CN110147573A - A kind of emulation mode of gas turbine, device and storage medium - Google Patents
A kind of emulation mode of gas turbine, device and storage medium Download PDFInfo
- Publication number
- CN110147573A CN110147573A CN201910303048.2A CN201910303048A CN110147573A CN 110147573 A CN110147573 A CN 110147573A CN 201910303048 A CN201910303048 A CN 201910303048A CN 110147573 A CN110147573 A CN 110147573A
- Authority
- CN
- China
- Prior art keywords
- model
- turbine
- gas
- component
- compressor
- 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
- 238000003860 storage Methods 0.000 title claims abstract description 11
- 238000004088 simulation Methods 0.000 claims abstract description 135
- 238000000034 method Methods 0.000 claims abstract description 66
- 230000008569 process Effects 0.000 claims abstract description 36
- 238000002485 combustion reaction Methods 0.000 claims description 82
- 238000004364 calculation method Methods 0.000 claims description 39
- 238000007906 compression Methods 0.000 claims description 22
- 230000006835 compression Effects 0.000 claims description 19
- 239000000446 fuel Substances 0.000 claims description 11
- 238000004590 computer program Methods 0.000 claims description 10
- 238000004422 calculation algorithm Methods 0.000 claims description 4
- 238000002474 experimental method Methods 0.000 abstract description 16
- 238000012803 optimization experiment Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 239
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 10
- 238000010586 diagram Methods 0.000 description 10
- 230000006870 function Effects 0.000 description 7
- 239000002737 fuel gas Substances 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 238000012545 processing Methods 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000005094 computer simulation Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- NAWXUBYGYWOOIX-SFHVURJKSA-N (2s)-2-[[4-[2-(2,4-diaminoquinazolin-6-yl)ethyl]benzoyl]amino]-4-methylidenepentanedioic acid Chemical compound C1=CC2=NC(N)=NC(N)=C2C=C1CCC1=CC=C(C(=O)N[C@@H](CC(=C)C(O)=O)C(O)=O)C=C1 NAWXUBYGYWOOIX-SFHVURJKSA-N 0.000 description 1
- WKBOTKDWSSQWDR-UHFFFAOYSA-N Bromine atom Chemical compound [Br] WKBOTKDWSSQWDR-UHFFFAOYSA-N 0.000 description 1
- GDTBXPJZTBHREO-UHFFFAOYSA-N bromine Substances BrBr GDTBXPJZTBHREO-UHFFFAOYSA-N 0.000 description 1
- 229910052794 bromium Inorganic materials 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
- Control Of Turbines (AREA)
Abstract
The invention discloses a kind of emulation mode of gas turbine, device and storage mediums, it is related to gas turbine field, for reducing period and the cost of gas turbine performance optimization experiment, improve the safety of experiment, which comprises obtain the input parameter being arranged for each partial model of gas turbine；Each partial model is pre-set for emulating the model of the operational process of the gas turbine corresponding component, is provided with the characterisitic parameter that its characteristic operation is realized for the partial model in each partial model；The input parameter that will acquire inputs corresponding each partial model respectively, to combine the characterisitic parameter in corresponding each partial model to carry out operation, obtains the first simulation result of the operational process of the gas turbine；Determine whether the simulation result matches with expected result, if matching, it is determined that the characterisitic parameter of each partial model is the actual characteristic parameter in its corresponding component, to use the corresponding component operating of the actual characteristic state modulator gas turbine.
Description
Technical Field
The invention relates to the field of gas turbines, in particular to a simulation method and device of a gas turbine and a storage medium.
Background
The Gas Turbine (Gas Turbine) is an internal combustion type power machine which takes continuously flowing Gas as a working medium to drive an impeller to rotate at a high speed and converts the energy of fuel into useful work, and along with the development of industry, the application field of the Gas Turbine is very wide, so that the Gas Turbine not only can transmit and distribute electric power and energy required in the national economy development, but also is an important application device in the national defense field. It follows that the operating conditions of gas turbines are becoming increasingly complex with the expansion of their field of application and therefore it is of great importance to optimize the overall performance of the gas turbine. However, the overall performance of the micro gas turbine is adjusted by testing the physical components of the gas turbine, so that the test period is long, the test cost is high, and the problem of test safety can also exist.
Disclosure of Invention
The embodiment of the invention provides a simulation method and device of a gas turbine and a storage medium, which are used for reducing the period and cost of performance optimization experiments of a micro gas turbine and improving the safety of the experiments.
In one aspect, an embodiment of the present invention provides a simulation method for a gas turbine, including:
acquiring input parameters set for each component model of the gas turbine; each component model is a preset model for simulating the operation process of the corresponding component of the gas turbine, and characteristic parameters for realizing characteristic operation of the component model are arranged in each component model;
respectively inputting the acquired input parameters into the corresponding component models, and calculating by combining the characteristic parameters in the corresponding component models to obtain a first simulation result of the operation process of the gas turbine;
and determining whether the simulation result is matched with an expected result, and if so, determining the characteristic parameter of each component model as an actual characteristic parameter in the corresponding component so as to control the operation of the corresponding component of the gas turbine by using the actual characteristic parameter.
Optionally, if it is determined that the simulation result does not match the expected result, the following operations are performed until an obtained second simulation result matches the expected result:
changing characteristic parameters in the set component model;
and combining the input parameters corresponding to the set component model and the changed characteristic parameters, and operating again to obtain a second simulation result of the operating process of the gas turbine.
Optionally, the set component model is a compressor model corresponding to a compressor component of the gas turbine, and the changing of the characteristic parameters in the set component model specifically includes:
changing the corresponding relation between the outlet flow of the compressor and the rotating speed and pressure ratio of the compressor; and
and changing the corresponding relation between the compression efficiency of the compressor and the rotating speed and outlet flow of the compressor.
Optionally, the compressor model is further provided with a characteristic parameter for performing thermodynamic calculation of the compressor, and the characteristic parameter is set in advance according to a variable specific heat algorithm.
Optionally, the input parameters corresponding to the compressor model include: the air pressure of the outlet of the air compressor, the air pressure of the inlet of the air compressor, the air temperature of the inlet of the air compressor and the rotating speed of the air compressor;
the compressor model comprises an output sub-interface for outputting a simulation sub-result corresponding to the compressor model, wherein the simulation sub-result comprises one or more of the following: compressor outlet air flow, compressor outlet air temperature, and compressor power consumption.
Optionally, the set component model is a turbine model corresponding to a turbine component of the gas turbine, and the changing of the characteristic parameter in the set component model specifically includes:
changing the corresponding relation between the outlet flow of the turbine and the rotating speed and pressure ratio of the turbine; and
and changing the corresponding relation between the turbine compression efficiency and the turbine speed and the turbine outlet flow.
