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
- compressor
- gas turbine
- 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
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)
- Control Of Turbines (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (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 present invention relates to gas turbine fields more particularly to a kind of emulation mode of gas turbine, device and storage to be situated between
Matter.
Background technique
Gas turbine (Gas Turbine) is gas continuously to flow as working medium impeller high speed rotation, by fuel
Energy conversion be useful work internal combustion type dynamic power machine, with the development of industry, the application field of gas turbine is also very wide
It is general, electric power required in the national economic development and the energy can not only be conveyed and distributed or national defence in
Important application equipment.It follows that the operating condition of gas turbine is also increasingly complicated with the extension of its application field, therefore,
Particularly significant is also shown to the optimization of gas turbine overall performance.However by gas turbine physical components tested come
Miniature gas turbine overall performance is adjusted, not only experimental period is long, and experimental cost is also high, it is also possible to there are problems that experiment safety.
Summary of the invention
It is micro- for reducing the embodiment of the invention provides a kind of emulation mode of gas turbine, device and storage medium
The period of type gas turbine performance optimization experiment and cost, improve the safety of experiment.
On the one hand, the embodiment of the invention provides a kind of emulation modes of gas turbine, comprising:
Obtain the input parameter being arranged for each partial model of gas turbine；Each partial model is pre-set use
It is provided in the model for the operational process for emulating the gas turbine corresponding component, each partial model for the partial model
Realize the characterisitic parameter of its characteristic operation；
The input parameter that will acquire inputs corresponding each partial model respectively, to combine in corresponding each partial model
Characterisitic parameter carries 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 characteristic of each partial model is joined
Number is the actual characteristic parameter in its corresponding component, to use the corresponding component of actual characteristic state modulator gas turbine
Operating.
Optionally, however, it is determined that the simulation result and expected result mismatch, then following operation are executed, until obtaining
The second simulation result matched with expected result:
Change the characterisitic parameter in set parts model；
In conjunction with the characterisitic parameter after the corresponding input parameter of the set parts model and change, operation is re-started, is obtained
Obtain the second simulation result of the operational process of the gas turbine.
Optionally, the set parts model is the corresponding compressor model of compressor part of the gas turbine, institute
The characterisitic parameter in change set parts model is stated, specifically:
Change the corresponding relationship of blower outlet flow and rotating speed of gas compressor, compressor pressure ratio；And
Change the corresponding relationship of compressor compression efficiency and rotating speed of gas compressor, blower outlet flow.
Optionally, the compressor model also sets up the characterisitic parameter for carrying out compressor thermodynamic computing, characteristic ginseng
Number is configured according to variable specific heat algorithm in advance.
Optionally, the corresponding input parameter of the compressor model includes: that blower outlet air pressure, compressor enter
Mouth air pressure, compressor inlet air themperature and rotating speed of gas compressor；
The compressor model includes output sub-interface, for exporting corresponding emulation of compressor model as a result, this is imitative
Very sub- result includes following one or more: blower outlet air mass flow, blower outlet air themperature and compressor disappear
Wasted work rate.
Optionally, the set parts model be the gas turbine the corresponding turbine model of turbine part, it is described more
Change the characterisitic parameter in set parts model, specifically:
Change the corresponding relationship of turbine outlet flow and secondary speed, turbine pressure ratio；And
Change the corresponding relationship of turbo-compressor efficiency and secondary speed, turbine outlet flow.
Optionally, the corresponding input parameter of the turbine model includes: turbine outlet gaseous-pressure, turbine inlet combustion gas
Pressure, Turbine Inlet Gas Temperature, oil-gas ratio and secondary speed；
The turbine model includes output sub-interface, for exporting corresponding emulation of turbine model as a result, the emulation is sub
As a result include following one or more: turbine inlet gas flow, turbine outlet gas flow, turbine outlet fuel gas temperature with
And turbine output rate.
It optionally, include combustion chamber model corresponding with combustion chamber components in the partial model of the gas turbine；It is described
The input parameter of combustion chamber model includes: that combustor exit gas flow, entry of combustion chamber compressed air require, combustion chamber enter
Mouth compressed air temperature, fuel flow rate；
The combustion chamber model includes output sub-interface, for exporting emulation knot corresponding with the combustion chamber model
Fruit；
The sub- result of the emulation includes following one or more: entry of combustion chamber compressed air pressure, combustor exit combustion gas
Pressure, combustor exit fuel gas temperature, oil-gas ratio.
Optionally, the partial model of the gas turbine further includes rotator model corresponding with rotor part；
The rotator model includes output sub-interface, for export corresponding with rotor submodel emulation it is sub as a result,
The sub- result of emulation includes at least rotor speed.
Optionally, the partial model of the gas turbine further includes regenerator model corresponding with regenerator component；It is described
The input parameter of regenerator model includes: regenerator inlet compression air themperature, regenerator outlet compressed air pressure, backheat
Device entrance fuel gas temperature, regenerator outlet gas pressure, regenerator inlet compression air mass flow, regenerator entrance gas flow,
Oil-gas ratio；
The regenerator model includes output sub-interface, for exporting emulation knot corresponding with the regenerator model
Fruit, the sub- result of emulation includes following one or more: it is empty that regenerator exports compressed air temperature, regenerator inlet compression
Atmospheric pressure, regenerator entrance gaseous-pressure, regenerator outlet gas temperature.
On the one hand, the embodiment of the present invention also provides a kind of simulator of gas turbine, comprising:
Module is obtained, for obtaining the input parameter for being directed to each partial model of gas turbine and being arranged；Each partial model is
The model of the pre-set operational process for being used to emulate the gas turbine corresponding component, the interior setting of each partial model are useful
The characterisitic parameter of its characteristic operation is realized in the partial model；
Computing module, the input parameter for will acquire input corresponding each partial model respectively, corresponding each to combine
Characterisitic parameter carries out operation in model, obtains the first simulation result of the operational process of the gas turbine；
Determining module, for determining whether the simulation result matches with expected result, if so, determining each component
The characterisitic parameter of model is the actual characteristic parameter in its corresponding component, to use the actual characteristic state modulator combustion gas wheel
The corresponding component operating of machine.
