the measured reliable value of the position of the actuator cylinder, so that the actuator cylinder reaches the required position to adjust the angle of the adjustable stator blade; and obtaining an angle indirect measurement value by utilizing the position measurement reliable value of the actuating cylinder and a third preset rule for judging the accuracy of angle control.
Description
Technical Field
The invention relates to a method, a system, equipment and a medium for controlling the angle of an adjustable stator blade of a gas turbine.
Background
The gas turbine is used as a bright bead on an industrial crown, is widely applied to various industrial scenes such as aviation power, gas power generation, pipeline compression and the like in China, and is extremely important in safe and stable operation because of going deep into key links of industrial production. However, the gas turbine technology is not completely mastered in China, and core technologies such as hot end component manufacturing, DLN combustion, automatic control systems and the like are still monopolized by foreign companies. The control of a Variable Stator Vane (VSV) of a gas turbine is a control method aiming at the stable operation of a compressor, and the main purpose of realizing the control is to ensure the fault-free operation of the compressor in various rotating speeds and inlet temperature ranges. The air compressor sucks air from the surrounding atmosphere, compresses the air and provides air with certain pressure and temperature for a combustion chamber behind the air compressor, and the VSV consists of angle-adjustable static blades in front of a first stage of movable blades at the inlet of the air compressor and a plurality of stages of static blades behind the static blades, so that the surge of a unit can be prevented in the starting and stopping processes of the unit, and the operation safety of the air compressor is protected. By controlling the deflection angle of the adjustable stator blade, the total cycle efficiency of the gas turbine can be effectively improved.
However, in the angle control process of the adjustable stator blade of the gas compressor of the existing gas turbine, the problems that the working point of the gas compressor is not matched with the angle of the VSV, the stability, the rapidity and the accuracy of VSV control cannot be guaranteed and the like exist.
Disclosure of Invention
Technical problem to be solved
In the angle control process of the adjustable stator blade of the gas compressor of the existing gas turbine, the problems that the working point of the gas compressor is not matched with the angle of the VSV, the stability, the rapidity and the accuracy of VSV control cannot be guaranteed and the like exist.
(II) technical scheme
The invention provides an angle control method of an adjustable stator blade of a gas turbine, which comprises the following steps: acquiring parameters of a gas turbine through N groups of sensors, and preferably logically obtaining a measurement reliable value of each gas turbine parameter according to preset multi-sensor monitoring values, wherein the gas turbine parameters comprise the rotating speed of the gas turbine, the inlet temperature of a gas compressor and the position measurement value of an actuating cylinder, and N is more than or equal to 1; obtaining a corrected gas turbine rotating speed according to the gas turbine rotating speed and the reliable measurement value of the gas compressor inlet temperature; obtaining an angle requirement value of the adjustable stator blade by using the corrected rotating speed of the gas turbine and a first preset rule; obtaining a required value of the position of an actuating cylinder for driving the adjustable stator blade by utilizing the required value of the angle of the adjustable stator blade and a second preset rule; obtaining a driving current input value of a servo valve for controlling a hydraulic pump by utilizing the deviation between the required value of the position of the actuating cylinder and the reliable measurement value of the position of the actuating cylinder, so that the servo valve controls the opening of the hydraulic pump according to the current input value, hydraulic oil is provided for the actuating cylinder, the actuating cylinder reaches the required position to drive the adjustable stator blade to act, and the angle of the adjustable stator blade is controlled; and obtaining the indirect measurement value of the angle of the current adjustable stator blade by utilizing the reliable value of the position measurement of the actuating cylinder and a third preset rule, and judging the accuracy of the angle control of the adjustable stator blade.
Optionally, the N sets of sensors are 2 sets of sensors, and the reliable value of the gas turbine parameter is one of the following values: the sensor system comprises a first sensor measurement value, a second sensor measurement value, an average of the first sensor measurement value and the second sensor measurement value, a maximum of the first sensor measurement value and the second sensor measurement value, a minimum of the first sensor measurement value and the second sensor measurement value, and a preset default value.
Optionally, the corrected gas turbine speed is obtained by: the corrected gas turbine speed is equal to the square root correction value of the gas turbine speed/the compressor inlet temperature.
Optionally, the first preset rule is an interpolation table of the rotating speed and the angle requirement value of the adjustable stator blade.
Optionally, the second predetermined rule is an interpolation table of the corrected angle requirement of the adjustable stator vane and the actuator position requirement for driving the adjustable stator vane.