Optionally, the input parameters corresponding to the turbine model include turbine outlet gas pressure, turbine inlet gas temperature, oil-gas ratio and turbine rotation speed;
the turbine model comprises an output sub-interface used for outputting a simulation sub-result corresponding to the turbine model, wherein the simulation sub-result comprises one or more of the following components: turbine inlet gas flow, turbine outlet gas temperature, and turbine output power.
Optionally, the part model of the gas turbine includes a combustion chamber model corresponding to the combustion chamber part; the input parameters of the combustion chamber model include: the flow rate of gas at the outlet of the combustion chamber, the flow rate of compressed air at the inlet of the combustion chamber, the temperature of compressed air at the inlet of the combustion chamber and the flow rate of fuel;
the combustion chamber model comprises an output sub-interface which is used for outputting a simulation sub-result corresponding to the combustion chamber model;
the simulation sub-result includes one or more of: compressed air pressure at the inlet of the combustion chamber, gas pressure at the outlet of the combustion chamber, gas temperature at the outlet of the combustion chamber and oil-gas ratio.
Optionally, the component model of the gas turbine further includes a rotor model corresponding to the rotor component;
the rotor model comprises an output sub-interface which is used for outputting a simulation sub-result corresponding to the rotor sub-model, and the simulation sub-result at least comprises the rotor rotating speed.
Optionally, the component model of the gas turbine further includes a regenerator model corresponding to the regenerator component; the input parameters of the regenerator model include: the compressed air temperature at the inlet of the heat regenerator, the compressed air pressure at the outlet of the heat regenerator, the gas temperature at the inlet of the heat regenerator, the gas pressure at the outlet of the heat regenerator, the compressed air flow at the inlet of the heat regenerator, the gas flow at the inlet of the heat regenerator and the oil-gas ratio are measured;
the heat regenerator model comprises an output sub-interface for outputting a simulation sub-result corresponding to the heat regenerator model, wherein the simulation sub-result comprises one or more of the following: the compressed air temperature at the outlet of the heat regenerator, the compressed air pressure at the inlet of the heat regenerator, the gas pressure at the inlet of the heat regenerator and the gas temperature at the outlet of the heat regenerator.
In one aspect, an embodiment of the present invention further provides a simulation apparatus for a gas turbine, including:
the acquisition module is used for acquiring input parameters set for each component model of the gas turbine; each component model is a preset model for simulating the operation process of the corresponding component of the gas turbine, and characteristic parameters for realizing characteristic operation of the component model are arranged in each component model;
the operation module is used for respectively inputting the acquired input parameters into the corresponding component models so as to carry out operation by combining the characteristic parameters in the corresponding models to obtain a first simulation result of the operation process of the gas turbine;
and the determining module is used for determining whether the simulation result is matched with an expected result, and if so, determining the characteristic parameter of each component model as the actual characteristic parameter in the corresponding component so as to control the operation of the corresponding component of the gas turbine by using the actual characteristic parameter.
Optionally, the determining module is further configured to, if it is determined that the simulation result does not match the expected result, perform the following operations until an obtained second simulation result matches the expected result:
changing characteristic parameters in the set component model;
and combining the input parameters corresponding to the set component model and the changed characteristic parameters, and operating again to obtain a second simulation result of the operating process of the gas turbine.
Optionally, the apparatus further comprises a changing module, where the changing module is configured to:
the set component model is a gas compressor model corresponding to a gas compressor component of the gas turbine, and the change of the characteristic parameters in the set component model specifically comprises the following steps:
changing the corresponding relation between the outlet flow of the compressor and the rotating speed and pressure ratio of the compressor; and
and changing the corresponding relation between the compression efficiency of the compressor and the rotating speed and outlet flow of the compressor.
Optionally, the compressor model is further provided with a characteristic parameter for performing thermodynamic calculation of the compressor, and the characteristic parameter is set in advance according to a variable specific heat algorithm.
Optionally, the input parameters corresponding to the compressor model include: the air pressure of the outlet of the air compressor, the air pressure of the inlet of the air compressor, the air temperature of the inlet of the air compressor and the rotating speed of the air compressor;
the compressor model comprises an output sub-interface for outputting a simulation sub-result corresponding to the compressor model, wherein the simulation sub-result comprises one or more of the following: compressor outlet air flow, compressor outlet air temperature, and compressor power consumption.
Optionally, the set component model is a turbine model corresponding to a turbine component of the gas turbine, and the changing of the characteristic parameter in the set component model specifically includes:
changing the corresponding relation between the outlet flow of the turbine and the rotating speed and pressure ratio of the turbine; and
and changing the corresponding relation between the turbine compression efficiency and the turbine speed and the turbine outlet flow.
Optionally, the input parameters corresponding to the turbine model include turbine outlet gas pressure, turbine inlet gas temperature, oil-gas ratio and turbine rotation speed;
the turbine model comprises an output sub-interface used for outputting a simulation sub-result corresponding to the turbine model, wherein the simulation sub-result comprises one or more of the following components: turbine inlet gas flow, turbine outlet gas temperature, and turbine output power.
Optionally, the part model of the gas turbine includes a combustion chamber model corresponding to the combustion chamber part; the input parameters of the combustion chamber model include: the flow rate of gas at the outlet of the combustion chamber, the flow rate of compressed air at the inlet of the combustion chamber, the temperature of compressed air at the inlet of the combustion chamber and the flow rate of fuel;
the combustion chamber model comprises an output sub-interface which is used for outputting a simulation sub-result corresponding to the combustion chamber model;
the simulation sub-result includes one or more of: compressed air pressure at the inlet of the combustion chamber, gas pressure at the outlet of the combustion chamber, gas temperature at the outlet of the combustion chamber and oil-gas ratio.
Optionally, the component model of the gas turbine further includes a rotor model corresponding to the rotor component;
the rotor model comprises an output sub-interface which is used for outputting a simulation sub-result corresponding to the rotor sub-model, and the simulation sub-result at least comprises the rotor rotating speed.
Optionally, the component model of the gas turbine further includes a regenerator model corresponding to the regenerator component; the input parameters of the regenerator model include: the compressed air temperature at the inlet of the heat regenerator, the compressed air pressure at the outlet of the heat regenerator, the gas temperature at the inlet of the heat regenerator, the gas pressure at the outlet of the heat regenerator, the compressed air flow at the inlet of the heat regenerator, the gas flow at the inlet of the heat regenerator and the oil-gas ratio are measured;
the heat regenerator model comprises an output sub-interface for outputting a simulation sub-result corresponding to the heat regenerator model, wherein the simulation sub-result comprises one or more of the following: the compressed air temperature at the outlet of the heat regenerator, the compressed air pressure at the inlet of the heat regenerator, the gas pressure at the inlet of the heat regenerator and the gas temperature at the outlet of the heat regenerator.