Optionally, the determining module is also used to, however, it is determined that the simulation result and expected result mismatch, then hold
The following operation of row, until the second simulation result of acquisition is matched with expected result:
Change the characterisitic parameter in set parts model；
In conjunction with the characterisitic parameter after the corresponding input parameter of the set parts model and change, operation is re-started, is obtained
Obtain the second simulation result of the operational process of the gas turbine.
Optionally, described device further includes change module, and the change module is used for:
The set parts model is the corresponding compressor model of compressor part of the gas turbine, the change
Characterisitic parameter in set parts model, specifically:
Change the corresponding relationship of blower outlet flow and rotating speed of gas compressor, compressor pressure ratio；And
Change the corresponding relationship of compressor compression efficiency and rotating speed of gas compressor, blower outlet flow.
Optionally, the compressor model also sets up the characterisitic parameter for carrying out compressor thermodynamic computing, characteristic ginseng
Number is configured according to variable specific heat algorithm in advance.
Optionally, the corresponding input parameter of the compressor model includes: that blower outlet air pressure, compressor enter
Mouth air pressure, compressor inlet air themperature and rotating speed of gas compressor；
The compressor model includes output sub-interface, for exporting corresponding emulation of compressor model as a result, this is imitative
Very sub- result includes following one or more: blower outlet air mass flow, blower outlet air themperature and compressor disappear
Wasted work rate.
Optionally, the set parts model be the gas turbine the corresponding turbine model of turbine part, it is described more
Change the characterisitic parameter in set parts model, specifically:
Change the corresponding relationship of turbine outlet flow and secondary speed, turbine pressure ratio；And
Change the corresponding relationship of turbo-compressor efficiency and secondary speed, turbine outlet flow.
Optionally, the corresponding input parameter of the turbine model includes: turbine outlet gaseous-pressure, turbine inlet combustion gas
Pressure, Turbine Inlet Gas Temperature, oil-gas ratio and secondary speed；
The turbine model includes output sub-interface, for exporting corresponding emulation of turbine model as a result, the emulation is sub
As a result include following one or more: turbine inlet gas flow, turbine outlet gas flow, turbine outlet fuel gas temperature with
And turbine output rate.
It optionally, include combustion chamber model corresponding with combustion chamber components in the partial model of the gas turbine；It is described
The input parameter of combustion chamber model includes: that combustor exit gas flow, entry of combustion chamber compressed air require, combustion chamber enter
Mouth compressed air temperature, fuel flow rate；
The combustion chamber model includes output sub-interface, for exporting emulation knot corresponding with the combustion chamber model
Fruit；
The sub- result of the emulation includes following one or more: entry of combustion chamber compressed air pressure, combustor exit combustion gas
Pressure, combustor exit fuel gas temperature, oil-gas ratio.
Optionally, the partial model of the gas turbine further includes rotator model corresponding with rotor part；
The rotator model includes output sub-interface, for export corresponding with rotor submodel emulation it is sub as a result,
The sub- result of emulation includes at least rotor speed.
Optionally, the partial model of the gas turbine further includes regenerator model corresponding with regenerator component；It is described
The input parameter of regenerator model includes: regenerator inlet compression air themperature, regenerator outlet compressed air pressure, backheat
Device entrance fuel gas temperature, regenerator outlet gas pressure, regenerator inlet compression air mass flow, regenerator entrance gas flow,
Oil-gas ratio；
The regenerator model includes output sub-interface, for exporting emulation knot corresponding with the regenerator model
Fruit, the sub- result of emulation includes following one or more: it is empty that regenerator exports compressed air temperature, regenerator inlet compression
Atmospheric pressure, regenerator entrance gaseous-pressure, regenerator outlet gas temperature.
On the one hand, the embodiment of the present invention also provides a kind of simulator of gas turbine, including at least one processor,
And at least one processor, wherein the memory is stored with computer program, when described program is held by the processor
When row, so that the step of processor executes the emulation mode of gas turbine provided in an embodiment of the present invention.
On the one hand, storage medium described in a kind of storage medium provided in an embodiment of the present invention is stored with computer instruction, when
When the computer instruction is run on computers, so that computer executes the imitative of gas turbine provided in an embodiment of the present invention
The step of true method.
In embodiments of the present invention, the input parameter of each partial model setting for gas turbine can be first obtained,
In each component be pre-set to be set for emulating the model of the operational process of gas turbine corresponding component, in each partial model
The input parameter that is equipped with the characterisitic parameter for realizing its characteristic operation for the partial model, and will acquire inputs corresponding respectively
Each partial model obtains the first of the operational process of gas turbine to combine characterisitic parameter in corresponding each model to carry out operation
Simulation result, and then may determine that the simulation result of acquisition is to match with expected result, if it does, then can determine each
The characterisitic parameter of partial model is the actual parameter in corresponding component, and then the actual characteristic state modulator combustion gas can be used
The corresponding component operating of turbine, reduces the period to gas turbine full-scale investigation, reduces experimental cost, and the peace of lifting test
Quan Xing.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, embodiment will be retouched below
Attached drawing needed in stating is briefly described, it should be apparent that, the accompanying drawings in the following description is only of the invention one
A little embodiments.
Fig. 1 is a kind of emulation mode flow chart of gas turbine provided in an embodiment of the present invention；
Fig. 2 is a kind of structure chart of gas turbine engine systems provided in an embodiment of the present invention；
Fig. 3 is compressor part model schematic provided in an embodiment of the present invention；
Fig. 4 is turbine part pattern diagram provided in an embodiment of the present invention；
Fig. 5 provides combustion chamber components model schematic for the embodiment of the present invention；
Fig. 6 provides combustion chamber components model schematic internal view for the embodiment of the present invention；
Fig. 7 provides rotator model schematic diagram for the embodiment of the present invention；
Fig. 8 provides regenerator partial model schematic diagram for the embodiment of the present invention；
Fig. 9 provides the simulator schematic diagram of gas turbine for the embodiment of the present invention；
Figure 10 provides the simulator schematic diagram of another gas turbine for the embodiment of the present invention.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical solution of the present invention is clearly and completely described, it is clear that described embodiment is skill of the present invention
A part of the embodiment of art scheme, instead of all the embodiments.Based on the embodiment recorded in present specification, this field
Those of ordinary skill's every other embodiment obtained without creative efforts, belongs to skill of the present invention
The range of art scheme protection.
