CN108223140A - A kind of three shaft gas turbine power turbine control of inlet guide vanes rule optimization method - Google Patents
A kind of three shaft gas turbine power turbine control of inlet guide vanes rule optimization method Download PDFInfo
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- CN108223140A CN108223140A CN201711274553.6A CN201711274553A CN108223140A CN 108223140 A CN108223140 A CN 108223140A CN 201711274553 A CN201711274553 A CN 201711274553A CN 108223140 A CN108223140 A CN 108223140A
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- power turbine
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- gas turbine
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- guide vane
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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
- F02C9/22—Control of working fluid flow by throttling; by adjusting vanes by adjusting turbine vanes
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- 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
- F05D2260/00—Function
- F05D2260/81—Modelling or simulation
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- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- Mechanical Engineering (AREA)
- Fluid Mechanics (AREA)
- Computer Hardware Design (AREA)
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- General Physics & Mathematics (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of change geometry three shaft gas turbine power turbine control of inlet guide vanes rule optimization methods, by establishing high-precision simulation model to the adjustable three shaft gas turbine of power turbine entry guide vane, it carries out simulation calculation under different atmospheric environments, loading condition, operating condition to gas turbine, finds combustion chamber overtemperature, compressor into asthma, low-pressure shaft excess revolutions boundary line.On this basis, optimal power turbine inlet guide vane angle under each operating mode is found according to result of calculation, using RBF neural fitting data, completes the formulation of optimal power turbine control of inlet guide vanes rule.Finally, established optimal power turbine control of inlet guide vanes rule is substituted into the reasonability of access control rule in Gas Turbine Simulation model.Optimal power turbine control of inlet guide vanes rule proposed by the present invention can allow gas turbine to be run safe efficiently under each operating mode, reduce gas turbine fuel consumption rate.
Description
Technical field
The present invention relates to gas turbine field, more particularly, to a kind of change geometry three shaft gas turbine power turbine
The optimization method of control of inlet guide vanes rule.
Background technology
Variable-geometry gas turbine has preferable mobility and Study on Variable Condition Features, how to optimize its control law, makes it
Efficiency reaches maximum value under different operating modes, atmospheric environment, loading condition, plays its performance to the maximum extent with important meaning
Justice.However, both at home and abroad in terms of variable-geometry gas turbine control law optimization, compressor inlet wicket gate control rule optimizing is ground
Study carefully more；In terms of variable geometry turbine gas turbine research, research emphasis is focused primarily upon on variable geometry turbine characteristics of components, and
Research in terms of its overall performance and control law is not carried out in a deep going way.Since the type gas turbine structure is complicated, limit
Amount processed is more, and control variable not only has fuel flow to also have power turbine inlet guide vane angle, the optimization of wicket gate control rule
Difficulty is larger.
Invention content
The present invention provides a kind of change geometry three shaft gas turbine power turbine to solve more than the deficiencies in the prior art
Wicket gate control rule optimization method, this method are right by establishing high-precision simulation model to becoming geometry three shaft gas turbine
Gas turbine difference atmospheric environment, loading condition, working condition carry out simulation calculation.Explore power turbine inlet guide vane angle pair
The affecting laws of gas turbine operating mode establish combustion chamber overtemperature, compressor into asthma, low-pressure shaft excess revolutions boundary line, in boundary line
Each operating mode is found out to order the highest power turbine inlet guide vane angle of gas turbine proficiency.Later, it is trained using RBF neural
Data, it is established that become geometry three shaft gas turbine different operating condition and optimal power turbine inlet guide vane angle under the operating mode
Between correspondence, complete power turbine control of inlet guide vanes rule optimization.