In one aspect, the embodiment of the present invention further provides a simulation apparatus for a gas turbine, which includes at least one processor and at least one memory, where the memory stores a computer program, and when the program is executed by the processor, the processor is caused to execute the steps of the simulation method for a gas turbine provided by the embodiment of the present invention.
In one aspect, embodiments of the present invention provide a storage medium storing computer instructions, which when executed on a computer, cause the computer to perform the steps of the simulation method of a gas turbine provided by embodiments of the present invention.
In the embodiment of the invention, input parameters set for each component model of the gas turbine can be firstly obtained, wherein each component is a preset model for simulating the operation process of a corresponding component of the gas turbine, characteristic parameters for realizing characteristic operation of the component model are arranged in each component model, the obtained input parameters are respectively input into the corresponding component models so as to carry out operation by combining the characteristic parameters in the corresponding models, a first simulation result of the operation process of the gas turbine is obtained, the obtained simulation result can be further judged to be matched with an expected result, if the obtained simulation result is matched with the expected result, the characteristic parameters of each component model can be determined to be actual parameters in the corresponding component, the actual characteristic parameters can be further used for controlling the operation of the corresponding component of the gas turbine, and the period of a gas turbine physical experiment can be reduced, the experiment cost is reduced, and the safety of the experiment is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention.
FIG. 1 is a flow chart of a simulation method for a gas turbine according to an embodiment of the present invention;
FIG. 2 is a block diagram of a gas turbine system according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a compressor component model according to an embodiment of the present invention;
FIG. 4 is a schematic view of a turbine component model provided by an embodiment of the present invention;
FIG. 5 is a schematic view of a combustion chamber component model according to an embodiment of the present invention;
FIG. 6 provides a schematic view of the interior of a combustor component model according to an embodiment of the present invention;
FIG. 7 provides a schematic view of a rotor model for an embodiment of the invention;
FIG. 8 provides a schematic view of a regenerator component model in accordance with an embodiment of the present invention;
FIG. 9 is a schematic view of a simulation apparatus for a gas turbine according to an embodiment of the present invention;
FIG. 10 is a schematic view of another simulation apparatus for a gas turbine according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the technical solutions of the present invention. Based on the embodiments described in this application, all other embodiments obtained by those skilled in the art without any creative work belong to the protection scope of the technical solution of the present invention.
In the prior art, as described above, performance optimization of a micro gas turbine mainly includes obtaining optimization data by performing an experiment on a gas turbine solid component, and then adjusting the micro gas turbine solid component, however, performing an experiment on the micro gas turbine solid component to adjust overall performance of the micro gas turbine not only has a long experiment period and high experiment cost, but also may have an experiment safety problem.
Based on this, the embodiment of the present invention provides a simulation method for a gas turbine, which may first obtain input parameters set for models of components of the gas turbine, where each component is a preset model for simulating an operation process of a corresponding component of the gas turbine, a characteristic parameter for the model to implement a characteristic operation is set in each component model, and the obtained input parameters are respectively input into the corresponding component models to perform an operation by combining the characteristic parameters in the corresponding models, so as to obtain a first simulation result of the operation process of the gas turbine, and further determine that the obtained simulation result is matched with an expected result, if matched, the characteristic parameters of each component model may be determined as actual parameters in the corresponding component, and further may control the operation of the corresponding component of the gas turbine by using the actual characteristic parameters, the period of gas turbine material object experiment is reduced, the experiment cost is reduced, and the safety of the experiment is improved.
Referring to fig. 1, a simulation method of a gas turbine according to an embodiment of the present invention includes:
step 101: input parameters set for each component model of the gas turbine are obtained.
The model of each component is a preset model for simulating the operation process of the corresponding component of the gas turbine, and characteristic parameters for realizing characteristic operation of the model of each component are arranged in the model of each component.
The gas turbine in the embodiment of the present invention may be a micro gas turbine, or may be another type of gas turbine, or may be a single-shaft gas turbine or a multi-shaft gas turbine, and here, a single-shaft gas turbine is taken as an example.
In a specific practical process, as shown in fig. 2, a gas turbine system comprises a gas compressor, a turbine, a rotor, a combustion chamber, a heat regenerator, a load, a bromine refrigerator and other parts, in the embodiment of the invention, a model of the gas turbine is built by parts one by one from front to back according to the direction of airflow in the gas turbine, and finally, relevant parameters among all the part models are connected to form a model of the whole gas turbine, namely, the gas compressor model, the turbine model, the rotor model, the combustion chamber model and the heat regenerator are built for five main parts of the gas compressor, the turbine, the rotor model, the combustion chamber model and the heat regenerator respectively, and the relevant parameters among the five models are connected.
The five simulation models are also provided with characteristic parameters for realizing characteristic operation, for example, the compressor model is provided with a flow-rotating speed-pressure ratio interpolation table, an efficiency-rotating speed-flow ratio interpolation table and the like of the compressor for realizing the characteristic operation of the compressor model, and the turbine model is provided with a flow-rotating speed-pressure ratio interpolation table, an efficiency-rotating speed-gas flow ratio interpolation table and the like for realizing the characteristic operation.
In the embodiment of the present invention, MATLAB, Simulink, or other software that can be used for simulation may be used for simulation modeling, and in the embodiment of the present invention, simulation modeling of each component of a gas turbine based on Simulink is specifically described as an example.
In the embodiment of the invention, a plurality of input parameters are acquired and set for each component model of the gas turbine, and the acquired input parameters can include parameters which are set to be input from the outside and parameters which are input into other models except for a certain model after being output from the model.
Step 102: and respectively inputting the acquired input parameters into the corresponding component models to calculate by combining the characteristic parameters in the corresponding component models, so as to obtain a first simulation result of the operation process of the gas turbine.
In the embodiment of the invention, after the input parameters are obtained, the obtained input parameters can be respectively input into the component models of the gas turbine corresponding to the input parameters, the component models for obtaining the input parameters can perform characteristic operation on the input parameters according to the characteristic parameters set in the components, and further a first simulation result for simulating the operation process of the gas turbine can be obtained, and the simulation result can comprise the output parameters of the whole model of the gas turbine, such as the efficiency of the gas turbine, the rotating speed of the gas turbine and the like.
Step 103: it is determined whether the first simulation result matches the expected result.
In the embodiment of the invention, the obtained simulation result is obtained by combining the models of all the parts of the gas turbine with the actual characteristic parameters of the parts of the gas turbine to perform characteristic operation, so the obtained simulation result can truly reflect the actual operation state of the whole gas turbine or all the parts of the gas turbine, and further, the obtained simulation result can be compared with the actual operation result expected to be reached by the gas turbine, namely the expected result, so as to determine the actual operation condition of the gas turbine.
Step 104 is performed when it is determined that the first simulation result matches the expected result, and step 105 is performed when it is determined that the first simulation result does not match the expected result.
Step 104: and determining the characteristic parameters of each component model as actual characteristic parameters in the corresponding component so as to control the operation of the corresponding component of the gas turbine by using the actual characteristic parameters.