In the prior art, as described above, the performance of miniature gas turbine optimizes mainly by gas turbine physical components
It is tested to obtain optimization data, and then miniature gas turbine physical components are adjusted, however, to micro-gas-turbine
Machine physical components are tested to adjust miniature gas turbine overall performance, and not only experimental period is long, and experimental cost is also high, also
There may be experiment safety problems.
Based on this, the embodiment of the invention provides a kind of emulation mode of gas turbine, this method can be obtained first and is directed to
The input parameter of each partial model setting of gas turbine, wherein each component is pre-set for emulating gas turbine pair
The model of the operational process of component is answered, the characteristic for realizing its characteristic operation for the partial model is provided in each partial model
Parameter, and the input parameter that will acquire inputs corresponding each partial model respectively, to combine characterisitic parameter in corresponding each model
Operation is carried out, the first simulation result of the operational process of gas turbine is obtained, and then may determine that the simulation result of acquisition and pre-
Phase the result is that matching, if it does, then can determine each partial model characterisitic parameter be corresponding component in practical ginseng
Number, and then the corresponding component operating of the actual characteristic state modulator gas turbine can be used, it reduces in kind to gas turbine real
The period tested reduces experimental cost, and the safety of lifting test.
Referring to FIG. 1, being a kind of emulation mode of gas turbine provided in an embodiment of the present invention, comprising:
Step 101: obtaining the input parameter being arranged for each partial model of gas turbine.
Wherein, each partial model is pre-set for emulating the model of the operational process of gas turbine corresponding component,
The characterisitic parameter that its characteristic operation is realized for the partial model is provided in each partial model.
Gas turbine in the embodiment of the present invention can be miniature gas turbine and be also possible to other kinds of combustion gas wheel
Machine is also possible to single-rotor gas turbine and multi-shaft gas turbine, herein by taking single-rotor gas turbine as an example.
In specific practice process, as shown in Fig. 2, gas turbine engine systems include compressor, turbine, rotor, burning
Multiple components such as room, regenerator, load, bromine cooling machine build the model of gas turbine in the embodiment of the present invention mainly according to combustion
Component is built one by one from front to back in the direction of air-flow in gas-turbine, finally connects relevant parameter between all parts model
Get up, ultimately form the model of a gas turbine complete machine, i.e., respectively compressor, turbine, rotor, combustion chamber, regenerator this
Five main components build compressor model, turbine model, rotator model, combustion chamber model, regenerative chamber model, and by this five
Relevant parameter connects between a model.
Wherein, the characterisitic parameter for realizing characteristic operation is additionally provided in this five simulation models, for example, compressor
Flow-revolving speed-pressure ratio the interpolation table for realizing the compressor of compressor model characteristic operation, efficiency-revolving speed-are provided in model
Flow interpolation table etc. is provided with the flow-revolving speed-blow down ratio interpolation table for realizing characteristic operation, efficiency-revolving speed-in turbine model
Gas flow interpolation table etc..
In embodiments of the present invention, can using MATLAB, Simulink or other can be used for emulate softwares into
Row simulation modeling, in the embodiment of the present invention for carrying out simulation modeling based on all parts of the Simulink to gas turbine
It is specifically described.
In embodiments of the present invention, the input parameter of each partial model setting for gas turbine of acquisition has multiple,
It may include the parameter set from external world's input, further include other moulds inputted again after the output of a certain model except the model
The parameter of type.
Step 102: the input parameter that will acquire inputs corresponding each partial model respectively, to combine corresponding each component
Characterisitic parameter in model carries out operation, obtains the first simulation result of the operational process of gas turbine.
In embodiments of the present invention, after obtaining input parameter, the input parameter that can be will acquire inputs and input respectively
In the partial model of the corresponding gas turbine of parameter, the partial model for obtaining input parameter can be according to the spy being arranged in component
Property parameter to input parameter carry out characteristic operation, and then it is available emulation gas turbine operation process the first simulation result,
The simulation result may include the output parameter of gas turbine whole machine model, such as the efficiency of gas turbine, the revolving speed of gas turbine
Deng.
Step 103: determining whether the first simulation result matches with expected result.
In embodiments of the present invention, the simulation result of acquisition is gas turbine components models coupling gas turbine component
Actual characteristic parameter carry out characteristic operation and obtain, so the simulation result obtained can really reflect actual combustion gas wheel
The operating condition of machine complete machine or all parts in turn can be by the simulation result of acquisition and the expected institute of actual gas turbine
The operation result to be reached, i.e. expected result are compared, with the working order of the actual gas turbine of determination.
When determining the first simulation result and expected result matches, step 104 is executed, when determining that first is imitative
When true result and expected result mismatch, 105 are thened follow the steps.
Step 104: the characterisitic parameter for determining each partial model is the actual characteristic parameter in its corresponding component, to make
With the corresponding component operating of the actual characteristic state modulator gas turbine.
In embodiments of the present invention, it when the first simulation result of acquisition is matched with expected result, then can determine each
The characterisitic parameter of partial model is the actual characteristic parameter of the corresponding component of each partial model, and then can be directly using practical
The corresponding component operating of characterisitic parameter control gas turbine, obtain control compared to being tested to gas turbine material object
For the characterisitic parameter of each component of gas turbine operating, reduce the period to gas turbine full-scale investigation, and reduce reality
Test cost.
Step 105: the characterisitic parameter in change set parts model, and it is corresponding defeated in conjunction with the set parts model
Characteristic parameter after entering parameter and change, re-starts operation, obtains the second simulation result of the operational process of gas turbine.
In embodiments of the present invention, when the first simulation result of acquisition and expected result mismatch, it can change and set
Determine the characterisitic parameter in partial model, and then the characterisitic parameter input corresponding with set parts model after change can be joined
Number combines, and re-starts characteristic operation, obtains the second simulation result of the operational process of emulation gas turbine.