Optionally, the corrected angle requirement of the adjustable stator vane is obtained by: and the corrected angle requirement value of the adjustable stator blade is equal to the angle requirement value of the adjustable stator blade multiplied by an adjustable stator blade scaling constant and an adjustable stator blade deviation constant, wherein the adjustable stator blade scaling constant is 0.0-5.0, and the adjustable stator blade deviation constant is-20.
Optionally, the driving current input value is obtained by: a drive current input value ═ proportional gain coefficient × (actuator position demand value-actuator position measurement reliability value) + integral gain coefficient × (actuator position demand value-actuator position measurement reliability value) dt; and calibrating the proportional gain coefficient and the integral gain coefficient according to the action time of not more than 10 seconds from the maximum stator angle to the minimum stator angle. The proportional gain coefficient is between 0 and 20, and the integral gain coefficient is between 0 and 1.
In another aspect of the present invention, there is provided a system for controlling an angle of an adjustable stator blade of a gas turbine, the system comprising: the parameter acquisition module is used for acquiring parameters of the gas turbines through N groups of sensors, and obtaining a measurement reliable value of each parameter of the gas turbines according to a preset multi-sensor monitoring value optimization logic rule, wherein the parameters of the gas turbines comprise the rotating speed of the gas turbines, the inlet temperature of a gas compressor and the position of an actuating cylinder, and N is more than or equal to 1; the rotating speed correction module is used for obtaining the corrected rotating speed of the gas turbine according to the rotating speed of the gas turbine and the measured reliable value of the inlet temperature of the gas compressor; the adjustable stator blade angle requirement value acquisition module is used for acquiring an angle requirement value of the adjustable stator blade by utilizing the corrected rotating speed of the gas turbine and a first preset rule; the actuating cylinder position required value acquisition module is used for acquiring an actuating cylinder position required value by utilizing the angle required value of the adjustable stator blade and a second preset rule; and the angle control module is used for obtaining a driving current input value of a servo valve of the control hydraulic pump by utilizing the deviation between the required value of the position of the actuating cylinder and the reliable value of the position measurement of the actuating cylinder, so that the servo valve controls the opening of the hydraulic pump according to the current input value, hydraulic oil is provided for the actuating cylinder, the actuating cylinder reaches the required position to drive the adjustable stator blade to act, and the angle of the adjustable stator blade is controlled. And the control accuracy judging module is used for obtaining the current adjustable stator blade angle indirect measurement value by utilizing the actuator cylinder position measurement reliable value and a third preset rule and is used for judging the accuracy of the adjustable stator blade angle control.
Yet another aspect of the present invention provides an electronic device, including: a processor; a memory storing a computer executable program which, when executed by the processor, causes the processor to implement a method of remote sensing data processing as described above.
A further aspect of the invention provides a computer-readable storage medium, on which a computer program is stored, which program, when being executed by a processor, carries out the method of remote sensing data processing as described above.
(III) advantageous effects
The angle control method for the adjustable stator blade of the gas turbine provided by the embodiment of the invention at least has the following beneficial effects:
a linear variable differential sensor, a temperature sensor and a rotating speed sensor are arranged on a gas turbine to feed back sensor signals to a gas turbine controller, a rotating speed correction value and an actuator cylinder position measurement reliable value of the gas turbine are obtained through logical selection and conversion of the sensors, and errors between a position required value of an adjustable stator blade, a driving current input value and the position and the requirement of the adjustable stator blade are obtained through calculation respectively. The angle of the adjustable stator blade can be accurately adjusted, and the working stability of the gas compressor is further improved.
The problem that the working condition point of the gas compressor is not matched with the angle of the adjustable stator blade in the angle control process of the adjustable stator blade of the gas compressor of the existing gas turbine is solved;
the negative feedback control mechanism for the angle control of the adjustable stator blade is provided, the close matching and the self-adaptive control of the angle and the performance parameter of the gas turbine can be realized, and a stable, quick and accurate method is provided for the control of the adjustable stator blade.
