CN110147573B - Simulation method and device of gas turbine and storage medium - Google Patents
Simulation method and device of gas turbine and storage medium Download PDFInfo
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- CN110147573B CN110147573B CN201910303048.2A CN201910303048A CN110147573B CN 110147573 B CN110147573 B CN 110147573B CN 201910303048 A CN201910303048 A CN 201910303048A CN 110147573 B CN110147573 B CN 110147573B
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Abstract
The invention discloses a simulation method, a simulation device and a storage medium of a gas turbine, which relate to the field of gas turbines and are used for reducing the period and the cost of a performance optimization experiment of the gas turbine and improving the safety of the experiment, wherein the method comprises the following steps: 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.
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 development of national economy, 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 may 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 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.
Optionally, if it is determined that the simulation result does not match the expected result, performing 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 performing operation again to obtain a second simulation result of the operation 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 compressor outlet air pressure, the air compressor inlet air temperature and the air compressor rotating speed;
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: combustion chamber outlet gas flow, combustion chamber inlet compressed air temperature and fuel flow;
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;
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 setting part 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.
Optionally, the apparatus further includes an altering module, where the altering 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 comprise: 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 obtained firstly, 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 be combined with the characteristic parameters in the corresponding models for operation, a first simulation result of the operation process of the gas turbine is obtained, the obtained simulation result can be 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 used for controlling the operation of the corresponding component of the gas turbine, the period of a gas turbine real experiment is 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 introduced, and it is apparent that the drawings in the 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 model of a compressor component 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. All other embodiments obtained by a person skilled in the art based on the embodiments described in the present application without any creative efforts shall fall within 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 physical part of the gas turbine, and then adjusting the physical part of the micro gas turbine, however, the experiment performed on the physical part of the micro gas turbine to adjust the overall performance of the micro gas turbine not only has a long experiment period and a high experiment cost, but also may have an experiment safety problem.
Based on this, the embodiment of the invention provides a simulation method of a gas turbine, which may first obtain input parameters set for each component model of the gas turbine, where each component is a preset model for simulating an operation process of a corresponding component of the gas turbine, characteristic parameters for the component model to implement characteristic operations are set in each component model, and the obtained input parameters are respectively input into the corresponding component models to perform operations 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, it may be determined that the obtained simulation result is matched with an expected result, and if matched, the characteristic parameters of each component model may be determined as actual parameters in the corresponding component, and further, the actual characteristic parameters may be used to control the operation of the corresponding component of the gas turbine, so as to reduce a period of a gas turbine physical experiment, reduce experiment cost, and improve safety of the experiment.
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 other types of gas turbines, and may also 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 gas flow 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, a gas compressor model, a turbine model, a rotor model, a combustion chamber model and a heat regenerator are built for five main parts of the gas compressor, the turbine, the rotor, the combustion chamber 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 present invention, the acquired input parameters set for each component model of the gas turbine may include setting parameters input from the outside, and also include parameters input to other models other than the 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 calculation, 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 changing of the characteristic parameters of the compressor model may be changing of a flow-rotation speed-pressure ratio interpolation table of the compressor model, that is, changing of a corresponding relation between the outlet flow of the compressor and the rotation speed and the pressure ratio of the compressor, and changing of an efficiency-rotation speed-flow ratio interpolation table of the compressor model, that is, changing of a corresponding relation between the compression efficiency of the compressor and the rotation speed and the outlet flow of the compressor, and further, the characteristic operation may be performed again in combination with the input parameters corresponding to the compressor model and the changed characteristic parameters of the compressor model, so as 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 compressor cout Inlet air pressure P of compressor cin Inlet air temperature T of compressor cin And a compressor speed n.
In the embodiment of the present invention, as 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 performs operation, the input parameter corresponding to the compressor model may be first 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 c For compressor outlet air flow, η, without taking into account thermal effects c Is the adiabatic compression efficiency value of the compressor,
for the pressure ratio of the compressor, in or on>
Converted into a rotational speed.
And then, inputting the parameters obtained by the operation of the characteristic calculation module in the compressor model into a thermodynamic calculation module of the compressor model for calculation.
In the embodiment of the invention, the calculation process of the thermodynamic calculation module in the compressor model mainly adopts a heat-variable ratio method for calculation, and the specific calculation process comprises the following steps:
s11: by using a specific entropy function methodAccording to compressor inlet air temperature T cin Inlet air pressure P of compressor cin And compressor outlet air pressure P cout And obtaining the specific entropy of the inlet of the compressor and the enthalpy value of the inlet of the compressor, and obtaining the outlet temperature of the isentropic compression of the compressor according to the inlet specific entropy and an entropy-temperature interpolation table of air.
S12: obtaining the temperature of the outlet of the compressor isentropic compression according to the S11, and obtaining the specific enthalpy value of the compressor isentropic compression outlet according to the temperature-enthalpy interpolation table of the 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 specific enthalpy increase of the isentropic compression obtained in the step S13 by the compression efficiency of the compressor to obtain the specific enthalpy increase 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 air;
s16: multiplying the specific enthalpy value of the actual compression process outlet of the compressor calculated in the S15 step 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 compressor c 。
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 compressor cout Temperature T of air at outlet of air compressor cout And compressor power consumption N c And may be via Displ as set forth in FIG. 3ay-Display8 looks at the simulation sub-result of the compressor model.