In turn, the second simulation result of acquisition can be compared with gas turbine expected result, determines that second is imitative
Whether true result matches with expected result, if it does, then determining that the characterisitic parameter after change is the corresponding combustion of the characterisitic parameter
The actual characteristic parameter of gas turbine component, if it does not match, continue the characterisitic parameter changed in set parts model, until
Obtained simulation result matches with expected result, so needing each component to gas turbine compared in full-scale investigation
Structure modify after again by carry out full-scale investigation for, use Gas Turbine Simulation model carry out analog simulation test reality
Test that the period is shorter, and cost is lower, safety is also higher.
As an alternative embodiment, in embodiments of the present invention, set parts model can be gas turbine portion
The corresponding compressor model of compressor part in part, it can change the characterisitic parameter of compressor model, wherein compressor mould
The characterisitic parameter of type includes compressor mass flow-revolving speed-pressure ratio interpolation table, efficiency-revolving speed-flow interpolation table, the temperature of air
Degree-enthalpy interpolation table, temperature-entropy interpolation table of air, entropy-temperature interpolation table of air, enthalpy-temperature interpolation table of air etc..
So flow-revolving speed-pressure ratio that the characterisitic parameter for changing compressor model can be change compressor model is inserted
It is worth table, the i.e. corresponding relationship of change blower outlet flow and rotating speed of gas compressor, compressor pressure ratio, and change compressor mould
Efficiency-revolving speed-flow interpolation table of type, i.e. pair of change compressor compression efficiency and rotating speed of gas compressor, blower outlet flow
It should be related to, and then can be in conjunction with the characterisitic parameter of the compressor model after the corresponding input parameter of compressor model and change, weight
It is new to carry out characteristic operation, obtain the second simulation result of gas turbine operation process.
Wherein, the corresponding input parameter of compressor model includes blower outlet air pressure Pcout, compressor inlet it is empty
Atmospheric pressure Pcin, compressor inlet air themperature TcinAnd rotating speed of gas compressor n.
In embodiments of the present invention, as shown in figure 3, compressor model includes property calculation module and thermodynamic computing module
Two computing modules can be first by the corresponding input parameter input characteristics meter of compressor model when compressor model carries out operation
Calculate module carry out characteristic operation, can be based on formula (1) and formula (2), using compressor flow-revolving speed-pressure ratio interpolation table with
Efficiency-revolving speed-flow interpolation table acquires the rate of discharge (G in Fig. 3 of compressor modelcin), the adiabatic compression of compressor effect
Rate value (EFC in Fig. 3) and compressor pressure ratio (Pi in Fig. 3):
Wherein, GcNot consider blower outlet air mass flow when fuel factor, ηcFor the adiabatic compression efficiency of compressor
Value,For compressor pressure ratio,For corrected spool speed.
It in turn, then will be through the heat of property calculation module operation obtains in compressor model parameter input compressor model
Power computing module carries out operation.
In embodiments of the present invention, the calculating process of thermodynamic computing module mainly uses no-load voltage ratio thermal method in compressor model
It is calculated, specific calculating process includes:
S11: it uses than Entropy Function Method, according to compressor inlet air themperature Tcin, compressor inlet air pressure PcinWith
Blower outlet air pressure Pcout, obtain the specific entropy of compressor inlet and the enthalpy of compressor inlet, according to import specific entropy and
The entropy of air-temperature interpolation table, obtains the outlet temperature of compressor isentropic Compression.
S12: obtaining the outlet temperature of compressor isentropic Compression according to S11, is obtained according to the temperature of air-enthalpy interpolation table
The ratio enthalpy of compressor isentropic Compression outlet；
S13: the ratio enthalpy for the compressor isentropic Compression outlet that S11 is obtained is subtracted to the ratio enthalpy of compressor inlet, is obtained
The specific enthalpy of compressor isentropic Compression increases；
S14: the specific enthalpy of the obtained isentropic Compression of S13 is increased and obtains compressor actual compression divided by compressor compression efficiency
The specific enthalpy of process increases；
S15: the specific enthalpy that S14 is calculated increases the ratio enthalpy of upper compressor inlet, obtains compressor actual compression process and goes out
The ratio enthalpy of mouth obtains practical compressor delivery temperature according to practical outlet than the enthalpy of enthalpy and air-temperature interpolation table；
S16: it by the ratio enthalpy of the S15 compressor actual compression procedure exit calculated multiplied by compressor mass flow, obtains
Power needed for compressor, wherein power needed for compressor is the consumption power N of compressorc。
In embodiments of the present invention, each component checked in gas turbine for convenience correspond to model emulation son as a result,
It is both provided with output sub-interface in the corresponding model of gas turbine components, for exporting corresponding emulation of each partial model
As a result, can check that each component corresponds to emulation of model as a result, convenient to each partial model by exporting sub-interface in turn
Operating status is observed.So being provided with output for emulating sub- result for exporting compressor model in compressor model
Interface, wherein the sub- result of emulation of the output sub-interface output of compressor model includes blower outlet air mass flow Gcout、
Blower outlet air themperature TcoutAnd compressor consumes power Nc, and can be by the Display- that is arranged in such as Fig. 3
Display8 checks the sub- result of the emulation of compressor model.
Another optional embodiment, in embodiments of the present invention, set parts model can also be gas turbine portion
The corresponding turbine model of turbine part in part, i.e., can also change the characterisitic parameter of turbine model, wherein the spy of turbine model
Property parameter includes turbine gas flow-revolving speed-blow down ratio interpolation table, efficiency-revolving speed-gas flow interpolation table, the temperature of combustion gas
Degree-enthalpy interpolation table, temperature-entropy interpolation table of combustion gas, entropy-temperature interpolation table of combustion gas, enthalpy-temperature interpolation table of combustion gas etc..
So changing the characterisitic parameter of turbine model, change turbine gas flow-revolving speed-blow down ratio interpolation can be
Table, the i.e. corresponding relationship of change turbine outlet flow and secondary speed, turbine pressure ratio, and the efficiency-of change turbine model turn
Speed-gas flow interpolation table, the i.e. corresponding relationship of change turbo-compressor efficiency and secondary speed, turbine outlet flow, Jin Erke
To combine the characterisitic parameter of the turbine model after the corresponding input parameter of turbine model and change, characteristic operation is re-started, is obtained
To the second simulation result of gas turbine operation process.