For realization more than goal of the invention, the technical solution adopted by the present invention is：
A kind of change geometry three shaft gas turbine power turbine control of inlet guide vanes rule optimization method, the change geometry three
Shaft type gas turbine includes gas generator and power turbine, and the inlet guide vane angle of the power turbine is adjustable, and feature exists
In the control law optimization method includes the following steps：
SS1. it is established by known characteristics of components and detailed engine operation data and becomes geometry three shaft gas turbine
High Precision Simulation model；
SS2. it is calculated under different atmospheric environments, loading condition, combustion engine operating mode using the simulation model that step SS1 is established, no
With the working condition of power turbine guide vane angle gas turbine, analysis power turbine inlet guide vane angle is to gas turbine work shape
The affecting laws of condition；
Specifically, by calculating analysis it is found that power turbine entry guide vane progressively closes off, angle reduces, power turbine
Negotiability reduces therewith, and gas turbine inlet flow-reduction, compressor operatlng polnt is close to surge line, meanwhile, inlet flow rate
Reduction oil-gas ratio is caused to rise, combustor exit temperature rises therewith.If power turbine entry guide vane is gradually opened, angle
Increase, power turbine negotiability increase therewith, and power turbine expansion ratio reduces, and low-pressure turbine expansion ratio rises, ability of doing work
Enhancing, low pressure rotating speed rise.To sum up, power turbine inlet guide vane angle is too small, and gas turbine has into asthma, the danger of overtemperature,
And excessive power turbine inlet guide vane angle may result in low-pressure shaft excess revolutions.Under low operating mode, combustion chamber goes out gas turbine
Mouth temperature is relatively low, at this point, smaller power turbine inlet guide vane angle can improve combustor exit temperature, is conducive to promote combustion
The gas-turbine thermal efficiency.When gas turbine is operated in higher operating mode, larger power turbine inlet guide vane angle can improve low
Last item rotating speed so that low-pressure turbine and low-pressure compressor are operated in higher efficiency area, are conducive to carrying for gas turbine overall efficiency
It is high.
SS3. it screens out and enables gas turbine overtemperature, excess revolutions or the power turbine inlet guide vane angle into asthma, find out remaining order
The highest power turbine inlet guide vane angle of gas turbine efficiency under different atmospheric environments, loading condition, working condition；
SS4. using atmospheric temperature T0, atmospheric pressure P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed NH to be defeated
Enter parameter, optimal power turbine inlet guide vane angle VGVbFor output parameter, using RBF neural training data, ginseng is completed
Optimal power turbine control of inlet guide vanes rule is established in several fittings；
Wherein, RBF neural can utilize existing algorithm, such as the RBF neural built in MATLAB/SIMULINK
Tool box, neural network play the role of a kind of multidimensional fitting, input parameter and output parameter are set up using it herein
Between correspondence, such as the corresponding optimal power turbine inlet guide vane angle mapping relations of gas turbine working condition can
It is expressed as：VGVb=f (T0, P0, NPT, NH).
SS5. established optimal power turbine control of inlet guide vanes rule is substituted into Gas Turbine Simulation model and carried out
Verification.
Preferably, the Gas Turbine Simulation model established by step SS1 calculates different atmospheric temperature T0, atmospheric pressure
It is fired in the case of P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed NH and power turbine inlet guide vane angle VGV
Gas-turbine working condition, analysis power turbine inlet guide vane angle is to the affecting laws of gas turbine working condition.
Preferably, according to result of calculation, high-pressure turbine overtemperature, compressor surge, low-pressure shaft excess revolutions boundary line are formulated successively,
Different operating modes are found out in the range of boundary line to order the highest power turbine inlet guide vane angle VGV of the combustion engine thermal efficiencybValue.
Preferably, can stablize for guarantee gas turbine, Effec-tive Function, with atmospheric temperature T0, atmospheric pressure P0, power whirlpool
It is input parameter to take turns relative rotation speed NPT, high-pressure shaft relative rotation speed NH, with the optimal power turbine inlet guide vane angle calculated
VGVbIt for output parameter, is trained using RBF neural, completes the fitting of parameter, established optimal power turbine import and lead
Leaf control law.
Preferably, the optimal power turbine control of inlet guide vanes rule built up is combined imitative with gas turbine Dynamic Simulation Model
Very, using trained RBF neural, pass through atmospheric temperature T0, atmospheric pressure P0, power turbine relative rotation speed NPT, high pressure
Axis relative rotation speed NH calculates power turbine inlet guide vane angle VGV values, and can verification gas turbine under this wicket gate control rule
Stablize, Effec-tive Function.