In the embodiment of the invention, when the obtained first simulation result is matched with the expected result, the characteristic parameters of each part model can be determined to be the actual characteristic parameters of the part corresponding to each part model, and then the actual characteristic parameters can be directly used for controlling the operation of the part corresponding to the gas turbine.
Step 105: and changing characteristic parameters in the set component model, combining the input parameters corresponding to the set component model and the changed characteristic parameters, and performing calculation again to obtain a second simulation result of the operation process of the gas turbine.
In the embodiment of the invention, when the obtained first simulation result is not matched with the expected result, the characteristic parameters in the set component model can be changed, and then the changed characteristic parameters and the input parameters corresponding to the set component model can be combined to perform the characteristic operation again to obtain the second simulation result of the operation process of the simulated gas turbine.
Furthermore, the obtained second simulation result can be compared with the expected result of the gas turbine to determine whether the second simulation result matches the expected result, if so, the changed characteristic parameter is determined to be the actual characteristic parameter of the gas turbine component corresponding to the characteristic parameter, and if not, the characteristic parameter in the set component model is continuously changed until the obtained simulation result matches the expected result.
As an optional implementation manner, in an embodiment of the present invention, the set component model may be a compressor model corresponding to a compressor component in a gas turbine component, that is, characteristic parameters of the compressor model may be changed, where the characteristic parameters of the compressor model include a compressor mass flow-rotation speed-pressure ratio interpolation table, an efficiency-rotation speed-flow interpolation table, an air temperature-enthalpy interpolation table, an air temperature-entropy interpolation table, an air entropy-temperature interpolation table, an air enthalpy-temperature interpolation table, and the like.
Therefore, the characteristic parameter of the compressor model can be changed by changing a flow-rotating speed-pressure ratio interpolation table of the compressor model, namely changing the corresponding relation between the outlet flow of the compressor and the rotating speed and the pressure ratio of the compressor, and changing an efficiency-rotating speed-flow ratio interpolation table of the compressor model, namely changing the corresponding relation between the compression efficiency of the compressor and the rotating speed and the outlet flow of the compressor, so that the characteristic operation can be performed again by combining the input parameter corresponding to the compressor model and the changed characteristic parameter of the compressor model to obtain a second simulation result of the operation process of the gas turbine.
Wherein, the input parameters corresponding to the compressor model comprise the pressure P of the outlet air of the compressorcoutInlet air pressure P of compressorcinInlet air temperature T of compressorcinAnd a compressor speed n.
In the embodiments of the present inventionAs shown in fig. 3, the compressor model includes two operation modules, i.e., a characteristic calculation module and a thermal calculation module, when the compressor model is operated, the input parameter corresponding to the compressor model may be input into the characteristic calculation module to perform characteristic operation, and based on the formula (1) and the formula (2), the outlet flow of the compressor model is obtained by using a compressor flow-rotation speed-pressure ratio interpolation table and an efficiency-rotation speed-flow interpolation table (G in fig. 3)cin) Adiabatic compression efficiency value of the compressor (EFC in fig. 3) and compressor pressure ratio (Pi in fig. 3):
wherein G iscη for compressor outlet air flow without regard to thermal effectscIs the adiabatic compression efficiency value of the compressor,the pressure ratio of the air compressor is set,converted into a rotational speed.
And then, inputting parameters obtained by the operation of the characteristic calculation module in the compressor model into a thermodynamic calculation module of the compressor model for operation.
In the embodiment of the invention, the calculation process of the thermodynamic calculation module in the compressor model mainly adopts a transformation ratio thermal method for calculation, and the specific calculation process comprises the following steps:
s11: according to the inlet air temperature T of the air compressor by adopting a specific entropy function methodcinInlet air pressure P of compressorcinAnd compressor outlet air pressure PcoutObtaining the specific entropy of the inlet of the compressor and the enthalpy of the inlet of the compressor according to the specific entropyAnd obtaining the outlet temperature of the compressor in isentropic compression by using a specific entropy and entropy-temperature interpolation table of air.
S12: obtaining the temperature of the outlet of the compressor isentropic compression according to S11, and obtaining the specific enthalpy value of the compressor isentropic compression outlet according to the temperature-enthalpy interpolation table of air;
s13: subtracting the specific enthalpy value of the compressor inlet from the specific enthalpy value of the compressor isentropic compression outlet obtained in the step S11 to obtain the specific enthalpy increase of the compressor isentropic compression;
s14: dividing the increase of the specific enthalpy of the isentropic compression obtained in the step S13 by the compression efficiency of the compressor to obtain the increase of the specific enthalpy of the actual compression process of the compressor;
s15: adding the specific enthalpy calculated in the S14 to the specific enthalpy value of the compressor inlet to obtain the specific enthalpy value of the actual compression process outlet of the compressor, and obtaining the actual compressor outlet temperature according to the actual outlet specific enthalpy value and the enthalpy-temperature interpolation table of the air;
s16: multiplying the specific enthalpy value of the actual compression process outlet of the compressor calculated in the S15 by the mass flow of the compressor to obtain the power required by the compressor, wherein the power required by the compressor is the consumed power N of the compressorc。
In the embodiment of the invention, in order to conveniently check the simulation sub-results of the models corresponding to the components in the gas turbine, the models corresponding to the components in the gas turbine are provided with the output sub-interfaces for outputting the simulation sub-results corresponding to the components, so that the simulation sub-results of the models corresponding to the components can be checked through the output sub-interfaces, and the operation states of the components can be conveniently observed. Therefore, an output sub-interface for outputting a simulation sub-result of the compressor model is arranged in the compressor model, wherein the simulation sub-result output by the output sub-interface of the compressor model comprises the air flow G at the outlet of the compressorcoutTemperature T of air at outlet of air compressorcoutAnd compressor power consumption NcAnd the simulation sub-result of the compressor model can be checked through Display-Display8 set in fig. 3.
In another alternative implementation manner, in an embodiment of the present invention, the set component model may also be a turbine model corresponding to a turbine component in the gas turbine component, that is, characteristic parameters of the turbine model may also be changed, where the characteristic parameters of the turbine model include a turbine gas flow-rotation speed-pressure drop ratio interpolation table, an efficiency-rotation speed-gas flow interpolation table, a gas temperature-enthalpy interpolation table, a gas temperature-entropy interpolation table, a gas entropy-temperature interpolation table, a gas enthalpy-temperature interpolation table, and the like.
Therefore, the characteristic parameter of the turbine model can be changed by changing a turbine gas flow-rotating speed-pressure drop ratio interpolation table, namely changing the corresponding relation between the turbine outlet flow and the turbine rotating speed and the turbine pressure ratio, and changing an efficiency-rotating speed-gas flow interpolation table of the turbine model, namely changing the corresponding relation between the turbine compression efficiency and the turbine rotating speed and the turbine outlet flow, and further performing characteristic operation again by combining the input parameter corresponding to the turbine model and the characteristic parameter of the changed turbine model to obtain a second simulation result of the gas turbine operation process.