Wherein, turbine model to input parameter include turbine outlet gaseous-pressure Ptout, turbine inlet gaseous-pressure
Ptin, Turbine Inlet Gas Temperature Ttin, oil-gas ratio f and secondary speed n.
In embodiments of the present invention, as shown in figure 4, turbine model also includes property calculation module and thermodynamic computing module
Two computing modules.It, can be first by the turbine outlet in the corresponding input parameter of turbine model when turbine model carries out operation
Gaseous-pressure Ptout, turbine inlet gaseous-pressure Ptin, Turbine Inlet Gas Temperature TtinAnd secondary speed n inputs turbine mould
The property calculation module of type carries out characteristic calculating, i.e., carries out characteristic calculating based on formula (3) and formula (4).
Wherein,For turbine corrected flow,Revolving speed, η are converted into for turbineTIndicate turbine efficiency, πTFor whirlpool
It takes turns expansion ratio (turbine blow down ratio).
Further, after being calculated by the characteristic of property calculation module, available turbine blow down ratio πT, turbine efficiency ηT
And turbine inlet gas flow Gtin, and then these three parameters and the corresponding input of turbine model are obtained after characteristic is calculated
Thermodynamic computing is carried out in the thermodynamic computing module of oil-gas ratio f input turbine model in parameter, obtains turbine output rate Nt,
Turbine-exit temperature TtoutAnd turbine outlet gas flow Gtout。
The process of turbine thermodynamic computing includes:
S21: according to the temperature T of turbine inlet combustion gastinAnd other characterisitic parameters in turbine model combine formula
(5) and formula (6) calculates the enthalpy and logarithm pressure ratio of inlet gas:
hgin=f (Ttin) formula (5)
lnπin=f (Ttin) formula (6)
Wherein, ln πinWith ln πoutIndicate turbine inlet and outlet than entropy function (being directed to 1kg working medium).
S22: according to turbine inlet combustion gas expansion ratio, the logarithm expansion ratio of turbine outlet is determined in conjunction with formula (7):
lnπout=ln πin-RglnπTFormula (7)
Wherein, RgIt indicates the gas constant of combustion gas, is molar gas constant R*With the ratio of the molal weight Mg of combustion gas.
S23: the enthalpy h of combustion gas after combustion gas constant entropy adiabatic expansion in turbine is determined according to formula (8)out:
hout=f (ln πout) formula (8)
S24: according to the efficiency eta of turbineTAnd formula (9), determine the practical enthalpy h of turbine outlet combustion gasouts:
hout=hin-(hin-houts)ηTFormula (9)
S25: by combustion gas thermodynamic properties relationship, the temperature T of turbine outlet combustion gas is determined in conjunction with formula (10)tout:
Ttout=f (hout) formula (10)
S26: finally formula (11) is combined to calculate the actual output power N of turbinet:
Nt=Gtin(hin-hout) formula (11)
In embodiments of the present invention, the operating status of turbine model is checked for convenience, is provided with and is used in turbine model
Output turbine model emulates the output sub-interface of sub- result, wherein the sub- result of emulation of the output sub-interface output of turbine model
Including turbine inlet gas flow Gtin, turbine outlet gas flow Gtout, turbine outlet fuel gas temperature TtoutAnd turbine output
Function Nt。
It in embodiments of the present invention, further include combustor section in the partial model of gas turbine in addition to set parts model
The corresponding combustion chamber model of part, referring to Fig. 5, the corresponding input parameter of combustion chamber model includes combustor exit gas flow
Gbout, entry of combustion chamber compressed air require Gbin, entry of combustion chamber compressed air temperature Tin, fuel flow rate Gf, look into for convenience
It sees the operating condition of combustion chamber model, output sub-interface is also equipped in combustion chamber model, for exporting the imitative of combustion chamber model
Very son is as a result, the sub- result of emulation of combustion chamber model output includes combustion chamber import compressed air pressure Pbin, combustor exit
Gaseous-pressure Pbout, combustor exit fuel gas temperature Tbout, oil-gas ratio f.
Specifically, combustion chamber model internal structure can be divided into four zonings according to different functions, referring to Fig. 6,
Area, which is calculated, by this four obtains emulation of combustion chamber model as a result, this four computing modules are that oil-gas ratio calculates mould respectively
Block, combustor exit gaseous-pressure computing module, entry of combustion chamber air pressure calculate module, combustor exit fuel gas temperature
Computing module.Combustor exit gaseous-pressure computing module is gone out for realizing the calculating process of formula (12) with obtaining combustion chamber
Mouth gaseous-pressure PboutThis emulation is as a result, entry of combustion chamber air pressure calculates module for realizing the meter of formula (13)
Calculation process, to obtain entry of combustion chamber air pressure PbinThis emulation is as a result, combustor exit fuel gas temperature computing module
For realizing the calculating process of formula (14), to obtain combustor exit fuel gas temperature Tbout。
Pbout=(1-Kb)PinPbout=(1-k) PbinFormula (14)
Wherein, V is the volume of combustion chamber, ηBFor the efficiency of combustion of combustion chamber, GgoutThe gas flow of-combustor exit,
GginFor the gas flow of combustion chamber import, GfFor the fuel flow rate for entering combustion chamber, hfinFor the ratio of the fuel of entrance combustion chamber
Enthalpy, hainFor the ratio enthalpy of entry of combustion chamber air, hgoutFor the ratio enthalpy of combustor exit combustion gas, HuFor fuel combustion
Calorific value, CpgConstant pressure specific heat for the indoor fuel gas that burns is held, and k is the specific heat ratio of combustion gas, PboutFor combustor exit gaseous-pressure,
PbinFor combustion chamber import compressed air pressure, KbFor combustion-chamber pressure loss coefficient.
It in embodiments of the present invention, further include rotator model in the partial model of gas turbine, referring to Fig. 7, the rotor mould
It can use compressor in type and its bearing power balance principle solve the revolving speed of rotor, i.e., obtain revolving speed by formula (15)
n。
Wherein, the partial model of characterisitic parameter is changed.For the inverse of rotor moment of inertia, NlFor compressor and load
Total consumed power.