Preferably, in step SS3, by the result of calculation of SS2 can obtain combustion chamber overtemperature, compressor into asthma, low pressure
Axis excess revolutions boundary line finds out the power turbine inlet guide vane angle corresponding to each operating mode in boundary line, enables gas turbine thermal effect
Rate highest.
Preferably, in step SS4, gas turbine includes two controls of fuel flow Wf and power turbine guide vane angle VGV
Variable processed forms closed-loop control to power turbine relative rotation speed NPT by fuel flow Wf and is exported come Indirect method gas turbine
Power, the atmospheric temperature T0 measured by sensor, atmospheric pressure P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed
NH parameters input trained RBF neural can calculate optimal power turbine inlet guide vane angle VGV in real timeb, so as to complete
Optimal control to power turbine inlet guide vane angle.
Preferably, in step SS5, neural network trained in step SS4 is substituted into gas turbine control system dynamic
Associative simulation is carried out in simulation model, you can verify the effect of optimization and reliability of the control law.
Compared with prior art, the beneficial effects of the invention are as follows：
Change geometry three shaft gas turbine power turbine wicket gate control rule optimization method proposed by the present invention, by dynamic
The adjustable three shaft gas turbine of power turbine inlet guide vane establishes high-precision simulation model, to gas turbine in different big compression rings
It carries out simulation calculation under border, loading condition, operating condition, finds combustion chamber overtemperature, compressor into asthma, low-pressure shaft excess revolutions boundary
Line.On this basis, optimal power turbine inlet guide vane angle under each operating mode is found according to result of calculation, utilizes RBF nerve nets
Network fitting data completes the formulation of optimal power turbine control of inlet guide vanes rule.Finally, by established optimal power turbine
Control of inlet guide vanes rule substitutes into the reasonability of access control rule in Gas Turbine Simulation model.It is proposed by the present invention optimal to lead
Leaf control law can allow gas turbine to be run safe efficiently under each operating mode, reduce gas turbine fuel consumption rate.
Description of the drawings
Fig. 1 is change geometry three shaft gas turbine power turbine control of inlet guide vanes rule optimization method provided by the invention
Flow chart.
Fig. 2 is the optimal power turbine control of inlet guide vanes rule schematic diagram that the present invention establishes.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention more comprehensible, develop simultaneously embodiment referring to the drawings, right
The present invention is further described, and so that the advantages and features of the present invention can be more easily understood by those skilled in the art.It needs
Illustrate, as described below is only presently preferred embodiments of the present invention, is not intended to limit the scope of the present invention.It is practical
On, in the case of without departing from the scope or spirit of the invention, it can carry out various modifications and change in the present invention, this is to this
It will be apparent for field technology personnel.For example, the feature that the part as one embodiment shows or describes can
To be used together to generate another embodiment with another embodiment.It is therefore, it is intended that of the invention by such modification and change
Change is included in the range of appended claims and their equivalent.
Below in conjunction with drawings and examples, the present invention is further elaborated.
As shown in Figure 1, change geometry three shaft gas turbine power turbine control of inlet guide vanes rule provided by the invention is excellent
Change method includes the following steps：
SS1. gas turbine High Precision Simulation mould is established by known characteristics of components and detailed engine operation data
Type；
SS2. it is calculated under different atmospheric environments, loading condition, combustion engine operating mode using the simulation model that step SS1 is established, no
With the working condition of power turbine inlet guide vane angle gas turbine, analysis power turbine inlet guide vane angle is to gas turbine work
Make the affecting laws of situation；Gas turbine steady state condition is codetermined by external parameter and state variable.External parameter has：Air
Environment (import stagnation pressure P0, import total temperature T0) and load characteristic (related with power turbine relative rotation speed NPT), state variable
Have：High-pressure shaft relative rotation speed NH and power turbine inlet guide vane angle VGV amount to 5 variables.Power turbine entry guide vane control
The selected of rule processed seeks to determine the best guide vane angle of power turbine under different P0, T0, the combination of NPT and NH.T0 takes
233.15K, 258.15K, 288.15K, 308.15K, 323.15K amount to 5 parameters, P0 take 0.87bar, 0.94bar,
1.013bar, 1.05bar, 1.08bar amount to 5 parameters, and NPT uniformly chooses 8 parameters in the range of 1.1 to 0.4, and NH exists
8 parameters are uniformly chosen in the range of 0.7 to 1.0, VGV uniformly chooses 50 points in the range of 20 ° to 40 °, therefore need to calculate 5 altogether ×
Under 5 × 8 × 8 × 50=80000 kind operating modes, the working condition of gas turbine.