In another optional 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-falling pressure 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 changed characteristic parameter of the 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 P tout Turbine inlet gas pressure P tin Turbine inlet gas temperature T tin Air-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 operated, the turbine outlet gas pressure P in the input parameters corresponding to the turbine model can be firstly calculated tout Turbine inlet gas pressure P tin Turbine inlet gas temperature T tin And 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 content of the first and second substances,
to convert the flow rate of the turbine into>
For turbine reduction of rotational speed, η T Denotes the turbine efficiency,. Pi T Is 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 obtained T Turbine efficiency η T And turbine inlet gas flow G tin And then the three parameters obtained after the characteristic calculation and the oil-gas ratio f in the corresponding input parameters of the turbine model are input into a thermodynamic calculation module of the turbine model for thermodynamic calculation to obtain the turbine output power N t Turbine outlet temperature T tout And turbine outlet gas flow rate G tout . The process of turbine thermodynamic calculations includes:
s21: according to the temperature T of the turbine inlet gas tin And other characteristic parameters in the turbine model to combine equations (5) and (6) to calculate the enthalpy and log pressure ratio of the inlet gas:
h gin ＝f(T tin ) Formula (5)
lnπ in ＝f(T tin ) Formula (6)
Wherein, ln pi in And ln pi out Representing 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):
lnπ out ＝lnπ in -R g lnπ T formula (7)
Wherein R is g Representing the gas constant of the combustion gas, as the molar gas constant R * With combustion gasesMolar mass Mg ratio.
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 ：
h out ＝f(lnπ out ) Formula (8)
S24: according to the efficiency η of the turbine T And formula (9) determining the actual enthalpy h of the turbine outlet gas outs ：
h out ＝h in -(h in -h outs )η T Formula (9)
S25: determining the temperature T of the turbine outlet gas by combining the formula (10) through the gas thermodynamic property relation tout ：
T tout ＝f(h out ) Formula (10)
S26: finally, the actual output power N of the turbine is calculated by combining the formula (11) t ：
N t ＝G tin (h in -h out ) 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 simulation sub-result of the turbine model 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 G tin Turbine outlet gas flow G tout Turbine outlet gas temperature T tout And turbine output work N t 。
In the embodiment of the present invention, in addition to setting the component model, the component model of the gas turbine further includes a combustor model corresponding to the combustor component, and referring to fig. 5, the input parameter corresponding to the combustor model includes the combustor outlet gas flow G bout Combustion chamber inlet compressed air flow rate G bin Temperature T of compressed air at inlet of combustion chamber in Fuel flow rate G f In order to conveniently check the operation 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 pressure P of the compressed air at the inlet of the combustion chamber bin And combustion of coalCombustion chamber outlet gas pressure P bout Temperature T of gas at outlet of combustion chamber bout And 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, and the simulation sub-results of the combustion chamber model are obtained through the four calculation regions, 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 P bout As 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 P bin As a result of the simulation, the combustion chamber outlet gas temperature calculation module is used to realize the calculation process of the formula (14) to obtain the combustion chamber outlet gas temperature T bout 。
P bout ＝(1-K b )P in P bout ＝(1-k)P bin Formula (14)
Wherein V is the volume of the combustion chamber eta B For combustion efficiency of the combustion chamber, G gout Gas flow at the outlet of the combustion chamber, G gin Gas flow at the inlet of the combustion chamber, G f For the fuel flow into the combustion chamber, h fin Is the specific enthalpy value, h, of the fuel entering the combustion chamber ain Is the specific enthalpy value, h, of the combustion chamber inlet air gout Is the specific enthalpy value, H, of the combustion gas at the outlet of the combustion chamber u Is the heat value of combustion of the fuel, C pg Is the isobaric specific heat capacity of the gas in the combustion chamber, k is the specific heat ratio of the gas, P bout For combustion chamber outlet gas pressureForce, P bin For compressing the air pressure at the combustion chamber inlet, K b Is 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, N l The 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 T ain Compressed air pressure P at outlet of heat regenerator aout Gas temperature T at inlet of heat regenerator gin Gas pressure P at outlet of heat regenerator gout Compressed air flow G at inlet of heat regenerator ain Gas flow G at inlet of heat regenerator gin The 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 simulation sub-result output by the heat regenerator model comprises the compressed air temperature T at the outlet of the heat regenerator aout Regenerator inlet compressed air pressure P ain Gas pressure P at inlet of heat regenerator gin And the temperature T of the gas at the outlet of the heat regenerator gout 。
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 the air passes 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-temperature-fuel gas enthalpy value interpolation table, an air temperature-enthalpy value interpolation table, an air enthalpy value-temperature interpolation table, a fuel gas enthalpy value-oil-gas ratio-fuel gas temperature interpolation table, and the like.
Q g ＝Q a Formula (16)
Q g ＝G gin (h in -h out ) Formula (17)
h = F (F, T) equation (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, G gin The flow of gas at the inlet of the heat regenerator, h in Is the enthalpy value, h, of the gas at the inlet of the regenerator out The enthalpy value of the gas at the outlet of the heat regenerator is f, the oil-gas ratio is f, the gas temperature is 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 the set component models 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, 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 the actual object 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, the characteristic parameters set in the 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 until 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 refer to the description of the above method embodiment, and the repeated parts 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 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 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 a second simulation result is obtained and the expected result matches:
changing characteristic parameters in the setting part 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.
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 the 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 used 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: combustion chamber outlet gas flow, combustion chamber inlet compressed air temperature and fuel flow;
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;
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, which includes 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 which, 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 is 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 also 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 the 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 used 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 of any of claims 1-4, 6, 7, wherein the component models of the gas turbine further include rotor models corresponding to the rotor components;
the rotor model comprises an output sub-interface which is used for outputting a simulation sub-result corresponding to the rotor 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 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.
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 inputting the acquired input parameters into the corresponding component models respectively so as to carry out operation 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 the determining module is used for determining whether the simulation result is matched with an expected result, and if so, 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.
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.
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