Wherein the input parameters for the turbine model pair include turbine outlet gas pressure PtoutTurbine inlet gas pressure PtinTurbine inlet gas temperature TtinAir-fuel ratio f and turbine speed n.
In the embodiment of the invention, as shown in fig. 4, the turbine model also comprises two operation modules, namely a characteristic calculation module and a thermal calculation module. When the turbine model is calculated, the turbine outlet gas pressure P in the input parameters corresponding to the turbine model can be calculated firsttoutTurbine inlet gas pressure PtinTurbine inlet gas temperature TtinAnd inputting the turbine speed n into a characteristic calculation module of the turbine model to perform characteristic calculation, namely performing characteristic calculation based on the formula (3) and the formula (4).
Wherein,the flow rate is reduced for the turbine,reduced rotational speed for turbine ηTDenotes the turbine efficiency,. piTIs a turbo expansion ratio (turbo pressure drop ratio).
Further, after the characteristic calculation of the characteristic calculation module, the turbine pressure drop ratio pi can be obtainedTTurbine efficiency ηTAnd turbine inlet gas flow GtinAnd then the three parameters are obtained after the characteristic calculation, and the oil-gas ratio f in the corresponding input parameters of the turbine model is input into a thermodynamic calculation module of the turbine model for thermodynamic calculation to obtain the turbine output power NtTurbine outlet temperature TtoutAnd turbine outlet gas flow rate Gtout。
The process of turbine thermodynamic calculations includes:
s21: according to the temperature T of the turbine inlet gastinAnd other characteristic parameters in the turbine model to combine equations (5) and (6) to calculate the enthalpy and the logarithmic pressure ratio of the inlet combustion gas:
hgin＝f(Ttin) Formula (5)
lnπin＝f(Ttin) Formula (6)
Wherein, ln piinAnd ln pioutRepresenting the turbine inlet-outlet specific entropy function (for 1kg of working medium).
S22: determining the logarithmic expansion ratio of the turbine outlet according to the turbine inlet gas expansion ratio by combining the formula (7):
lnπout＝lnπin-RglnπTformula (7)
Wherein R isgRepresenting the gas constant of the combustion gas, as the molar gas constant R*Ratio to the molar mass of the fuel gas Mg.
S23: determining the enthalpy value h of the gas after isentropic adiabatic expansion of the gas in the turbine according to the formula (8)out：
hout＝f(lnπout) Formula (8)
S24 turbine efficiency ηTAnd formula (9) determining the actual enthalpy h of the turbine outlet gasouts：
hout＝hin-(hin-houts)ηTFormula (9)
S25: determining the temperature T of the turbine outlet gas by the gas thermal property relation in combination with the formula (10)tout：
Ttout＝f(hout) Formula (10)
S26: finally, the actual output power N of the turbine is calculated by combining the formula (11)t：
Nt＝Gtin(hin-hout) Formula (11)
In the embodiment of the invention, in order to conveniently check the operating state of the turbine model, an output sub-interface for outputting a turbine model simulation sub-result is arranged in the turbine model, wherein the simulation sub-result output by the output sub-interface of the turbine model comprises the turbine inlet gas flow GtinTurbine outlet gas flow GtoutTurbine outlet gas temperature TtoutAnd turbine output work Nt。
In the embodiment of the present invention, in addition to setting the part model, the part model of the gas turbine further includes a combustion chamber model corresponding to the combustion chamber part, and referring to fig. 5, the input parameter corresponding to the combustion chamber model includes the combustion chamberOutlet gas flow GboutCombustion chamber inlet compressed air flow rate GbinTemperature T of compressed air at inlet of combustion chamberinFuel flow rate GfIn order to conveniently check the running condition of the combustion chamber model, an output sub-interface is also arranged in the combustion chamber model and used for outputting a simulation sub-result of the combustion chamber model, and the simulation sub-result output by the combustion chamber model comprises the inlet compressed air pressure P of the combustion chamberbinGas pressure P at the outlet of the combustion chamberboutTemperature T of gas at outlet of combustion chamberboutAnd the oil-gas ratio f.
Specifically, the internal structure of the combustion chamber model can be divided into four calculation regions according to different functions, see fig. 6, the four calculation regions are used for obtaining the simulation sub-results of the combustion chamber model, and the four calculation modules are respectively an oil-gas ratio calculation module, a combustion chamber outlet gas pressure calculation module, a combustion chamber inlet air pressure calculation module and a combustion chamber outlet gas temperature calculation module. The combustion chamber outlet gas pressure calculation module is used for realizing the calculation process of the formula (12) to obtain the combustion chamber outlet gas pressure PboutAs a result of this simulation, the combustor inlet air pressure calculation module is used to implement the calculation process of equation (13) to obtain the combustor inlet air pressure PbinAs a result of the simulation, the combustion chamber outlet gas temperature calculation module is used for realizing the calculation process of the formula (14) so as to obtain the combustion chamber outlet gas temperature Tbout。
Pbout＝(1-Kb)PinPbout＝(1-k)PbinFormula (14)
Wherein V is the volume of the combustion chamber, ηBFor combustion efficiency of the combustion chamber, GgoutGas flow at the outlet of the combustion chamber, GginGas flow at the inlet of the combustion chamber, GfFor the fuel flow into the combustion chamber, hfinIs the specific enthalpy value, h, of the fuel entering the combustion chamberainIs the specific enthalpy value, h, of the combustion chamber inlet airgoutIs the specific enthalpy value, H, of the combustion gas at the outlet of the combustion chamberuIs the heat value of combustion of the fuel, CpgIs the isobaric specific heat capacity of the gas in the combustion chamber, k is the specific heat ratio of the gas, PboutFor combustion chamber outlet gas pressure, PbinFor compressing the air pressure at the combustion chamber inlet, KbIs the combustion chamber pressure loss coefficient.
In the embodiment of the present invention, the component model of the gas turbine further includes a rotor model, see fig. 7, in which the rotation speed of the rotor can be solved by using the principle of balancing the load power of the compressor, that is, the rotation speed n is obtained by the formula (15).
Wherein the component model of the characteristic parameter is modified.Is the inverse of the moment of inertia of the rotor, NlThe total power consumption of the compressor and the load.