By result of calculation it is found that power turbine entry guide vane progressively closes off, angle reduce, power turbine negotiability with
Reduction, gas turbine inlet flow-reduction, compressor operatlng polnt is close to surge line, meanwhile, the reduction of inlet flow rate causes
Oil-gas ratio rises, and combustor exit temperature rises therewith.If power turbine entry guide vane is gradually opened, angle increase, power
Turbine negotiability increases therewith, and power turbine expansion ratio reduces, and low-pressure turbine expansion ratio rises, acting ability enhancing, low pressure
Rotating speed rises.To sum up, power turbine inlet guide vane angle is too small, and gas turbine has into asthma, the danger of overtemperature, and excessive dynamic
Power turbine inlet guide vane angle may result in low-pressure shaft excess revolutions.For gas turbine under low operating mode, combustor exit temperature is relatively low,
At this point, smaller power turbine inlet guide vane angle can improve combustor exit temperature, be conducive to promote gas turbine thermal effect
Rate.When gas turbine is operated in higher operating mode, larger power turbine inlet guide vane angle can improve low pressure rotating speed, make
It obtains low-pressure turbine and low-pressure compressor is operated in higher efficiency area, be conducive to the raising of gas turbine overall efficiency.
SS3. it screens out and enables gas turbine overtemperature, excess revolutions or the power turbine inlet guide vane angle into asthma, find out remaining order
Gas turbine highest power turbine of efficiency under different atmospheric environments (T0, P0), loading condition (NPT), working condition (NH)
Inlet guide vane angle (VGVb)；
It is analyzed by the calculating of SS2, combustion chamber overtemperature, compressor can be formulated into asthma, low-pressure shaft excess revolutions boundary line, screened
Fall to enable the operating mode of combustion engine danger, optimal power turbine corresponding under 5 × 5 × 8 × 8=1600 group operating modes is chosen in boundary line
Inlet guide vane angle (VGVb), gas turbine efficiency in the case of not overtemperature, not excess revolutions, not into asthma is made to reach highest.
Fig. 2 is (P0 101.325kPa, T0 288.15K) under normal atmospheric environment, when NPT perseverances are 0.9, different high pressures
In the case of rotating speed NH, combustion chamber overtemperature, compressor are selected into asthma, low-pressure shaft excess revolutions boundary line and in boundary line
Optimal wicket gate control rule.As can be seen that under this control law, gas turbine reaches efficiency highest while safe operation
Point.
SS4. using atmospheric temperature T0, atmospheric pressure P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed NH to be defeated
Enter parameter, corresponding optimal power turbine inlet guide vane angle VGVbFor output parameter, number is trained using RBF neural
According to optimal power turbine control of inlet guide vanes rule is established in the fitting of 1600 groups of parameters chosen in completion SS3；
Wherein, RBF neural can utilize existing algorithm, such as the RBF neural built in MATLAB/SIMULINK
Tool box, neural network play the role of a kind of multidimensional fitting, input parameter and output parameter are set up using it herein
Between correspondence, such as the corresponding optimal power turbine inlet guide vane angle mapping relations of gas turbine working condition can
It is by Neural Networks Representation：VGVb=f (T0, P0, NPT, NH).
SS5. established optimal power turbine control of inlet guide vanes rule is substituted into Gas Turbine Simulation model and carried out
Verification.
