CN108005795A - A kind of compressor inlet guide vane angle real-time control apparatus and method - Google Patents
A kind of compressor inlet guide vane angle real-time control apparatus and method Download PDFInfo
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- CN108005795A CN108005795A CN201711314723.9A CN201711314723A CN108005795A CN 108005795 A CN108005795 A CN 108005795A CN 201711314723 A CN201711314723 A CN 201711314723A CN 108005795 A CN108005795 A CN 108005795A
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- Prior art keywords
- guide vane
- compressor inlet
- vane angle
- inlet guide
- gas turbine
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Classifications
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- 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
Abstract
The present invention is not high and the problems such as real-time is poor to solve existing gas turbine or aero-engine compressor inlet guide vane angle control accuracy, there is provided a kind of compressor inlet guide vane angle real-time control apparatus and method.The device in gas turbine or aeroengine control system by increasing angular displacement sensor, guide vane adjusting mechanism, when compressor inlet vane apparatus works, measure guide vane angle value in real time by angular displacement sensor, give guide vane angle Real-time Feedback to gas turbine controller, gas turbine controller adjusts compressor inlet guide vane angle size, so as to change intake air flow in real time by controlling program, ensure the margin of operation of compressor, prevent surge.The device and method is with a wide range of applications.
Description
Technical field
The invention belongs to compressor field, relates generally to a kind of gas turbine or aero-engine compressor entry guide vane angle
The control device and method during high-precision real of degree, realizes that gas turbine inlet air mass flow controls in real time by this method.Specifically
For, it is proposed that a kind of compressor inlet guide vane angle real-time control apparatus and method.It mainly utilizes guide vane regulating system, angle
Displacement sensor and control system are spent to realize that compressor inlet guide vane angle controls in real time, so as to fulfill compressor inlet air
Flow is adjusted in real time.
Background technology
Gas turbine or aero-engine using the adjustable mode of compressor inlet guide vane come realize control compressor into
The purpose of mouth flow, but compressor inlet adjustable vane angle control at present is realized by mechanical-hydraulic regulative mode,
There are degree of regulation is low and the problems such as real-time is poor for this mode.
The content of the invention
The present invention is solves in gas turbine or aero-engine operational process due to adjustable vane angle control precision not
High, air flow control not in time, the problem of causing gas turbine or aero-engine that surge occurs, in order to improve compressor into
The real-time that mouth guide vane is adjusted, preferably plays the role of anti-asthma, and the present invention proposes one kind and controlled in real time by angular displacement sensor
The adjustable apparatus and method of compressor inlet guide vane processed, the device and method are primarily adapted for use in gas turbine or aero-engine etc.
In the real-time adjusting of power set entry guide vane, increase angle displacement transducer in gas turbine or aeroengine control system
Device, guide vane adjusting mechanism and corresponding program.When compressor inlet vane apparatus works, measured in real time by angular displacement sensor
Guide vane angle value, it is big to adjust compressor inlet angle by controlling program to controller, controller by guide vane angle Real-time Feedback
It is small, so as to change intake air flow, ensure the margin of operation of compressor, prevent surge.
The present invention is that technical solution is used by solving its technical problem：
A kind of compressor inlet guide vane angle real-time control apparatus, including it is arranged on the adjustable vane machine at compressor inlet
Structure, pressurized strut control unit and gas turbine controller, it is characterised in that
The adjustable guide vane mechanism nearby sets angular displacement sensor, the angular displacement sensor and gas turbine controller
Communication connection；
The pressurized strut control unit includes fuel tank, oil feed pump, solenoid directional control valve and pressurized strut, and the fuel tank passes through pipeline
Connected successively with the plunger pump, solenoid directional control valve and pressurized strut, the output terminal of the pressurized strut and the adjustable guide vane mechanism
Connection, the oil feed pump, solenoid directional control valve are communicated to connect with the gas turbine controller；
The angular displacement sensor passes through to measurement compressor inlet guide vane angle, the gas turbine controller in real time
Theoretical compressor inlet guide vane angle value relatively under the compressor inlet guide vane angle and design conditions of measurement in real time, judges real
Whether the compressor inlet guide vane angle run under the operating mode of border meets design requirement, passes through the electromagnetic switch if being unsatisfactory for
Valve and pressurized strut adjust the adjustable guide vane mechanism, until the compressor inlet guide vane angle that the angular displacement sensor is measured
Degree is equal with theoretical compressor inlet guide vane angle value.