In the embodiment of the present invention, the model of the gas turbine component further includes a regenerator model corresponding to the regenerator component, and referring to fig. 8, the input parameter corresponding to the regenerator model includes a regenerator inlet compressed air temperature TainCompressed air pressure P at outlet of regeneratoraoutGas temperature T at inlet of heat regeneratorginGas pressure P at outlet of heat regeneratorgoutRegenerator inlet compressed air flow rate GainGas flow G at inlet of heat regeneratorginThe oil-gas ratio f is used for conveniently checking the running condition of the heat regenerator model, an output sub-interface is also arranged in the heat regenerator model and used for outputting a simulation sub-result of the heat regenerator model, and the heat regenerator model outputsThe simulation sub-result comprises the temperature T of the compressed air at the outlet of the heat regeneratoraoutRegenerator inlet compressed air pressure PainGas pressure P at inlet of heat regeneratorginGas temperature T at outlet of heat regeneratorgout。
Specifically, in order to improve the speed and stability of the simulation operation, when the heat regenerator model performs the characteristic operation, energy conservation (under an ideal condition) can be utilized, that is, the heat output released after the fuel gas passes through the heat regenerator is equal to the heat absorbed by the air after passing through the heat regenerator, and further, the simulation sub-result of the heat regenerator model can be obtained by combining the formula (16), the formula (17) and the formula (18) according to the characteristic parameters set in the heat regenerator model, such as an oil-gas ratio-fuel gas enthalpy interpolation table, an air temperature-enthalpy interpolation table, an air enthalpy-temperature interpolation table, a fuel gas enthalpy-oil-gas ratio-fuel gas temperature interpolation table and the like.
Qg＝QaFormula (16)
Qg＝Ggin(hin-hout) Formula (17)
h ═ F (F, T) formula (18)
Wherein Qa is the heat released by the turbine outlet gas after passing through the heat regenerator, Qg is the heat absorbed by the compressed air after passing through the heat regenerator, GginIs the inlet gas flow h of the heat regeneratorinIs the enthalpy value, h, of the regenerator inlet gasoutThe enthalpy value of the gas at the outlet of the heat regenerator is represented as f, the oil-gas ratio is represented as T, the gas temperature is represented as T, and h is the gas enthalpy value under the conditions of the current temperature and the oil-gas ratio.
Therefore, by the above method, after the input parameters set for each component model of the gas turbine are acquired, the acquired input parameters are respectively input into the corresponding gas turbine component models, and the characteristic parameters in each component model are combined to perform calculation, so as to obtain a first simulation result of the operation process of the fuel turbine, and further, the first simulation result can be compared with an expected gas turbine operation result, and whether the first simulation result is matched with the expected gas turbine operation result is judged, if the first simulation result is matched with the expected result, the characteristic parameters of each component of the gas turbine for simulation can be determined to be actual characteristic parameters applicable to actual objects of each component of the gas turbine, and the actual characteristic parameters can be used for controlling the operation of the corresponding component of the gas turbine; if the first simulation result is not matched with the expected result, characteristic parameters set in a model corresponding to the gas turbine setting component for simulation need to be changed, and then the changed characteristic parameters are used for carrying out simulation test until the obtained simulation result is matched with the expected result, namely the actual characteristic parameters which can be used for controlling the operation of the component corresponding to the gas turbine are obtained, so that the experiment period and the experiment cost are reduced, and the experiment safety is improved.
Based on the same inventive concept, an embodiment of the present invention provides a simulation apparatus for a gas turbine, and the specific implementation of the simulation method for the gas turbine of the apparatus can be referred to the description of the above method embodiment, and repeated details are not repeated, as shown in fig. 9, the apparatus includes:
an obtaining module 90, configured to obtain input parameters set for each component model of the gas turbine; each part model is a preset model for simulating the operation process of the corresponding part of the gas turbine, and characteristic parameters for realizing characteristic operation of the part model are arranged in each part model;
the operation module 91 is configured to input the acquired input parameters into the corresponding component models respectively, so as to perform operation by combining the characteristic parameters in the corresponding component models, and obtain a first simulation result of the operation process of the gas turbine;
and the determining module 92 is used for determining whether the simulation result is matched with an expected result, and if so, determining the characteristic parameter of each component model as the actual characteristic parameter in the corresponding component so as to control the operation of the corresponding component of the gas turbine by using the actual characteristic parameter.
Optionally, the determining module 92 is further configured to, if it is determined that the simulation result does not match the expected result, perform the following operations until the obtained second simulation result matches the expected result:
changing characteristic parameters in the set component model;
and combining the input parameters corresponding to the set component model and the changed characteristic parameters, and operating again to obtain a second simulation result of the operating process of the gas turbine.
Optionally, the apparatus further includes an altering module 93, where the altering module 93 is configured to:
the set component model is a gas compressor model corresponding to a gas compressor component of the gas turbine, and the change of the characteristic parameters in the set component model specifically comprises the following steps:
changing the corresponding relation between the outlet flow of the compressor and the rotating speed and pressure ratio of the compressor; and
and changing the corresponding relation between the compression efficiency of the compressor and the rotating speed and outlet flow of the compressor.
Optionally, the compressor model is further provided with a characteristic parameter for performing thermodynamic calculation of the compressor, and the characteristic parameter is set in advance according to a variable specific heat algorithm.
Optionally, the input parameters corresponding to the compressor model include: the air pressure of the outlet of the air compressor, the air pressure of the inlet of the air compressor, the air temperature of the inlet of the air compressor and the rotating speed of the air compressor;
the compressor model comprises an output sub-interface for outputting a simulation sub-result corresponding to the compressor model, wherein the simulation sub-result comprises one or more of the following: compressor outlet air flow, compressor outlet air temperature, and compressor power consumption.
Optionally, the set component model is a turbine model corresponding to a turbine component of the gas turbine, and the changing of the characteristic parameter in the set component model specifically includes:
changing the corresponding relation between the outlet flow of the turbine and the rotating speed and pressure ratio of the turbine; and
and changing the corresponding relation between the turbine compression efficiency and the turbine speed and the turbine outlet flow.
Optionally, the input parameters corresponding to the turbine model include turbine outlet gas pressure, turbine inlet gas temperature, oil-gas ratio and turbine rotation speed;
the turbine model comprises an output sub-interface used for outputting a simulation sub-result corresponding to the turbine model, wherein the simulation sub-result comprises one or more of the following components: turbine inlet gas flow, turbine outlet gas temperature, and turbine output power.
Optionally, the part model of the gas turbine includes a combustion chamber model corresponding to the combustion chamber part; the input parameters of the combustion chamber model include: the flow rate of gas at the outlet of the combustion chamber, the flow rate of compressed air at the inlet of the combustion chamber, the temperature of compressed air at the inlet of the combustion chamber and the flow rate of fuel;
the combustion chamber model comprises an output sub-interface which is used for outputting a simulation sub-result corresponding to the combustion chamber model;
the simulation sub-result includes one or more of: compressed air pressure at the inlet of the combustion chamber, gas pressure at the outlet of the combustion chamber, gas temperature at the outlet of the combustion chamber and oil-gas ratio.
Optionally, the component model of the gas turbine further includes a rotor model corresponding to the rotor component;
the rotor model comprises an output sub-interface which is used for outputting a simulation sub-result corresponding to the rotor sub-model, and the simulation sub-result at least comprises the rotor rotating speed.