Drawings
For a more complete understanding of the present invention, and the advantages thereof, reference is now made to the following descriptions taken in conjunction with the accompanying drawings, in which:
FIG. 1 schematically illustrates a general schematic view of a gas turbine adjustable stator vane adjustment system provided by an embodiment of the present invention;
FIG. 2 is a flow chart illustrating a method for controlling an angle of a variable stator vane of a gas turbine according to an embodiment of the present invention;
FIG. 3 is a flow chart schematically illustrating preferred logic for multiple sensor monitoring values in a method for controlling the angle of a variable stator vane of a gas turbine engine provided in accordance with an embodiment of the present invention;
FIG. 4 is a block diagram schematically illustrating an angle control system for a variable stator vane of a gas turbine engine provided in an embodiment of the present invention;
FIG. 5 schematically illustrates a block diagram of an electronic device provided in accordance with an embodiment of the invention;
FIG. 6 is a block diagram schematically illustrating a method for controlling an angle of a variable stator vane of a gas turbine provided by an embodiment of the present invention;
FIG. 7 is a schematic illustration of the adjustable stator structure of a gas turbine engine;
FIG. 8 is a schematic illustration of a gas turbine adjustable stator hydraulic drive apparatus assembly and description;
FIG. 9 schematically illustrates a logic diagram for an angle requirement calculation module for a variable stator vane of a gas turbine provided in an embodiment of the present invention;
FIG. 10 is a block diagram schematically illustrating a driving current input calculation of a gas turbine hydraulic drive apparatus provided by an embodiment of the present invention;
FIG. 11 is a block diagram of a gas turbine adjustable stator vane control accuracy determination calculation according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to specific embodiments and the accompanying drawings. It is to be understood that such description is merely illustrative and not intended to limit the scope of the present invention. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the invention. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
One embodiment of the invention provides a method for controlling the angle of an adjustable stator blade of a gas turbine.
First, it should be noted that the angle control method for the adjustable Stator Vane of the gas turbine provided by the embodiment of the present invention is applied to a Variable Stator Vane (VSV) system of the gas turbine, which is an essential part of a compressor Stator, and is composed of an Inlet Guide Vane (Inlet Guide Vane, IGV), multiple stages of Stator vanes, 2 VSV cylinders and torque shafts, an actuating ring, and a linkage for each VSV stage, referring to fig. 1, 7, and 8. The IGV is located in the front of the compressor and is mechanically connected to the VSV, which regulates flow at part load and increases the efficiency of the gas turbine. The positions of the Inlet Guide Vanes (IGV) and the adjustable stator vanes (VSV) can be controlled by a control system by actuating current-regulated servo valves. The control system comprises a hydraulic pump, a servo valve and a Linear Variable Differential Transformer (LVDT), wherein the servo valve supplies hydraulic oil to the actuating cylinder by controlling the opening degree of the hydraulic pump and is used for driving a torque shaft of the inlet guide vane and the adjustable stator vane linkage device, and each stage of VSV actuating ring is driven to act by the torque shaft, so that each stage of stator vane rotates to the angle required by the control system.
Referring to fig. 2 and fig. 6, which include step 101 and step 106, specifically, the control method includes:
step 101: the method comprises the steps of obtaining parameters of the gas turbine through N groups of sensors, and obtaining a measurement reliable value of each parameter of the gas turbine according to a preset multi-sensor monitoring value optimization logic, wherein the parameters of the gas turbine comprise the rotating speed of the gas turbine, the inlet temperature of a gas compressor and the position of an actuating cylinder, and N is larger than or equal to 1.
In the embodiment of the present invention, 2 sets of sensors are taken as an example for illustration, but the number of the sensors in the embodiment of the present invention is not particularly limited. Namely, one group of sensors comprises 1 linear variable differential sensor, 1 temperature sensor and 1 rotating speed sensor, and 2 linear variable differential sensors, 2 temperature sensors and 2 rotating speed sensors are mounted on the gas turbine. The measured reliable value of the gas turbine parameter is one of the following values: the first sensor measurement value, the second sensor measurement value, an average of the first sensor measurement value and the second sensor measurement value, a maximum of the first sensor measurement value and the second sensor measurement value, a minimum of the first sensor measurement value and the second sensor measurement value, and a preset default value.
Referring to fig. 3, it shows the flow of the method of the embodiment of the present invention for obtaining gas turbine parameters through 2 sets of sensors and obtaining the reliable measurement value of each of the gas turbine parameters according to the preset selection statistical rule. Specifically, as can be seen from the arrow direction from the start position to the right in fig. 3, it is first determined whether the first sensor measurement value is in the sensor normal measurement range, if not, it is determined whether the second sensor measurement value is in the sensor normal measurement range, if so, the second sensor measurement value is taken as a measurement reliability value, if not, both sensors fail, it is determined whether the sensor monitoring value allows the use of an artificial preset value for logical determination, if so, a preset default value is taken as a measurement reliability value, and if not, an alarm shutdown is performed. As can be seen from the arrow direction from the start position to the left in fig. 3, it is first determined whether the first sensor measurement value is in the sensor normal measurement range, if so, it is determined whether the second sensor measurement value is in the sensor normal measurement range, if not, the first sensor measurement value is taken as a measurement reliable value, if so, it is determined whether an error between the first sensor measurement value and the second sensor measurement value is smaller than an allowable error, if so, it is determined whether to execute an average value taking method, if so, an average value taking method is executed, an average value of the first sensor measurement value and the second sensor measurement value is taken as a measurement reliable value, and if not, a minimum value of the first sensor measurement value and the second sensor measurement value is taken as a measurement reliable value. And when the error between the measured value of the first sensor and the measured value of the second sensor is greater than the allowable error, judging whether the maximum value safety value taking method is executed on the measured value of the first sensor and the measured value of the second sensor, if so, taking the maximum value of the measured value of the first sensor and the measured value of the second sensor as a reliable measurement value, and if not, taking the average value of the measured value of the first sensor and the measured value of the second sensor as a reliable measurement value and giving an alarm. Whether the average value taking method and the maximum value safe value taking method are selected is manually set and selected, and the average value taking method and the maximum value safe value taking method can be selected by operators according to the execution condition of control logic.