It in embodiments of the present invention, further include the corresponding regenerator model of regenerator component in gas turbine component model,
Referring to Fig. 8, the corresponding input parameter of regenerator model includes regenerator inlet compression air themperature Tain, regenerator outlet compression
Air pressure Paout, regenerator entrance fuel gas temperature Tgin, regenerator outlet gas pressure Pgout, regenerator inlet compression air
Flow Gain, regenerator entrance gas flow Ggin, oil-gas ratio f, check the operating condition of regenerator model, regenerator for convenience
Output sub-interface is also equipped in model, for exporting emulation of regenerator model as a result, the emulation that regenerator model exports
Sub- result includes regenerator outlet compressed air temperature Taout, regenerator inlet compression air pressure Pain, regenerator entrance combustion
Atmospheric pressure Pgin, regenerator outlet gas temperature Tgout。
Specifically, to improve the speed and stability of simulation calculating, when regenerator model carries out characteristic operation, Ke Yili
With the conservation of energy (ideally), i.e. combustion gas is equal to air by inhaling after regenerator by the heat that goes out released after regenerator
The heat of receipts, so can according to the characterisitic parameter being arranged in regenerator model such as oil-gas ratio-temperature-combustion gas enthalpy interpolation table,
The temperature of air-enthalpy interpolation table, enthalpy-temperature interpolation table of air, combustion gas enthalpy-oil-gas ratio-fuel gas temperature interpolation table
Deng the sub- result of emulation of regenerator model can be obtained in conjunction with formula (16), formula (17) and formula (18).
Qg=QaFormula (16)
Qg=Ggin(hin-hout) formula (17)
H=F (f, T) formula (18)
Wherein, Qa is the heat that turbine outlet combustion gas discharges after regenerator, and Qg is compressed air after regenerator
The heat of absorption, GginFor regenerator entrance gas flow, hinFor the enthalpy of regenerator entrance combustion gas, houtFor regenerator outlet
The enthalpy of combustion gas, f are oil-gas ratio, and T is fuel gas temperature, and h is the combustion gas enthalpy under the conditions of Current Temperatures and oil-gas ratio.
So by the above method, it, will after the input parameter that each partial model obtained for gas turbine is arranged
The input parameter of acquisition is inputted respectively in corresponding gas turbine component model, to combine the characteristic being arranged in each partial model
Parameter carries out operation, to obtain the first simulation result of gas turbine operational process, and then can be by first simulation result
It is compared with expected gas turbine operation result, judges whether the two matches, if the first simulation result and expected knot
Fruit matching can then determine that the characterisitic parameter of the gas turbine components of emulation is that can be applied to gas turbine components
The actual characteristic parameter can be used to control the corresponding component operating of gas turbine in actual characteristic parameter in kind；If the
One simulation result and expected result mismatch, then need to correspond in model the gas turbine set parts of emulation and be arranged
Characterisitic parameter be modified, then carries out l-G simulation test with the characterisitic parameter after change, until obtained simulation result in advance
The result of phase matches, i.e., until obtaining the actual characteristic parameter that can be used for controlling the corresponding component of gas turbine and operate, into
And reduce experimental period and experimental cost, and improve the safety of experiment.
Based on the same inventive concept, a kind of simulator of gas turbine is provided in the embodiment of the present invention, the device
The specific implementation of the emulation mode of gas turbine can be found in the description of above method embodiment part, and overlaps will not be repeated,
As shown in figure 9, the device includes:
Module 90 is obtained, for obtaining the input parameter for being directed to each partial model of gas turbine and being arranged；Each partial model
To be pre-set for emulating the model of the operational process of the gas turbine corresponding component, it is provided in each partial model
The characterisitic parameter of its characteristic operation is realized for the partial model；
Computing module 91, the input parameter for will acquire input corresponding each partial model respectively, corresponding to combine
Characterisitic parameter carries out operation in each model, obtains the first simulation result of the operational process of the gas turbine；
Determining module 92, for determining whether the simulation result matches with expected result, if so, determining each portion
The characterisitic parameter of part model is the actual characteristic parameter in its corresponding component, to use the actual characteristic state modulator combustion gas
The corresponding component operating of turbine.
Optionally, the determining module 92 is also used to, however, it is determined that the simulation result and expected result mismatch, then
Following operation is executed, until the second simulation result of acquisition is matched with expected result:
Change the characterisitic parameter in set parts model；
In conjunction with the characterisitic parameter after the corresponding input parameter of the set parts model and change, operation is re-started, is obtained
Obtain the second simulation result of the operational process of the gas turbine.
Optionally, described device further includes change module 93, and the change module 93 is used for:
The set parts model is the corresponding compressor model of compressor part of the gas turbine, the change
Characterisitic parameter in set parts model, specifically:
Change the corresponding relationship of blower outlet flow and rotating speed of gas compressor, compressor pressure ratio；And
Change the corresponding relationship of compressor compression efficiency and rotating speed of gas compressor, blower outlet flow.
Optionally, the compressor model also sets up the characterisitic parameter for carrying out compressor thermodynamic computing, characteristic ginseng
Number is configured according to variable specific heat algorithm in advance.
Optionally, the corresponding input parameter of the compressor model includes: that blower outlet air pressure, compressor enter
Mouth air pressure, compressor inlet air themperature and rotating speed of gas compressor；
The compressor model includes output sub-interface, for exporting corresponding emulation of compressor model as a result, this is imitative
Very sub- result includes following one or more: blower outlet air mass flow, blower outlet air themperature and compressor disappear
Wasted work rate.
Optionally, the set parts model be the gas turbine the corresponding turbine model of turbine part, it is described more
Change the characterisitic parameter in set parts model, specifically:
Change the corresponding relationship of turbine outlet flow and secondary speed, turbine pressure ratio；And
Change the corresponding relationship of turbo-compressor efficiency and secondary speed, turbine outlet flow.
Optionally, the corresponding input parameter of the turbine model includes: turbine outlet gaseous-pressure, turbine inlet combustion gas
Pressure, Turbine Inlet Gas Temperature, oil-gas ratio and secondary speed；
The turbine model includes output sub-interface, for exporting corresponding emulation of turbine model as a result, the emulation is sub
As a result include following one or more: turbine inlet gas flow, turbine outlet gas flow, turbine outlet fuel gas temperature with
And turbine output rate.