Optionally, the component model of the gas turbine further includes a regenerator model corresponding to the regenerator component; the input parameters of the regenerator model include: the compressed air temperature at the inlet of the heat regenerator, the compressed air pressure at the outlet of the heat regenerator, the gas temperature at the inlet of the heat regenerator, the gas pressure at the outlet of the heat regenerator, the compressed air flow at the inlet of the heat regenerator, the gas flow at the inlet of the heat regenerator and the oil-gas ratio are measured;
the heat regenerator model comprises an output sub-interface for outputting a simulation sub-result corresponding to the heat regenerator model, wherein the simulation sub-result comprises one or more of the following: the compressed air temperature at the outlet of the heat regenerator, the compressed air pressure at the inlet of the heat regenerator, the gas pressure at the inlet of the heat regenerator and the gas temperature at the outlet of the heat regenerator.
Based on the same inventive concept, an embodiment of the present invention further provides a simulation apparatus for a gas turbine, as shown in fig. 10, including at least one processor 100 and at least one memory 101, where the memory 101 stores a computer program, and when the program is executed by the processor 100, the processor 101 is caused to execute the steps of the simulation method for a gas turbine provided in the embodiment of the present invention.
Based on the same inventive concept, an embodiment of the present invention provides a computer-readable storage medium storing computer instructions that, when executed on a computer, cause the computer to perform the steps of a simulation method of a gas turbine as described above.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, optical storage, and the like) having computer-usable program code embodied therein.
The present invention has been described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is intended to include such modifications and variations.
Claims (13)
1. A method of simulating a gas turbine, comprising:
acquiring input parameters set for each component model of the gas turbine; each component model is a preset model for simulating the operation process of the corresponding component of the gas turbine, and characteristic parameters for realizing characteristic operation of the component model are arranged in each component model;
respectively inputting the acquired input parameters into the corresponding component models, and calculating by combining the characteristic parameters in the corresponding component models to obtain a first simulation result of the operation process of the gas turbine;
and determining whether the simulation result is matched with an expected result, and if so, determining the characteristic parameter of each component model as an actual characteristic parameter in the corresponding component so as to control the operation of the corresponding component of the gas turbine by using the actual characteristic parameter.
2. The method of claim 1, wherein if it is determined that the simulation result does not match the expected result, performing the following until a second simulation result is obtained that matches the expected result:
changing characteristic parameters in the set component model;
and combining the input parameters corresponding to the set component model and the changed characteristic parameters, and performing operation again to obtain a second simulation result of the operation process of the gas turbine.
3. The method according to claim 2, wherein the setting component model is a compressor model corresponding to a compressor component of the gas turbine, and the changing characteristic parameters in the setting component model includes:
changing the corresponding relation between the outlet flow of the compressor and the rotating speed and pressure ratio of the compressor; and
and changing the corresponding relation between the compression efficiency of the compressor and the rotating speed and outlet flow of the compressor.
4. A method as set forth in claim 3, wherein the compressor model further sets characteristic parameters for performing compressor thermodynamic calculations, the characteristic parameters being set in advance in accordance with a variable heat ratio algorithm.
5. A method according to claim 3 or 4, wherein the input parameters corresponding to the compressor model comprise: the air pressure of the outlet of the air compressor, the air pressure of the inlet of the air compressor, the air temperature of the inlet of the air compressor and the rotating speed of the air compressor;
the compressor model comprises an output sub-interface for outputting a simulation sub-result corresponding to the compressor model, wherein the simulation sub-result comprises one or more of the following: compressor outlet air flow, compressor outlet air temperature, and compressor power consumption.
6. The method according to claim 2, wherein the set-up part model is a turbine model corresponding to a turbine part of the gas turbine, and the modifying the characteristic parameter in the set-up part model comprises:
changing the corresponding relation between the outlet flow of the turbine and the rotating speed and pressure ratio of the turbine; and
and changing the corresponding relation between the turbine compression efficiency and the turbine speed and the turbine outlet flow.
7. The method of claim 6, wherein the input parameters corresponding to the turbine model include turbine outlet gas pressure, turbine inlet gas temperature, gas-oil ratio, and turbine speed;
the turbine model comprises an output sub-interface used for outputting a simulation sub-result corresponding to the turbine model, wherein the simulation sub-result comprises one or more of the following components: turbine inlet gas flow, turbine outlet gas temperature, and turbine output power.
8. The method of any of claims 1-4, 6, 7, wherein the component models of the gas turbine include a combustor model corresponding to a combustor component; the input parameters of the combustion chamber model include: combustion chamber outlet gas flow, combustion chamber inlet compressed air temperature and fuel flow;
the combustion chamber model comprises an output sub-interface for outputting a simulation sub-result corresponding to the combustion chamber model, the simulation sub-result comprising one or more of: compressed air pressure at the inlet of the combustion chamber, gas pressure at the outlet of the combustion chamber, gas temperature at the outlet of the combustion chamber and oil-gas ratio.
9. The method according to any of claims 1-4, 6, 7, wherein the component model of the gas turbine further comprises a rotor model corresponding to a rotor component;
the rotor model comprises an output sub-interface which is used for outputting a simulation sub-result corresponding to the rotor sub-model, and the simulation sub-result at least comprises the rotor rotating speed.
10. The method of any of claims 1-4, 6, 7, wherein the component model of the gas turbine further comprises a regenerator model corresponding to a regenerator component; the input parameters of the regenerator model include: the compressed air temperature at the inlet of the heat regenerator, the compressed air pressure at the outlet of the heat regenerator, the gas temperature at the inlet of the heat regenerator, the gas pressure at the outlet of the heat regenerator, the compressed air flow at the inlet of the heat regenerator, the gas flow at the inlet of the heat regenerator and the oil-gas ratio;
the heat regenerator model comprises an output sub-interface for outputting a simulation sub-result corresponding to the heat regenerator model, wherein the simulation sub-result comprises one or more of the following: the compressed air temperature at the outlet of the heat regenerator, the compressed air pressure at the inlet of the heat regenerator, the gas pressure at the inlet of the heat regenerator and the gas temperature at the outlet of the heat regenerator.
11. A simulation apparatus of a gas turbine, comprising:
the acquisition module is used for acquiring input parameters set for each component model of the gas turbine; each component model is a preset model for simulating the operation process of the corresponding component of the gas turbine, and characteristic parameters for realizing characteristic operation of the component model are arranged in each component model;
the operation module is used for respectively inputting the acquired input parameters into the corresponding component models so as to carry out operation by combining the characteristic parameters in the corresponding models to obtain a first simulation result of the operation process of the gas turbine;
and the determining module is used for determining whether the simulation result is matched with an expected result, and if so, determining the characteristic parameter of each component model as the actual characteristic parameter in the corresponding component so as to control the operation of the corresponding component of the gas turbine by using the actual characteristic parameter.