Step 102: and obtaining the corrected rotating speed of the gas turbine according to the reliable measurement value of the rotating speed of the gas turbine and the inlet temperature of the gas compressor.
Wherein the corrected gas turbine speed is obtained by:
referring to fig. 9, step 103: and obtaining the angle requirement value of the adjustable stator blade by using the corrected rotating speed of the gas turbine and a first preset rule.
The first preset rule is an interpolation table of the rotating speed and the angle requirement value of the adjustable stator blade.
In the interpolation table of the rotating speed and the angle requirement value of the adjustable stator blade, the rotating speed and the angle requirement value of the adjustable stator blade are composed of 2 rows of data of different rotating speeds of the gas turbine and the position angles of the adjustable stator blades of the gas compressor which correspond to the gas turbine one by one, and when the gas turbine operates at a specific rotating speed, the angle requirement value of the adjustable stator blade at the rotating speed is obtained through interpolation of 2 groups of rotating speeds adjacent to the rotating speed and the position angles of the corresponding adjustable stator blades. The data in the interpolation table is the adjustable stationary blade position angle value which is determined by the gas compressor under the typical working condition rotating speed of the gas turbine through the gas compressor part test and the numerical simulation research and has the comprehensive optimal safety margin, pressure ratio and efficiency.
Step 104: and obtaining a required value of the position of the actuating cylinder for driving the adjustable stator blade by using the required value of the angle of the adjustable stator blade and a second preset rule.
The second preset rule is an interpolation table of the corrected angle requirement of the adjustable stator blade and the actuator cylinder position requirement for driving the adjustable stator blade.
In the interpolation table of the angle requirement value of the adjustable stator blade and the actuator cylinder position requirement value for driving the adjustable stator blade, the interpolation table consists of 2 lines of data in total, namely the corrected angle requirement value of the adjustable stator blade and the actuator cylinder position requirement value for driving the adjustable stator blade, which corresponds to the angle requirement value of the adjustable stator blade one by one. When the angle requirement value of a specific adjustable stator blade needs to be reached, the corresponding actuator cylinder position requirement value is obtained through interpolation of 2 groups of adjustable stator blade angle requirement values adjacent to the angle requirement value and the actuator cylinder position requirement value for driving the adjustable stator blade. The data in the interpolation table is determined by the relationship between the motion position of the actuating cylinder obtained by mechanical tests and the deflection angle of the adjustable stationary blade which can be driven.
The corrected angle requirement of the adjustable stator vane is obtained by the following formula:
the corrected adjustable stator vane angle requirement is the adjustable stator vane angle requirement x the adjustable stator vane zoom constant + the adjustable stator vane offset constant,
wherein the zoom constant of the adjustable stator blade is 0.0-5.0, the common value is 1.0, the deviation constant of the adjustable stator blade is-20, and the common value is 0. The purpose of the correction is to correct and compensate for deviations due to wear of the adjusting device after long-term operation.
Referring to fig. 10, step 105: and obtaining a driving current input value of a servo valve for controlling the hydraulic pump by utilizing the deviation between the required value of the position of the actuating cylinder and the reliable measurement value of the position of the actuating cylinder, so that the servo valve controls the opening of the hydraulic pump according to the current input value, hydraulic oil is provided for the actuating cylinder, the actuating cylinder reaches the required position to drive the adjustable stator blade to act, and the angle of the adjustable stator blade is controlled.
The torque motor current input value is obtained by the following formula:
a drive current input value ═ proportional gain coefficient × (actuator position required value-actuator position measurement reliability) + integral gain coefficient × (actuator position required value-actuator position measurement reliability) dt;
and calibrating the proportional gain coefficient and the integral gain coefficient according to the action time of not more than 10 seconds from the maximum stator angle to the minimum stator angle. The proportional gain coefficient is between 0 and 20, and the integral gain coefficient is between 0 and 1.