Further, the gas turbine controller judges according to the compressor inlet guide vane angle of real-time relatively measurement
Whether this angle, if within surge margin, adjusts the guide vane adjusting mechanism and is stopped, will press within surge margin
The angle value of mechanism of qi import adjustable vane determines constant in the value, if not within surge margin, passes through the electromagnetic switch
Valve and pressurized strut adjust the adjustable guide vane mechanism, until compressor inlet adjustable vane angle value is within surge margin.
Preferably, in the pressurized strut control unit, the fuel tank passes sequentially through crude oil filter, manual switch valve and the confession
The oil inlet connection of oil pump, the oil outlet of the oil feed pump pass sequentially through the filter of high pressure essential oil, check valve, pressure-regulating valve with it is described
The oil inlet connection of solenoid directional control valve.
Further, pressure sensor, the pressure sensor and institute are set on the oil inlet pipe of the solenoid directional control valve
State the communication connection of gas turbine controller.
Further, overflow valve and pressure sensor are set in the oil outlet pipe of the oil feed pump, and the overflow valve overflows
Head piece is connected with the fuel tank, and the overflow valve and pressure sensor are communicated to connect with the gas turbine controller.
According to another aspect of the present invention, present invention also offers a kind of above-mentioned compressor inlet guide vane using the present invention
Angle real-time control apparatus carries out the method that compressor inlet guide vane angle controls in real time, it is characterised in that the control method
Comprise the following steps：
SS1. after gas turbine or aero-engine assign initiation command, starter starts and gas turbine controller
Work, makes gas turbine or aero-engine in running order；
SS2. start the combustion chamber fuel feeding to gas turbine or aero-engine, and calculated by oil inlet uninterrupted
Compressor inlet guide vane angle value under design point operating mode；
SS3. inlet guide vane angle is adjusted by solenoid directional control valve and pressurized strut, with gas turbine or aero-engine
Rotating speed constantly rise, measure compressor inlet guide vane angle in real time by angular displacement sensor；
SS4. the compressor inlet guide vane angle and flow rate calculation measured by angular displacement sensor comes out theoretic
Whether the contrast of inlet guide vane angle, the compressor inlet guide vane angle for judging to run under actual condition meet design requirement, no
Satisfaction then continues through solenoid directional control valve and pressurized strut adjusts compressor inlet guide vane angle, until angular displacement sensor is measured
Come compressor inlet guide vane angle with setting compressor inlet guide vane angle value it is equal, then meet whole gas turbine or
The demand of compressor air inlet machine flow under person's aeroengine operation status.
Further, to prevent the gas turbine or aero-engine from surge occurs, the control method further includes
Following steps：
SS5. the compressor inlet guide vane angle value measured according to angular displacement sensor judges whether this angle is abundant in surge
Within degree, if within surge margin, guide vane adjusting mechanism is stopped, and compressor inlet guide vane angle value is determined at this
Be worth it is constant, if not within surge margin, guide vane adjusting mechanism work, change compressor inlet adjustable vane angle value,
Until compressor inlet guide vane angle value within surge margin, then completes the target of anti-asthma, guide vane adjusting mechanism is stopped.
Compared with the existing technology, compressor inlet adjustable vane angle real-time control apparatus of the invention and method, have
Significant technique effect：By increasing angular displacement sensor in gas turbine or aeroengine control system, guide vane is adjusted
Mechanism and program is accordingly controlled, when compressor inlet vane apparatus works, measure guide vane angle in real time by angular displacement sensor
Angle value, by guide vane angle Real-time Feedback to controller, controller adjusts compressor inlet angular dimension by controlling program, from
And change intake air flow, ensure the margin of operation of compressor, prevent surge.
Brief description of the drawings
Fig. 1 is the compressor inlet guide vane angle real-time control apparatus of the present invention；
The real-time control flow chart of Fig. 2 compressor inlet guide vane angles；
Fig. 3 compressor inlet guide vane angle anti-asthma control flow charts.
Embodiment
For the objects, technical solutions and advantages of the present invention are more clearly understood, develop simultaneously embodiment referring to the drawings, right
The present invention is further described.It should be noted that as described below is only presently preferred embodiments of the present invention, therefore do not limit
Determine protection scope of the present invention.
As shown in Figure 1, the compressor inlet guide vane angle real-time control apparatus of the present invention, including pressurized strut control unit,
Compressor adjustable vane control unit and gas turbine or aero-engine critical piece unit.