12. A simulation device of a gas turbine, comprising at least one processor and at least one memory, wherein the memory stores a computer program which, when executed by the processor, causes the processor to carry out the steps of the method according to any one of claims 1 to 10.
13. A storage medium storing computer instructions which, when executed on a computer, cause the computer to perform the steps of the method according to any one of claims 1 to 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910303048.2A CN110147573B (en) | 2019-04-16 | 2019-04-16 | Simulation method and device of gas turbine and storage medium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910303048.2A CN110147573B (en) | 2019-04-16 | 2019-04-16 | Simulation method and device of gas turbine and storage medium |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110147573A true CN110147573A (en) | 2019-08-20 |
| CN110147573B CN110147573B (en) | 2023-04-07 |
Family
ID=67589542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910303048.2A Active CN110147573B (en) | 2019-04-16 | 2019-04-16 | Simulation method and device of gas turbine and storage medium |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110147573B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111339681A (en) * | 2020-03-23 | 2020-06-26 | 中国空气动力研究与发展中心计算空气动力研究所 | Nozzle outlet parameter matching method for simulating engine gas medium jet flow aerodynamic interference effect by adopting air medium |
| CN112666922A (en) * | 2020-12-17 | 2021-04-16 | 中国科学院工程热物理研究所 | Method and system for testing light gas turbine control system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4249238A (en) * | 1978-05-24 | 1981-02-03 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Apparatus for sensor failure detection and correction in a gas turbine engine control system |
| US20110153295A1 (en) * | 2009-12-21 | 2011-06-23 | United Technologies Corporation | Method and system for modeling the performance of a gas turbine engine |
| US20110224959A1 (en) * | 2008-10-17 | 2011-09-15 | Zhang Xiao-Yi | Gas turbine model and a method for the modeling of a gas turbine |
| CN102436182A (en) * | 2011-08-31 | 2012-05-02 | 哈尔滨工程大学 | Semi-physical simulation device and simulation method of ship gas turbine generator set |
| CN105740559A (en) * | 2016-02-03 | 2016-07-06 | 珠海市钰海电力有限公司 | Real-time energy efficiency optimization method for combustion gas turbine |
| CN106874569A (en) * | 2017-01-19 | 2017-06-20 | 中国科学院工程热物理研究所 | One kind becomes geometry split gas turbine real-time simulation modeling method |
-
2019
- 2019-04-16 CN CN201910303048.2A patent/CN110147573B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4249238A (en) * | 1978-05-24 | 1981-02-03 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Apparatus for sensor failure detection and correction in a gas turbine engine control system |
| US20110224959A1 (en) * | 2008-10-17 | 2011-09-15 | Zhang Xiao-Yi | Gas turbine model and a method for the modeling of a gas turbine |
| US20110153295A1 (en) * | 2009-12-21 | 2011-06-23 | United Technologies Corporation | Method and system for modeling the performance of a gas turbine engine |
| CN102436182A (en) * | 2011-08-31 | 2012-05-02 | 哈尔滨工程大学 | Semi-physical simulation device and simulation method of ship gas turbine generator set |
| CN105740559A (en) * | 2016-02-03 | 2016-07-06 | 珠海市钰海电力有限公司 | Real-time energy efficiency optimization method for combustion gas turbine |
| CN106874569A (en) * | 2017-01-19 | 2017-06-20 | 中国科学院工程热物理研究所 | One kind becomes geometry split gas turbine real-time simulation modeling method |
Non-Patent Citations (1)
| Title |
|---|
| 黄荣华等: "双轴燃气轮机动态仿真模型研究", 《华中科技大学学报(自然科学版)》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111339681A (en) * | 2020-03-23 | 2020-06-26 | 中国空气动力研究与发展中心计算空气动力研究所 | Nozzle outlet parameter matching method for simulating engine gas medium jet flow aerodynamic interference effect by adopting air medium |
| CN111339681B (en) * | 2020-03-23 | 2020-11-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Nozzle outlet parameter matching method for simulating engine gas medium jet flow aerodynamic interference effect by adopting air medium |
| CN112666922A (en) * | 2020-12-17 | 2021-04-16 | 中国科学院工程热物理研究所 | Method and system for testing light gas turbine control system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110147573B (en) | 2023-04-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106844893B (en) | Method for calculating low pressure cylinder efficiency of steam turbine of single-shaft gas-steam combined cycle unit | |
| Houssainy et al. | Thermodynamic performance and cost optimization of a novel hybrid thermal-compressed air energy storage system design | |
| He et al. | Compression performance optimization considering variable charge pressure in an adiabatic compressed air energy storage system | |
| Antonelli et al. | Operating maps of a rotary engine used as an expander for micro-generation with various working fluids | |
| Song et al. | Effects of suction port arrangements on a scroll expander for a small scale ORC system based on CFD approach | |
| Li et al. | Backpressure adjustable gas turbine combined cycle: A method to improve part-load efficiency | |
| Badami et al. | Dynamic parsimonious model and experimental validation of a gas microturbine at part-load conditions | |
| Malinowski et al. | Analytical model-based energy and exergy analysis of a gas microturbine at part-load operation | |
| Cheng et al. | Bi-directional nozzle control of multistage radial-inflow turbine for optimal part-load operation of compressed air energy storage | |
| CN110147573B (en) | Simulation method and device of gas turbine and storage medium | |
| CN104533821A (en) | Gas compressor control method | |
| Haugwitz | Modelling of microturbine systems | |
| Gobran | Off-design performance of solar Centaur-40 gas turbine engine using Simulink | |
| CN114462245B (en) | Multi-shaft gas turbine optimal rotation speed determination method and system | |
| CN114462253B (en) | Method for analyzing performance parameters of key parts of heavy-duty gas turbine | |
| CN108304678A (en) | The method for being directed to different fuel calculation gas turbine performance based on emulation platform | |
| CN106840685B (en) | A kind of gas turbine dynamic operation condition database sample point choosing method | |
| CN107301268A (en) | A kind of ship gas turbine variable stator vane angle compressor deflection angle optimization method | |
| Song et al. | Investigation on the wet compression performance of a co-rotating scroll hydrogen recirculation pump for fuel cell engine systems | |
| CN109858129A (en) | A kind of gas turbine dynamic emulation method about combined supply system | |
| Roberts et al. | Dynamic simulation of energy systems: comparison of a physics-based against time constant based approach applied to a microturbine test rig | |
| Hugenroth et al. | Experimental investigation of a liquid-flooded Ericsson cycle cooler | |
| Bozzi et al. | Simplified simulation block diagram of twin-shaft gas turbines | |
| Iliescu et al. | Gas turbine modeling for load-frequency control | |
| Mahmood et al. | Analysis of a Regenerative Gas Turbine Cycle for Power Plant |
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 |