Referring to fig. 11, step S106: and obtaining the indirect measurement value of the angle of the current adjustable stator blade by using the measurement reliable value of the position of the actuating cylinder and a third preset rule, and judging the accuracy of the angle control of the adjustable stator blade. And obtaining an angle value of the adjustable stator blade through the measurement reliable value of the actuator cylinder position and a third preset rule, and obtaining an error between the angle value of the adjustable stator blade and the angle required value of the adjustable stator blade, wherein the third preset rule is an interpolation table for driving the position of the adjustable stator blade actuator cylinder and the angle of the adjustable stator blade.
In the interpolation table of the actuator cylinder position and the adjustable stator blade angle, the position of the movable adjustable stator blade actuator cylinder and the adjustable stator blade angle corresponding to the movable adjustable stator blade actuator cylinder one by one are composed of 2 rows of data. When the current adjustable stator blade angle needs to be obtained through judgment, the corresponding adjustable stator blade angle is obtained through interpolation of the position values of 2 groups of actuating cylinders adjacent to the current actuating cylinder position and the adjustable stator blade angle. The data in the interpolation table is determined by the relationship between the motion position of the actuating cylinder obtained by mechanical tests and the deflection angle of the adjustable stationary blade which can be driven.
When the deviation between the indirect measured value of the angle of the adjustable stator blade and the required value is still larger in fixed time (5 seconds), the accuracy of angle control on the adjustable stator blade is lower, and alarm shutdown processing can be carried out. Further, when it is determined that the accuracy of the angle control of the adjustable stator blade is low, the angle indirect measurement value or the difference between the angle indirect measurement value and the angle required value may be selectively used as reference data to improve the accuracy of the angle control of the adjustable stator blade.
In summary, the angle control method for the adjustable stator blade of the gas turbine provided by the embodiment of the invention at least has the following beneficial effects:
a linear variable differential sensor, a temperature sensor and a rotating speed sensor are arranged on a gas turbine to feed back sensor signals to a gas turbine controller, a rotating speed corrected value and a measured value of a actuating cylinder position are obtained through a preset multi-sensor monitoring value optimization logic, and a required value of the position of an adjustable stator blade, a current input of a torque motor, a required value of the actuating cylinder position and a current angle error of an adjustable stator blade are obtained through calculation respectively. The VSV deflection angle is adjusted, and the working stability of the air compressor is improved.
The problem that the working point of the gas compressor is not matched with the deflection angle of the VSV in the angle control process of the adjustable stator blade of the gas compressor of the existing gas turbine is solved;
the negative feedback control mechanism for the angle control of the adjustable stator blade is provided, the close matching and the self-adaptive control of the angle and the performance parameters of the gas turbine can be realized, and a stable, quick and accurate method is provided for VSV control.
Yet another embodiment of the present invention provides a system for controlling the angle of a variable stator blade of a gas turbine, referring to FIG. 4, the system 400 comprising: the parameter acquisition module 401 is used for acquiring parameters of the gas turbine through N groups of sensors, and obtaining a measurement reliable value of each parameter of the gas turbine according to a preset multi-sensor monitoring value optimization logic rule, wherein the parameters of the gas turbine comprise the rotating speed of the gas turbine, the inlet temperature of a gas compressor and the position value of an actuating cylinder, and N is more than or equal to 1; a rotating speed correction module 402, configured to obtain a corrected rotating speed of the gas turbine according to the reliable measurement value of the rotating speed of the gas turbine and the inlet temperature of the compressor; an adjustable stator blade angle requirement obtaining module 403, configured to obtain an angle requirement of the adjustable stator blade by using the corrected rotation speed of the gas turbine and a first preset rule; a required actuator cylinder position value obtaining module 404, configured to obtain a required actuator cylinder position value by using the required angle value of the adjustable stator blade and a second preset rule; the control angle module 405 is configured to obtain a driving current input value of a servo valve for controlling the hydraulic pump by using a deviation between a required value of the position of the actuator cylinder and a reliable value of the position measurement of the actuator cylinder, and the servo valve controls the opening of the hydraulic pump according to the current input value to provide hydraulic oil to the actuator cylinder, so that the actuator cylinder reaches a required position to drive the adjustable stator blade to act, and the angle of the adjustable stator blade is controlled; and a control accuracy judgment module 406, configured to obtain an indirect measurement value of the current adjustable stator blade angle by using the measurement reliability value of the actuator cylinder position and a third preset rule, and use the indirect measurement value of the current adjustable stator blade angle for accuracy of angle control of the adjustable stator blade.