The adjustable three shaft gas turbine of power turbine entry guide vane includes fuel flow Wf and power turbine import is led
Two control variables of leaf angle VGV, form closed-loop control to adjust indirectly by fuel flow Wf to power turbine relative rotation speed NPT
Whole gas turbine output power.The T0 measured by sensor, P0, NPT, NH parameters input trained RBF neural can
VGV is calculated in real timeb, so as to complete the optimal control to power turbine inlet guide vane angle.By neural network trained in SS4
It substitutes into gas turbine control system Dynamic Simulation Model and carries out associative simulation, gas turbine is calculated in difference by Multi simulation running
Under atmospheric environment (T0, P0), loading condition (NPT), working condition (NH) during steady operation, power turbine inlet guide vane angle
Whether gas turbine not overtemperature, not excess revolutions, not into asthma in the case of efficiency highest is enabled, you can verifies the optimization of the control law
Effect and reliability.
Obviously, examples detailed above of the invention be only to clearly illustrate example of the present invention, and not be to this
The restriction of the embodiment of invention.It for those of ordinary skill in the art, on the basis of the above description can be with
It makes other variations or changes in different ways.There is no necessity and possibility to exhaust all the enbodiments.It is all in this hair
All any modification, equivalent and improvement made within bright spirit and principle etc., should be included in the claims in the present invention
Within protection domain.
Claims (8)
1. a kind of change geometry three shaft gas turbine power turbine wicket gate control rule optimization method, the three shaft gas turbine
Including gas generator and power turbine, the inlet guide vane angle of the power turbine is adjustable, it is characterised in that：The control rule
Rule optimization method includes the following steps：
SS1. it is high-precision change geometry three shaft gas turbine to be established by known characteristics of components and detailed engine operation data
Spend simulation model；
SS2. it is calculated under different atmospheric environments, loading condition, combustion engine operating mode using the simulation model that step SS1 is established, difference is dynamic
The working condition of power turbine guide vane angle gas turbine, analysis power turbine inlet guide vane angle is to gas turbine working condition
Affecting laws；
SS3. it screens out and enables gas turbine overtemperature, excess revolutions or the power turbine inlet guide vane angle into asthma, find out remaining and enable combustion gas
The highest power turbine inlet guide vane angle of turbine efficiency under different atmospheric environments, loading condition, working condition；
SS4. joined using atmospheric temperature T0, atmospheric pressure P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed NH as input
Number, optimal power turbine inlet guide vane angle VGVbFor output parameter, using RBF neural training data, parameter is completed
Fitting, establishes optimal power turbine control of inlet guide vanes rule；
SS5. established optimal power turbine control of inlet guide vanes rule is substituted into Gas Turbine Simulation model and verified.
2. optimization method according to claim 1, it is characterised in that：The Gas Turbine Simulation mould established by step SS1
Type calculates different atmospheric temperature T0, atmospheric pressure P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed NH and power
Gas turbine working condition in the case of turbine inlet guide vane angle VGV, analysis power turbine inlet guide vane angle is to combustion gas wheel
The affecting laws of machine working condition.
3. the optimization method according to the claims, it is characterised in that：According to result of calculation, high-pressure turbine is formulated successively
Overtemperature, compressor surge, low-pressure shaft excess revolutions boundary line find out different operating modes in the range of boundary line and order combustion engine thermal efficiency highest
Power turbine inlet guide vane angle VGVbValue.
4. the optimization method according to the claims, it is characterised in that：It can stablize for guarantee gas turbine, efficiently transport
Row, using atmospheric temperature T0, atmospheric pressure P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed NH as input parameter, with
The optimal power turbine inlet guide vane angle VGV calculatedbIt for output parameter, is trained using RBF neural, completes ginseng
Optimal power turbine control of inlet guide vanes rule is established in several fittings.
5. the optimization method according to the claims, it is characterised in that：The optimal power turbine entry guide vane control built up
Rule processed and gas turbine Dynamic Simulation Model associative simulation, using trained RBF neural, by atmospheric temperature T0,
Atmospheric pressure P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed NH calculate power turbine inlet guide vane angle VGV values,
Can verification gas turbine be stablized under this wicket gate control rule, Effec-tive Function.
6. the optimization method according to the claims, it is characterised in that：In step SS3, according to the result of calculation of SS2,
Combustion chamber overtemperature, compressor are obtained into asthma, low-pressure shaft excess revolutions boundary line, is found out in boundary line later dynamic corresponding to each operating mode
Power turbine inlet guide vane angle, enables thermal efficiency of gas turbine highest.