Pressurized strut control unit, it is acted on mainly is transformed into fuel injection pressure signal, including oil by the electric signal in control system
Case 18, crude oil filter 26, manual switch valve 25, plunger pump 24, high pressure essential oil filter 20, check valve 19, pressure-regulating valve 17, electromagnetism change
To valve 16, pressurized strut 14, fuel tank 18 is filtered with crude oil filter 26, manual switch valve 25, plunger pump 24, high pressure essential oil successively by pipeline
20th, check valve 19, pressure-regulating valve 17, solenoid directional control valve 16, pressurized strut 14 connect, output terminal and the compressor 3 of pressurized strut 14
The adjustable guide vane mechanism 4 of entrance connects, and pressure sensor 15, pressure sensor are set on the oil inlet pipe of solenoid directional control valve 16
15th, solenoid directional control valve 16 is communicated to connect with gas turbine controller 11.
Specifically, it is for whole system that fuel tank 18, which is connected with crude oil filter 26, liquid level gauge 27 and overflow valve 23, its main function,
Hydraulic oil is provided.Crude oil filters 26 one end then fuel tank 18, and then manual switch valve 25, its main function are that elimination fuel oil is miscellaneous for one end
Matter.The then crude oil filter 26 of 25 one end of manual switch valve, then plunger pump 24, its effect are the works for controlling whole unit manually for one end
Make state.24 one end of plunger pump is ined succession manual switch valve 25, and one end is ined succession high pressure essential oil filter 20, its effect is carried for whole unit
Motor is controlled for power, and by gas turbine controller 11, so that it is the oil pressure that whole system provides to control plunger pump 24
Size.High pressure essential oil filters 20 one end and ins succession plunger pump 24, and one end is ined succession check valve 19, its act on be complete by plunger pump 24 it
High pressure oil filtering afterwards.19 one end of check valve is ined succession high pressure essential oil filter 20, and one end is ined succession pressure-regulating valve 17, its effect is unidirectional
Circulation, prevents hydraulic oil from flowing back.17 one end of pressure-regulating valve is ined succession check valve 19, and one end is ined succession solenoid directional control valve 16, it is acted on
It is to adjust hydraulic fluid pressure.16 one end of solenoid directional control valve is ined succession pressure-regulating valve 17, and one end is ined succession pressurized strut 14, its effect is to change
Become oil pressure direction, control the oil inlet direction of pressurized strut 14.14 one end of pressurized strut is ined succession solenoid directional control valve 16, and one end is ined succession adjustable lead
Leaf mechanism 4, it is to adjust inlet guide vane angle that it, which is acted on, controls the change of adjustable vane angle.In the pressurized strut unit, electromagnetism
The motor of pressure sensor 15 and 21 and plunger pump 24 is connected on gas turbine controller 11 at reversal valve 16, two, to
Upper transmission receives electric signal.And the liquid level gauge 27 that fuel tank 18 connects, its one end are ined succession fuel tank 18, one end is ined succession gas turbine
Controller 11, it is the real-time liquid level height value for measuring fuel tank that it, which is acted on,.The overflow valve 23 of fuel tank connection, one end are ined succession fuel tank 18,
One end is ined succession pressure gauge 22, its effect is that oil pressure is excessive after solving the problems, such as plunger pump 24.22 one end of pressure gauge is ined succession overflow valve, and one
Pressure sensor 21 of ining succession is held, it is to show the oil pressure value that high pressure essential oil is filtered before 20 that it, which is acted on,.21 one end of pressure sensor connects
Pressure gauge, one end is ined succession gas turbine controller 11, it is acted on be measurement high pressure essential oil filter 20 before oil pressure value.Hydraulic oil exists
Into before solenoid directional control valve 16, pressure sensor 15 is connected with, measures the pressure before solenoid directional control valve 16, and pressure value is transmitted
To gas turbine controller 11.Gas turbine controller 11 further with host computer 12,13 communication link of condition monitoring display device
Connect.