Any number of the modules according to embodiments of the invention, or at least part of the functionality of any number thereof, may be implemented in one module. Any one or more of the modules according to the embodiments of the present invention may be implemented by being split into a plurality of modules. Any one or more of the modules according to embodiments of the present invention may be implemented at least in part as a hardware circuit, such as a Field Programmable Gate Array (FPGA), a Programmable Logic Array (PLA), a system on a chip, a system on a substrate, a system on a package, an Application Specific Integrated Circuit (ASIC), or may be implemented in any other reasonable manner of hardware or firmware by integrating or packaging circuits, or in any one of three implementations, or in any suitable combination of any of these. Alternatively, one or more of the modules according to embodiments of the invention may be implemented at least partly as computer program modules which, when executed, may perform corresponding functions.
Fig. 5 schematically shows a block diagram of an electronic device according to an embodiment of the invention.
As shown in fig. 5, the electronic device 500 includes a processor 501 and a memory 502. The electronic device 500 may perform a method according to an embodiment of the invention.
In particular, processor 501 may include, for example, a general purpose microprocessor, an instruction set processor and/or related chip set and/or a special purpose microprocessor (e.g., an Application Specific Integrated Circuit (ASIC)), and/or the like. The processor 501 may also include onboard memory for caching purposes. The processor 501 may be a single processing unit or a plurality of processing units for performing the different actions of the method flows according to embodiments of the present invention.
The memory 502, for example, can be any medium that can contain, store, communicate, propagate, or transport instructions. For example, a readable storage medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, device, or propagation medium. Specific examples of the readable storage medium include: magnetic storage devices, such as magnetic tape or Hard Disk Drives (HDDs); optical storage devices, such as compact disks (CD-ROMs); a memory, such as a Random Access Memory (RAM) or a flash memory; and/or wired/wireless communication links. Which stores a computer executable program which, when executed by the processor, causes the processor to perform the live-air tag adding method as described above.
The present invention also provides a computer-readable medium, which may be embodied in the apparatus/device/system described in the above embodiments; or may exist separately and not be assembled into the device/apparatus/system. The computer-readable medium carries one or more programs which, when executed, implement the method according to an embodiment of the invention.
According to embodiments of the present invention, a computer readable medium may be a computer readable signal medium or a computer readable storage medium or any combination of the two. A computer readable storage medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the foregoing. More specific examples of the computer readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the present invention, a computer readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. In the present invention, however, a computer readable signal medium may include a propagated data signal with computer readable program code embodied therein, for example, in baseband or as part of a carrier wave. Such a propagated data signal may take many forms, including, but not limited to, electro-magnetic, optical, or any suitable combination thereof. A computer readable signal medium may also be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wired, optical fiber cable, radio frequency signals, etc., or any suitable combination of the foregoing.
It will be appreciated by a person skilled in the art that various combinations and/or combinations of features described in the various embodiments and/or in the claims of the invention are possible, even if such combinations or combinations are not explicitly described in the invention. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present invention may be made without departing from the spirit or teaching of the invention. All such combinations and/or associations fall within the scope of the present invention.
While the invention has been shown and described with reference to certain exemplary embodiments thereof, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims and their equivalents. Accordingly, the scope of the present invention should not be limited to the above-described embodiments, but should be defined not only by the appended claims, but also by equivalents thereof.
Claims (10)
1. A method of controlling an angle of a variable stator vane of a gas turbine engine, the method comprising:
acquiring parameters of a gas turbine through N groups of sensors, and preferably logically obtaining a measurement reliable value of each gas turbine parameter according to preset multi-sensor monitoring values, wherein the gas turbine parameters comprise the rotating speed of the gas turbine, the inlet temperature of a gas compressor and the position of an actuating cylinder, and N is more than or equal to 1;
obtaining a corrected gas turbine rotating speed according to the gas turbine rotating speed and the reliable measurement value of the gas compressor inlet temperature;
obtaining an angle requirement value of the adjustable stator blade by using the corrected rotating speed of the gas turbine and a first preset rule;
obtaining a required value of the position of an actuating cylinder for driving the adjustable stator blade by utilizing the required value of the angle of the adjustable stator blade and a second preset rule;
obtaining a driving current input value of a servo valve for controlling a hydraulic pump by utilizing the deviation between the required value of the position of the actuating cylinder and the reliable value of the position measurement of the actuating cylinder, so that the servo valve controls the opening of the hydraulic pump according to the current input value, hydraulic oil is provided for the actuating cylinder, and the actuating cylinder reaches the required position, so that an adjustable stator blade is driven to act, and the angle of the adjustable stator blade is controlled;
and obtaining an indirect angle measurement value of the current adjustable stator blade by utilizing the position measurement reliable value of the actuating cylinder and a third preset rule, and judging the accuracy of angle control of the adjustable stator blade.