It optionally, include combustion chamber model corresponding with combustion chamber components in the partial model of the gas turbine；It is described
The input parameter of combustion chamber model includes: that combustor exit gas flow, entry of combustion chamber compressed air require, combustion chamber enter
Mouth compressed air temperature, fuel flow rate；
The combustion chamber model includes output sub-interface, for exporting emulation knot corresponding with the combustion chamber model
Fruit；
The sub- result of the emulation includes following one or more: entry of combustion chamber compressed air pressure, combustor exit combustion gas
Pressure, combustor exit fuel gas temperature, oil-gas ratio.
Optionally, the partial model of the gas turbine further includes rotator model corresponding with rotor part；
The rotator model includes output sub-interface, for export corresponding with rotor submodel emulation it is sub as a result,
The sub- result of emulation includes at least rotor speed.
Optionally, the partial model of the gas turbine further includes regenerator model corresponding with regenerator component；It is described
The input parameter of regenerator model includes: regenerator inlet compression air themperature, regenerator outlet compressed air pressure, backheat
Device entrance fuel gas temperature, regenerator outlet gas pressure, regenerator inlet compression air mass flow, regenerator entrance gas flow,
Oil-gas ratio；
The regenerator model includes output sub-interface, for exporting emulation knot corresponding with the regenerator model
Fruit, the sub- result of emulation includes following one or more: it is empty that regenerator exports compressed air temperature, regenerator inlet compression
Atmospheric pressure, regenerator entrance gaseous-pressure, regenerator outlet gas temperature.
Based on the same inventive concept, a kind of simulator of gas turbine, such as Figure 10 are additionally provided in the embodiment of the present invention
It is shown, including at least one processor 100 and at least one processor 101, wherein the memory 101 is stored with meter
Calculation machine program, when described program is executed by the processor 100, so that the processor 101 executes in the embodiment of the present invention
The step of emulation mode of the gas turbine of offer.
Based on the same inventive concept, a kind of computer readable storage medium, the calculating are provided in the embodiment of the present invention
Machine readable storage medium storing program for executing is stored with computer instruction, when the computer instruction is run on computers, so that computer is held
The step of emulation mode of capable gas turbine a kind of as described above.
It should be understood by those skilled in the art that, the embodiment of the present invention can provide as method, system or computer journey
Sequence product.Therefore, complete hardware embodiment, complete software embodiment or combining software and hardware aspects can be used in the present invention
The form of embodiment.Moreover, it wherein includes the calculating of computer usable program code that the present invention, which can be used in one or more,
The computer program product implemented in machine usable storage medium (including but not limited to magnetic disk storage and optical memory etc.)
Form.
The present invention be referring to according to the method for the embodiment of the present invention, the process of equipment (system) and computer program product
Figure and/or block diagram describe.It should be understood that can be realized by computer program instructions each in flowchart and/or the block diagram
The combination of process and/or box in process and/or box and flowchart and/or the block diagram.It can provide these computers
Processor of the program instruction to general purpose computer, special purpose computer, Embedded Processor or other programmable data processing devices
To generate a machine, so that being generated by the instruction that computer or the processor of other programmable data processing devices execute
For realizing the function of being specified in one or more flows of the flowchart and/or one or more blocks of the block diagram
Device.
These computer program instructions, which may also be stored in, is able to guide computer or other programmable data processing devices with spy
Determine in the computer-readable memory that mode works, so that instruction stored in the computer readable memory generation includes
The manufacture of command device, the command device are realized in one box of one or more flows of the flowchart and/or block diagram
Or the function of being specified in multiple boxes.
These computer program instructions also can be loaded onto a computer or other programmable data processing device, so that
Series of operation steps are executed on computer or other programmable devices to generate computer implemented processing, thus calculating
The instruction executed on machine or other programmable devices is provided for realizing in one or more flows of the flowchart and/or side
The step of function of being specified in block diagram one box or multiple boxes.
Obviously, various changes and modifications can be made to the invention without departing from of the invention by those skilled in the art
Spirit and scope.In this way, if these modifications and changes of the present invention belongs to the model of the claims in the present invention and its equivalent technologies
Within enclosing, then the present invention is also intended to include these modifications and variations.
Claims (13)
1. a kind of emulation mode of gas turbine characterized by comprising
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 in each partial model and realizes its spy for the partial model
Levy the characterisitic parameter of operation；
The input parameter that will acquire inputs corresponding each partial model respectively, to combine the characteristic ginseng in corresponding each partial model
Number carries 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
Actual characteristic parameter in its corresponding component, to use the corresponding component operating of the actual characteristic state modulator gas turbine.
2. the method as described in claim 1, which is characterized in that if it is determined that the simulation result and expected result mismatch,
Following operation is then executed, until the second simulation result of acquisition is matched with expected result:
Change the characterisitic parameter in set parts model；
In conjunction with the characterisitic parameter after the corresponding input parameter of the set parts model and change, operation is re-started, institute is obtained
State the second simulation result of the operational process of gas turbine.
3. method according to claim 2, which is characterized in that the set parts model is the compressor of the gas turbine
The corresponding compressor model of component, the characterisitic parameter changed in set parts model, specifically:
Change the corresponding relationship of blower outlet flow and rotating speed of gas compressor, compressor pressure ratio；And
Change the corresponding relationship of compressor compression efficiency and rotating speed of gas compressor, blower outlet flow.
4. method as claimed in claim 3, which is characterized in that the compressor model is also set up for carrying out compressor heating power
The characterisitic parameter of calculating, the characterisitic parameter are configured according to variable specific heat algorithm in advance.
5. the method as claimed in claim 3 or 4, which is characterized in that the corresponding input parameter of the compressor model includes: pressure
Mechanism of qi outlet air pressure, compressor inlet air pressure, compressor inlet air themperature and rotating speed of gas compressor；
The compressor model includes output sub-interface, for exporting corresponding emulation of compressor model as a result, the emulation is sub
As a result include following one or more: blower outlet air mass flow, blower outlet air themperature and compressor consume function
Rate.