Compressor adjustable vane control unit, its effect is to realize that compressor adjustable vane angle controls in real time, including can
Adjust guide vane mechanism 4 and angular displacement sensor 10, wherein adjustable guide vane mechanism 4 is on compressor 3 and in succession pressurized strut 14 and angle position
Displacement sensor 10, it is adjustment guide vane angle value that it, which is acted on,.10 one end of angular displacement sensor is ined succession adjustable guide vane mechanism 4, and one end connects
Gas turbine controller 11, it is real-time measurement adjustable vane angle value that it, which is acted on, and result is fed back to gas turbine control
Device 11.The one end in this unit of gas turbine controller 11 is ined succession angular displacement sensor 10, and one end is ined succession solenoid directional control valve 16,
It is that the received adjustable vane angle value of docking carries out processing judgement that it, which is acted on, and the result electric signal after processing is passed to electromagnetism
Reversal valve 16.16 one end of solenoid directional control valve is ined succession gas turbine controller 11, and one end is ined succession pressurized strut 14, it is acted on combustion gas wheel
The electric signal that machine controller 11 transmits is converted into fuel injection pressure signal, is transmitted to pressurized strut 14, is then transmitted to adjustable guide vane mechanism 4.
Gas turbine critical piece unit, it is the conversion for completing chemical energy and kinetic energy that it, which is acted on, realizes the output of power.Can
4 one end of guide vane mechanism is adjusted in succession starter 1, one end is ined succession compressor 3, and it is size by controlling guide vane angle that it, which is acted on, is changed
Become intake air flow.3 one end of compressor is ined succession adjustable guide vane mechanism 4, and one end is ined succession combustion chamber 5, its act on be by air into
Row compression, improves the air pressure into combustion chamber.5 one end of combustion chamber is ined succession compressor 3, and one end is ined succession turbine 7, its effect is
Fuel combustion, thermal energy is converted into by chemical energy.Turbine 7 is ined succession combustion chamber and compressor, and it is the height for coming out combustion chamber that it, which is acted on,
Portion of energy in warm high-pressure gas is converted into kinetic energy, promotes compressor operating.Power turbine 8 is ined succession load 9, its act on be by
The high temperature and high pressure gas that combustion chamber comes out change into mechanical energy and do work to load.Gas turbine controller 11 is ined succession angle displacement transducer
Device 10 and speed measuring device 6, its effect is that the working status of whole gas turbine is regulated and controled according to the rotating speed of gas turbine.
As shown in Fig. 2, using the present invention compressor inlet guide vane angle real-time control apparatus, in real time control compressor into
The flow of mouthful guide vane angle is：
Step1:After gas turbine or aero-engine assign initiation command, starter starts and combustion engine controller work
Make, make gas turbine or aero-engine in running order；
Step2:Start to give combustion chamber fuel feeding, and the guide vane angle under design point operating mode is calculated by inlet flow rate size
Value；
Step3:Inlet guide vane angle is adjusted by solenoid directional control valve and pressurized strut, with gas turbine or aeroplane engine
The rotating speed of machine constantly rises, and measures compressor inlet guide vane angle in real time by angular displacement sensor.
Step4:The theoretic import that the inlet guide vane angle and flow rate calculation measured by angular displacement sensor comes out
Whether the contrast of guide vane angle, the guide vane angle for judging to run under actual condition meet design requirement, are unsatisfactory for, continue through
Solenoid directional control valve and pressurized strut adjust inlet guide vane angle, until the inlet guide vane angle that angular displacement sensor is measured is with setting
Fixed inlet guide vane angle value is equal, then meet compressor under whole gas turbine or aeroengine operation status into
The demand of throughput.
As shown in figure 3, using the compressor inlet guide vane angle real-time control apparatus of the present invention, angular displacement sensor is utilized
The control flow for playing anti-asthma is：
Step1:The auxiliary system of gas turbine will power so that control system can work normally；
Step2:After angular displacement sensor normal work, the angle of compressor adjustable vane is measured, can according to what is measured
The angle value of guide vane is adjusted to judge this angle whether within surge margin, if within surge margin, guide vane adjusting mechanism stops
Only work, the angle value of compressor inlet adjustable vane is determined it is constant in the value, if not within surge margin, guide vane tune
Mechanism work is saved, changes the angle value of compressor inlet adjustable vane；
Step3:Guide vane angle is remeasured using angular displacement sensor, whether it is judged according to the guide vane angle value measured
Within surge margin, this flow is repeated, until compressor inlet adjustable vane angle value within surge margin, is then completed anti-
The target of asthma, is oriented to adjusting mechanism and is stopped.
The basic principles, main features and advantages of the invention have been shown and described above.The technical staff of the industry should
Understand, the present invention is not limited to the above embodiments, and the above embodiments and description only describe the original of the present invention
Reason, without departing from the spirit and scope of the present invention, various changes and modifications of the present invention are possible, these changes and improvements
It all fall within the protetion scope of the claimed invention.The claimed scope of the invention is by appended claims and its equivalent circle
It is fixed.