2. The control method of claim 1, wherein said N sets of sensors are 2 sets of sensors, and said reliable value of said gas turbine parameter is one of the following values:
the sensor system comprises a first sensor measurement value, a second sensor measurement value, an average of the first sensor measurement value and the second sensor measurement value, a maximum of the first sensor measurement value and the second sensor measurement value, a minimum of the first sensor measurement value and the second sensor measurement value, and a preset default value.
3. The control method of claim 1, wherein the corrected gas turbine speed is obtained by:
the corrected gas turbine speed is the corrected value of the square root of the gas turbine speed/the inlet temperature of the compressor.
4. Control method according to claim 1, characterized in that the first preset rule is an interpolation table of the rotational speed and the angle requirement value of the adjustable stator blade.
5. The control method according to claim 1, wherein the second preset rule is a table of interpolation of the corrected angle requirement of the adjustable stator vane and the actuator position requirement.
6. The control method of claim 5, wherein the corrected adjustable stator vane angle requirement value is obtained by:
the corrected adjustable stator vane angle requirement is the adjustable stator vane angle requirement x the adjustable stator vane zoom constant + the adjustable stator vane offset constant,
wherein the adjustable stator blade scaling constant is 0.0-5.0, and the adjustable stator blade deviation constant is-20.
7. The control method of claim 1, wherein the drive current input value is calculated by:
a drive current input value ═ proportional gain coefficient × (actuator position required value-measurement reliability of actuator position) + integral gain coefficient × (actuator position required value-measurement reliability of actuator position) dt;
the proportional gain coefficient and the integral gain coefficient are calibrated according to the action time of not more than 10 seconds from the maximum stator angle to the minimum stator angle, the proportional gain coefficient is between 0 and 20, and the integral gain coefficient is between 0 and 1.
8. An angle control system for adjustable stator vanes of a gas turbine engine, said control system comprising:
the parameter acquisition module is used for acquiring parameters of the gas turbines through N groups of sensors, and obtaining a measurement reliable value of each parameter of the gas turbines according to a preset multi-sensor monitoring value optimization logic rule, wherein the parameters of the gas turbines comprise the rotating speed of the gas turbines, the inlet temperature of the gas compressor and the position of the actuating cylinder, and N is more than or equal to 1:
the rotating speed correction module is used for obtaining the corrected rotating speed of the gas turbine according to the rotating speed of the gas turbine and the measured reliable value of the inlet temperature of the gas compressor;
the adjustable stator blade angle requirement value acquisition module is used for acquiring an angle requirement value of the adjustable stator blade by utilizing the corrected rotating speed of the gas turbine and a first preset rule;
the actuating cylinder position required value acquisition module is used for acquiring an actuating cylinder position required value for driving the adjustable stator blade by utilizing the angle required value of the adjustable stator blade and a second preset rule;
the control angle module is used for obtaining a driving current input value of a servo valve for controlling a hydraulic pump by utilizing the deviation between the required value of the position of the actuating cylinder and the reliable value of the position of the actuating cylinder, so that the servo valve controls the opening of the hydraulic pump according to the current input value, hydraulic oil is provided for the actuating cylinder, the actuating cylinder reaches the required position, and therefore the adjustable stator blade is driven to act, and the angle of the adjustable stator blade is controlled;
and the control accuracy judgment module is used for obtaining an angle indirect measurement value of the current adjustable stator blade by utilizing the position measurement reliable value of the actuating cylinder and a third preset rule and is used for controlling the angle of the adjustable stator blade.
9. An electronic device, characterized in that the device comprises:
a processor;
a memory storing a computer executable program which, when executed by the processor, causes the processor to implement the method of angle control of a gas turbine adjustable stator blade as claimed in claims 1-7.