7. the optimization method according to the claims, it is characterised in that：In step SS4, by fuel flow Wf to dynamic
Power turbine relative rotation speed NPT forms closed-loop control and comes Indirect method gas turbine output power, the air measured by sensor
The parameters such as temperature T0, atmospheric pressure P0, power turbine relative rotation speed NPT, high-pressure shaft relative rotation speed NH input trained RBF god
Optimal power turbine inlet guide vane angle VGV can be calculated in real time through networkb, so as to complete to power turbine inlet guide vane angle
Optimal control.
8. the optimization method according to the claims, it is characterised in that：It, will be trained in step SS4 in step SS5
Neural network substitutes into gas turbine control system Dynamic Simulation Model and carries out associative simulation, you can verifies the excellent of the control law
Change effect and reliability.
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| CN109083748A (en) * | 2018-07-24 | 2018-12-25 | 中国科学院工程热物理研究所 | Become the high-power control method of geometry three shaft gas turbine |
| CN109488462A (en) * | 2018-12-28 | 2019-03-19 | 中国科学院工程热物理研究所 | Change geometry three shaft gas turbine control method comprising regenerator |
| CN110836144A (en) * | 2019-12-05 | 2020-02-25 | 上海电气燃气轮机有限公司 | Method and regulating system for preventing thermal suspension of gas turbine |
| CN112464357A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Low-working-condition rotatable guide vane corner rule design method for axial flow compressor of ship gas turbine |
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| CN109488462A (en) * | 2018-12-28 | 2019-03-19 | 中国科学院工程热物理研究所 | Change geometry three shaft gas turbine control method comprising regenerator |
| CN110836144A (en) * | 2019-12-05 | 2020-02-25 | 上海电气燃气轮机有限公司 | Method and regulating system for preventing thermal suspension of gas turbine |
| CN112464357B (en) * | 2020-10-27 | 2022-04-08 | 中国船舶重工集团公司第七0三研究所 | Low-working-condition rotatable guide vane corner rule design method for axial flow compressor of ship gas turbine |
| CN112487566A (en) * | 2020-10-27 | 2021-03-12 | 中国船舶重工集团公司第七0三研究所 | Multi-column rotatable guide/stationary blade split type combined regulation and control rule design method for multistage axial flow compressor of ship gas turbine |
| CN112464357A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Low-working-condition rotatable guide vane corner rule design method for axial flow compressor of ship gas turbine |
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| CN112487565A (en) * | 2020-10-27 | 2021-03-12 | 中国船舶重工集团公司第七0三研究所 | Multi-column rotatable guide/stationary blade power exponent type combined regulation and control rule design method for multistage axial flow compressor of ship gas turbine |
| CN112487565B (en) * | 2020-10-27 | 2022-11-01 | 中国船舶重工集团公司第七0三研究所 | Multi-column rotatable guide/stationary blade power exponent type combined regulation and control rule design method for multistage axial flow compressor of ship 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 |
| 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 |
| CN113807024B (en) * | 2021-10-08 | 2024-03-22 | 大连理工大学 | Gas turbine optimal dynamic working point selection method based on proxy model |
| CN113807024A (en) * | 2021-10-08 | 2021-12-17 | 大连理工大学 | Gas turbine optimal dynamic working point selection method based on proxy model |
| CN114635801A (en) * | 2022-03-23 | 2022-06-17 | 合肥工业大学 | Method and device for optimizing backpressure characteristic of gas generator |
| CN114635801B (en) * | 2022-03-23 | 2023-11-21 | 合肥工业大学 | Back pressure characteristic optimization method and device for gas generator |
| CN117569875A (en) * | 2024-01-16 | 2024-02-20 | 济南中科先行燃气轮机科技有限公司 | Structure of gas turbine rotation speed matching VSV rotatable guide vane and adjusting method |
| CN117569875B (en) * | 2024-01-16 | 2024-05-14 | 济南中科先行燃气轮机科技有限公司 | Structure of gas turbine rotation speed matching VSV rotatable guide vane and adjusting method |
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