Claims (7)
1. a kind of compressor inlet guide vane angle real-time control apparatus, including it is arranged on the adjustable vane machine at compressor inlet
Structure, pressurized strut control unit and gas turbine controller, it is characterised in that
The adjustable guide vane mechanism nearby sets angular displacement sensor, and the angular displacement sensor communicates with gas turbine controller
Connection；
The pressurized strut control unit includes fuel tank, oil feed pump, solenoid directional control valve and pressurized strut, the fuel tank by pipeline successively
Being connected with the plunger pump, solenoid directional control valve and pressurized strut, the output terminal of the pressurized strut is connected with the adjustable guide vane mechanism,
The oil feed pump, solenoid directional control valve are communicated to connect with the gas turbine controller；
To measurement compressor inlet guide vane angle in real time, the gas turbine controller passes through real-time the angular displacement sensor
Compare the theoretical compressor inlet guide vane angle value under the compressor inlet guide vane angle and design conditions of measurement, judge actual work
Whether the compressor inlet guide vane angle run under condition meets design requirement, if being unsatisfactory for by the solenoid directional control valve and
Pressurized strut adjusts the adjustable guide vane mechanism, until the compressor inlet guide vane angle measured of the angular displacement sensor with
Theoretical compressor inlet guide vane angle value is equal.
2. the compressor inlet guide vane angle real-time control apparatus according to the claims, it is characterised in that the combustion
Turbine machine controller according to the compressor inlet guide vane angle of real-time relatively measurement, judge this angle whether surge margin with
It is interior, if within surge margin, adjust the guide vane adjusting mechanism and be stopped, by the angle of compressor inlet adjustable vane
Value determines constant in the value, if not within surge margin, is adjusted by the solenoid directional control valve and pressurized strut described adjustable
Guide vane mechanism, until compressor inlet adjustable vane angle value is within surge margin.
3. the compressor inlet guide vane angle real-time control apparatus according to the claims, it is characterised in that the work
In dynamic cylinder control unit, the fuel tank passes sequentially through crude oil filter, manual switch valve is connected with the oil inlet of the oil feed pump, described
The oil outlet of oil feed pump passes sequentially through the filter of high pressure essential oil, check valve, the oil inlet company of pressure-regulating valve and the solenoid directional control valve
It is logical.
4. the compressor inlet guide vane angle real-time control apparatus according to the claims, it is characterised in that the electricity
Pressure sensor, the pressure sensor and the gas turbine controller communication link are set on the oil inlet pipe of magnetic reversal valve
Connect.
5. the compressor inlet guide vane angle real-time control apparatus according to the claims, it is characterised in that the confession
Overflow valve and pressure sensor are set in the oil outlet pipe of oil pump, and the overflow port of the overflow valve is connected with the fuel tank, described
Overflow valve and pressure sensor are communicated to connect with the gas turbine controller.
6. a kind of compressor inlet guide vane angle real-time control apparatus using described in the claims carries out compressor inlet
The method that guide vane angle controls in real time, it is characterised in that the control method comprises the following steps：
SS1. after gas turbine or aero-engine assign initiation command, starter starts and gas turbine controller work
Make, make gas turbine or aero-engine in running order；
SS2. start the combustion chamber fuel feeding to gas turbine or aero-engine, and design is calculated by oil inlet uninterrupted
Compressor inlet guide vane angle value under point operating mode；
SS3. inlet guide vane angle is adjusted by solenoid directional control valve and pressurized strut, with gas turbine or turn of aero-engine
It is fast constantly to rise, measure compressor inlet guide vane angle in real time by angular displacement sensor；
SS4. the theoretic import that the compressor inlet guide vane angle and flow rate calculation measured by angular displacement sensor comes out
Whether the contrast of guide vane angle, the compressor inlet guide vane angle for judging to run under actual condition meet design requirement, are unsatisfactory for
Then continue through solenoid directional control valve and pressurized strut adjusts compressor inlet guide vane angle, until what angular displacement sensor was measured
Compressor inlet guide vane angle is equal with the compressor inlet guide vane angle value set, then meets whole gas turbine or boat
The demand of compressor air inlet machine flow under empty engine behavior.