6. method according to claim 2, which is characterized in that the set parts model is the turbine portion of the gas turbine
The corresponding turbine model of part, the characterisitic parameter changed in set parts model, specifically:
Change the corresponding relationship of turbine outlet flow and secondary speed, turbine pressure ratio；And
Change the corresponding relationship of turbo-compressor efficiency and secondary speed, turbine outlet flow.
7. method as claimed in claim 6, which is characterized in that the corresponding input parameter of the turbine model includes: that turbine goes out
Mouth gaseous-pressure, turbine inlet gaseous-pressure, Turbine Inlet Gas Temperature, oil-gas ratio and secondary speed；
The turbine model includes output sub-interface, for exporting corresponding emulation of turbine model as a result, the sub- result of the emulation
Including following one or more: turbine inlet gas flow, turbine outlet gas flow, turbine outlet fuel gas temperature and turbine
Output power.
8. the method as described in any one of claim 1-4,6,7, which is characterized in that in the partial model of the gas turbine
Including combustion chamber model corresponding with combustion chamber components；The input parameter of the combustion chamber model includes: combustor exit combustion gas
Flow, entry of combustion chamber compressed air require, entry of combustion chamber compressed air temperature, fuel flow rate；
The combustion chamber model includes output sub-interface, for exporting emulation corresponding with the combustion chamber model as a result, should
Emulating sub- result includes following one or more: entry of combustion chamber compressed air pressure, combustor exit gaseous-pressure, combustion chamber
Outlet gas temperature, oil-gas ratio.
9. the method as described in any one of claim 1-4,6,7, which is characterized in that the partial model of the gas turbine is also
Including rotator model corresponding with rotor part；
The rotator model includes output sub-interface, for exporting emulation corresponding with the rotor submodel as a result, described
Sub- result is emulated including at least rotor speed.
10. the method as described in any one of claim 1-4,6,7, which is characterized in that the partial model of the gas turbine
It further include regenerator model corresponding with regenerator component；The input parameter of the regenerator model includes: regenerator entrance pressure
Contracting air themperature, regenerator export compressed air pressure, regenerator entrance fuel gas temperature, regenerator outlet gas pressure, backheat
Device inlet compression air mass flow, regenerator entrance gas flow, oil-gas ratio；
The regenerator model includes output sub-interface, for exporting emulation corresponding with the regenerator model as a result, institute
Stating the sub- result of emulation includes following one or more: regenerator export compressed air temperature, regenerator inlet compression air pressure,
Regenerator entrance gaseous-pressure, regenerator outlet gas temperature.
11. a kind of simulator of gas turbine characterized by comprising
Module is obtained, for obtaining the input parameter for being directed to each partial model of gas turbine and being arranged；Each partial model is preparatory
What is be arranged is used to emulate the model of the operational process of the gas turbine corresponding component, is provided in each partial model for the portion
The characterisitic parameter of its characteristic operation of part model realization；
Computing module, the input parameter for will acquire input corresponding each partial model respectively, to combine corresponding each model
Middle characterisitic parameter carries out operation, obtains the first simulation result of the operational process of the gas turbine；
Determining module, for determining whether the simulation result matches with expected result, if so, determining each partial model
Characterisitic parameter is the actual characteristic parameter in its corresponding component, to use the actual characteristic state modulator gas turbine corresponding
Component operating.
12. a kind of simulator of gas turbine, which is characterized in that including at least one processor and at least one storage
Device, wherein the memory is stored with computer program, when described program is executed by the processor, so that the processing
Device perform claim requires the step of any one of 1-10 the method.
13. a kind of storage medium, which is characterized in that the storage medium is stored with computer instruction, when the computer instruction
When running on computers, so that computer is executed such as the step of any one of claim 1-10 the method.
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 |
|---|---|---|
| US10815874B2 (en) | Turbocharger system for a rotary machine and method of assembling the same | |
| He et al. | Compression performance optimization considering variable charge pressure in an adiabatic compressed air energy storage system | |
| Sanjay et al. | Energy and exergy analysis of steam cooled reheat gas–steam combined cycle | |
| CN110222401A (en) | Aero-engine nonlinear model modeling method | |
| He et al. | A compressed air energy storage system with variable pressure ratio and its operation control | |
| Li et al. | Backpressure adjustable gas turbine combined cycle: A method to improve part-load efficiency | |
| CN108223139B (en) | Deflation Rule adjusting optimization method before a kind of split gas turbine power turbine | |
| CN108843451B (en) | Gas-turbine combustion chamber outlet temperature calculation method | |
| CN106874569A (en) | One kind becomes geometry split gas turbine real-time simulation modeling method | |
| CN110147573A (en) | A kind of emulation mode of gas turbine, device and storage medium | |
| Haugwitz | Modelling of microturbine systems | |
| CN109858129A (en) | A kind of gas turbine dynamic emulation method about combined supply system | |
| CN110348078A (en) | A kind of modeling method of turboshaft engine volume dynamics combination thermo-optic effect | |
| CN108304678A (en) | The method for being directed to different fuel calculation gas turbine performance based on emulation platform | |
| Saddiq et al. | Modelling of gas turbine and gas turbine exhaust and its utilisation as combined cycle in utility system | |
| Johnson | Prediction of gas turbine on-and off-design performance when firing coal-derived syngas | |
| WO2024120432A1 (en) | Method for constructing start performance model for naval-ship gas turbine | |
| CN107301268A (en) | A kind of ship gas turbine variable stator vane angle compressor deflection angle optimization method | |
| CN114427975A (en) | Tandem type combined power mode conversion verification method | |
| CN110148332A (en) | Marine main engine remote control operation simulated training system | |
| Tajalli et al. | Thermodynamic simulation of two-shaft gas turbine to study invasive weeds optimization and Min-Max controller strategies considering air-cooled blades | |
| Kowalski et al. | Performance analysis of gas turbine air heat recovery unit using GateCycle software | |
| Mahmood et al. | Analysis of a Regenerative Gas Turbine Cycle for Power Plant | |
| Iliescu et al. | Gas turbine modeling for load-frequency control | |
| Chen et al. | Power and efficiency optimizations for an open cycle two-shaft gas turbine 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 |