10. A computer-readable storage medium, on which a computer program is stored, which program, when being executed by a processor, is adapted to carry out a method for controlling the angle of a variable stator vane of a gas turbine as claimed in claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210260923.5A CN114592973B (en) | 2022-03-16 | 2022-03-16 | Method, system, equipment and medium for controlling angle of adjustable stator blade of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210260923.5A CN114592973B (en) | 2022-03-16 | 2022-03-16 | Method, system, equipment and medium for controlling angle of adjustable stator blade of gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114592973A true CN114592973A (en) | 2022-06-07 |
| CN114592973B CN114592973B (en) | 2023-10-13 |
Family
ID=81817822
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210260923.5A Active CN114592973B (en) | 2022-03-16 | 2022-03-16 | Method, system, equipment and medium for controlling angle of adjustable stator blade of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114592973B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0882228A (en) * | 1994-07-14 | 1996-03-26 | Toshiba Corp | Variable guide vane control device for gas turbine |
| US20150308353A1 (en) * | 2014-04-25 | 2015-10-29 | Rolls-Royce Plc | Control of a gas turbine engine |
| CN111441994A (en) * | 2020-04-09 | 2020-07-24 | 中国航发沈阳发动机研究所 | Stator blade rotation angle adjusting and measuring structure and calibration method thereof |
| CN112128133A (en) * | 2020-11-25 | 2020-12-25 | 中国航发上海商用航空发动机制造有限责任公司 | Opening margin measurement test method for adjustable stationary blade of high-pressure gas compressor |
| CN113833694A (en) * | 2020-06-08 | 2021-12-24 | 中国航发商用航空发动机有限责任公司 | Control system and control method for adjustable stationary blade assembly of gas compressor, storage medium and test bench |
-
2022
- 2022-03-16 CN CN202210260923.5A patent/CN114592973B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0882228A (en) * | 1994-07-14 | 1996-03-26 | Toshiba Corp | Variable guide vane control device for gas turbine |
| US20150308353A1 (en) * | 2014-04-25 | 2015-10-29 | Rolls-Royce Plc | Control of a gas turbine engine |
| CN111441994A (en) * | 2020-04-09 | 2020-07-24 | 中国航发沈阳发动机研究所 | Stator blade rotation angle adjusting and measuring structure and calibration method thereof |
| CN113833694A (en) * | 2020-06-08 | 2021-12-24 | 中国航发商用航空发动机有限责任公司 | Control system and control method for adjustable stationary blade assembly of gas compressor, storage medium and test bench |
| CN112128133A (en) * | 2020-11-25 | 2020-12-25 | 中国航发上海商用航空发动机制造有限责任公司 | Opening margin measurement test method for adjustable stationary blade of high-pressure gas compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114592973B (en) | 2023-10-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7762084B2 (en) | System and method for controlling the working line position in a gas turbine engine compressor | |
| EP3892829B1 (en) | Modeling and control of gas cycle power plant operation with variant control profile | |
| US8311684B2 (en) | Output flow control in load compressor | |
| CA3024808A1 (en) | Torque signal dynamic compensation based on sensor location | |
| JP6812107B2 (en) | Compensation systems and methods for gas turbine proportional droop governors | |
| US9512784B2 (en) | Free gas turbine with constant temperature-corrected gas generator speed | |
| US10961921B2 (en) | Model-based control system and method for a turboprop engine | |
| EP2634396A2 (en) | Sensor-based performance-seeking gas turbine engine control | |
| US20130039736A1 (en) | Variable Stator Vane Control System | |
| EP3263907B1 (en) | Singular stator vane control | |
| CA2904309A1 (en) | Axial turbomachine compressor external casing with seal | |
| EP3385806A1 (en) | Control systems and methods for controlling power systems based on operational reliabilities and operational anomalies | |
| EP2808493A1 (en) | Two-shaft gas turbine | |
| CA3015288A1 (en) | Corrected parameters control logic for variable geometry mechanisms | |
| EP3567234B1 (en) | Method for controlling an inlet-adjustment mechanism for a turbocharger compressor | |
| US11773743B2 (en) | Model-based rotor speed keep out zone control | |
| CN114592973B (en) | Method, system, equipment and medium for controlling angle of adjustable stator blade of gas turbine | |
| RU2432562C2 (en) | Control method of gas-turbine unit technical condition | |
| Cruz-Manzo et al. | Performance analysis of a twin-shaft gas turbine with fault in the variable stator guide vane system of the axial compressor | |
| EP2743476B1 (en) | Turbine purge flow control system and related method of operations | |
| CN113294246B (en) | Method for controlling rotatable guide vanes of gas turbine | |
| RU2417326C2 (en) | Method of control over gas turbine engine | |
| RU2422657C1 (en) | Gas turbine electric power station control method | |
| RU2348824C2 (en) | Method for control of gas turbine engine | |
| Latimer et al. | Performance analysis of a twin-shaft gas turbine with fault in the variable stator guide vane system of the axial compressor |
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 |