7. according to the method described in claim 6, it is characterized in that, to prevent the gas turbine or aero-engine from occurring
Surge, the control method are further comprising the steps of：
SS5. the compressor inlet guide vane angle value measured according to angular displacement sensor judge this angle whether surge margin with
Interior, if within surge margin, guide vane adjusting mechanism is stopped, and compressor inlet guide vane angle value is determined in the value not
Become, if not within surge margin, the work of guide vane adjusting mechanism, the angle value of change compressor inlet adjustable vane, until
Compressor inlet guide vane angle value then completes the target of anti-asthma within surge margin, and guide vane adjusting mechanism is stopped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201711314723.9A CN108005795B (en) | 2017-12-12 | 2017-12-12 | Device and method for controlling angle of inlet guide vane of air compressor in real time |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711314723.9A CN108005795B (en) | 2017-12-12 | 2017-12-12 | Device and method for controlling angle of inlet guide vane of air compressor in real time |
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| CN108005795B CN108005795B (en) | 2023-07-21 |
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| CN109356726A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | The control method of aero-engine coaxial compressor machine adjustable vane |
| CN109372588A (en) * | 2018-09-30 | 2019-02-22 | 上海科梁信息工程股份有限公司 | Adjustable vane scaling method, device, system and computer readable storage medium |
| CN110195715A (en) * | 2019-04-19 | 2019-09-03 | 中国神华能源股份有限公司 | Control method, device and the mechanical equipment of the adjustable vane of mechanical equipment |
| CN113294246A (en) * | 2021-06-30 | 2021-08-24 | 中国航发动力股份有限公司 | Method for controlling rotatable guide vanes of gas turbine |
| CN113700676A (en) * | 2021-07-27 | 2021-11-26 | 中国科学院工程热物理研究所 | Self-air-entraining control gas turbine compressor guide vane adjusting and driving mechanism |
| CN114183252A (en) * | 2021-12-13 | 2022-03-15 | 中国船舶重工集团公司第七0三研究所 | Main actuating cylinder of rotatable guide vane rotating mechanism of gas turbine |
| CN114278611A (en) * | 2022-01-06 | 2022-04-05 | 重庆江增船舶重工有限公司 | Adjustable guide vane structure of turbocharger compressor and control method |
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| CN109372588A (en) * | 2018-09-30 | 2019-02-22 | 上海科梁信息工程股份有限公司 | Adjustable vane scaling method, device, system and computer readable storage medium |
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| CN109356726B (en) * | 2018-12-14 | 2019-09-13 | 中国航发沈阳发动机研究所 | The control method of aero-engine coaxial compressor machine adjustable vane |
| CN110195715A (en) * | 2019-04-19 | 2019-09-03 | 中国神华能源股份有限公司 | Control method, device and the mechanical equipment of the adjustable vane of mechanical equipment |
| CN113294246B (en) * | 2021-06-30 | 2022-11-04 | 中国航发动力股份有限公司 | Method for controlling rotatable guide vanes of gas turbine |
| CN113294246A (en) * | 2021-06-30 | 2021-08-24 | 中国航发动力股份有限公司 | Method for controlling rotatable guide vanes of gas turbine |
| CN113700676A (en) * | 2021-07-27 | 2021-11-26 | 中国科学院工程热物理研究所 | Self-air-entraining control gas turbine compressor guide vane adjusting and driving mechanism |
| CN113700676B (en) * | 2021-07-27 | 2023-05-16 | 中国科学院工程热物理研究所 | Self-bleed air control guide vane adjusting driving mechanism of gas turbine compressor |
| CN114183252A (en) * | 2021-12-13 | 2022-03-15 | 中国船舶重工集团公司第七0三研究所 | Main actuating cylinder of rotatable guide vane rotating mechanism of gas turbine |
| CN114183252B (en) * | 2021-12-13 | 2023-09-12 | 中国船舶重工集团公司第七0三研究所 | Main actuator cylinder of rotary guide vane rotating mechanism of gas turbine |
| CN114278611A (en) * | 2022-01-06 | 2022-04-05 | 重庆江增船舶重工有限公司 | Adjustable guide vane structure of turbocharger compressor and control method |
| CN115014791A (en) * | 2022-06-23 | 2022-09-06 | 南京航空航天大学 | Stationary blade angle adjusting and calibrating method for aero-engine compression component test and angular displacement sensor mounting method |
| CN115014791B (en) * | 2022-06-23 | 2023-03-31 | 南京航空航天大学 | Stationary blade angle adjusting and calibrating method for aero-engine compression component test and angular displacement sensor mounting method |
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