CN109684750A - A kind of compressor model modeling method for helium turbine - Google Patents
A kind of compressor model modeling method for helium turbine Download PDFInfo
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- CN109684750A CN109684750A CN201811613138.3A CN201811613138A CN109684750A CN 109684750 A CN109684750 A CN 109684750A CN 201811613138 A CN201811613138 A CN 201811613138A CN 109684750 A CN109684750 A CN 109684750A
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Abstract
A kind of compressor model modeling method for helium turbine belongs to compressor model modeling field.There are limitations for existing compressor modeling method, and expressed result has error.A kind of compressor model modeling method for helium turbine designs compressor impeller using CAD software；The compressor impeller model of design is imported and carries out geometry pre-treatment in BladeModeler；Using BladeGen software, to treated, compressor impeller model carries out impeller parameters extraction；The modeling process of the entry guide vane module of compressor model is carried out using the parameter of extraction；The modeling process of the stator blade module of compressor model is carried out using the parameter of extraction；Above-mentioned model is verified, stable state and dynamic authentication are carried out to each submodule simulated program respectively, determine final model and program.The helium turbine closed circuit system simulated program that the present invention establishes can correctly reflect its stable state and dynamic characteristic, can provide foundation for the optimization of helium turbine closed circuit system.
Description
Technical field
The present invention relates to the modeling of compressor, in particular to a kind of compressor model modeling method for helium turbine.
Background technique
Still in the stage of experience accumulation, the simulation study to helium turbine is still to grind for the design and operation of helium turbine
The necessary process studied carefully.In the simulation process to helium turbine closed circuit system, establishing suitable compressor model is key,
Especially when the start-up course to helium turbine closed circulation system emulates, since one of the result for comparing concern is
The active line of compressor needs more accurate compressor model.
Have to the method for the comparison mainstream that compressor is modeled following several: one, primitive blade method, the method utilize two
The theory of first Cascade Flow acquires the performance of each primitive blade, successively determines the performance of blade row, then the property that blade is arranged
It can be superimposed, obtain total performance of compressor.Two, quasi-nonlinear method, the method can calculate the fortune of the compressor within the scope of little deviation
Market condition is not appropriate for the compressor machine emulation of gamut.Three, curve-fitting method or statistic law, the method to compressor into
Although row performance estimation is applied to the present, but have certain limitation, it depends not only upon the trial curve of compressor, and
And general difference.In the case where known Compressor test curve is sparse, it may appear that biggish error.Four, Three-dimensional Flow model,
The method carries out performance to compressor and calculates a large amount of discrete and calculating process of needs, is also not suitable for helium turbine closed cycle
The process of device progress real-time simulation.
Summary of the invention
The purpose of the present invention is to solve the existing compressor modeling method scope of applications to be limited to, and expressed
As a result there is the big problem of error, and propose a kind of compressor model modeling method for helium turbine.
A kind of compressor model modeling method for helium turbine, the modeling method the following steps are included:
Step 1: designing compressor impeller using CAD software；
Geometry pre-treatment is carried out in BladeModeler Step 2: the compressor impeller model of design is imported；
Step 3: to treated, compressor impeller model carries out impeller parameters extraction using BladeGen software；
Step 4: carrying out the modeling process of the entry guide vane module of compressor model using the parameter that step 3 is extracted；
Step 5: carrying out the modeling process of the stator blade module of compressor model using the parameter that step 3 is extracted；
Step 6: above-mentioned model is written as Fortran program, ring is run in Compaq Visual Fortran 6
Under border, verified using the design parameter and operating parameter of helium turbine closed circuit system, it is imitative to each submodule respectively
Proper program carries out stable state and dynamic authentication, determines final model and program.
The invention has the benefit that
The present invention models compressor using averga cross section method.The averga cross section simplification owned by France in primitive blade method
Form.Since helium compressor has big wheel hub ratio, blade height is small and as series increase variation is small, so that application is average
The characteristic that method of section replaces completely radial balancing method to calculate compressor stage has remained to good effect.It is set up using the method
Compressor model can be realized the simulation of Complex compressor independent of test feature, suitable for compressor under full working scope
Simulation work.
Small flow, the calculating of the compressor characteristics under small revolving speed can be carried out using compressor model of the invention.As incited somebody to action
In its simulation calculation for being applied to entire helium turbine closed circuit system, it is only necessary to inlet flow rate is provided, it is whole using what is acquired
Machine pressure ratio is verified, to expand the compressor modeling method scope of application.
The helium turbine closed circuit system simulated program that the present invention establishes can correctly reflect that its stable state and dynamic are special
Property, reduce the error of expressed result, foundation can be provided for the optimization of helium turbine closed circuit system, and in this base
Control characteristic is further studied on plinth.
Specific embodiment
Specific embodiment 1:
A kind of compressor model modeling method for helium turbine of present embodiment, the modeling method include with
Lower step:
Step 1: designing compressor impeller using CAD software；
Geometry pre-treatment is carried out in BladeModeler Step 2: the compressor impeller model of design is imported；
Step 3: to treated, compressor impeller model carries out impeller parameters extraction using BladeGen software；
Step 4: carrying out the modeling process of the entry guide vane module of compressor model using the parameter that step 3 is extracted；
Step 5: carrying out the modeling process of the stator blade module of compressor model using the parameter that step 3 is extracted；
Step 6: above-mentioned model is written as Fortran program, ring is run in Compaq Visual Fortran 6
Under border, school is carried out using the design parameter and operating parameter of 10MW high temperature gas cooled reactor the second stage of the project helium turbine closed circuit system
It tests, stable state and dynamic authentication is carried out to each submodule simulated program respectively, determine final model and program correctness；
On this basis, for each submodule simulated program to be carried out joint debugging, to complete entire helium turbine closed cycle
Static Simulation and start operating performance dynamic simulation of the device under nominal operating conditions.
Specific embodiment 2:
Unlike specific embodiment one, a kind of compressor model for helium turbine of present embodiment is modeled
Method, in the step four, the parameter for utilizing step 3 to extract carries out the modeling of the entry guide vane module of compressor model
Journey specifically:
The parameter of the entrance helium temperature, entrance helium pressure and entrance helium gas flow that are extracted according to step 3, by Mach
Several definition can obtain:
In formula: GGVIndicate entry guide vane inlet mass flow, kg/s；AGV, 1Indicate entry guide vane inlet flow area, m2；
PGV, 1Indicate entry guide vane entrance helium pressure；TGV, 1Indicate entry guide vane entrance helium temperature；MaGVIndicate entry guide vane entrance
Mach number；
It is defined by continuity equation, stagnation temperature and obtains the Mach number such as following formula institute of guide vane exit flow with adiabatic process
Show:
In formula: βGV, 2Entry guide vane exports absolute air flow angle；MaGV, 2Entry guide vane exit Mach number；
Then entry guide vane inlet pressure, i.e. compressor inlet stagnation pressure and entrance stagnation temperature can be by formula (3) and formulas
(4) it acquires:
In formula: PGV, 01Indicate entry guide vane entrance stagnation pressure, MPa；TGV, 01Indicate entry guide vane entrance stagnation temperature, K
The outlet stagnation pressure and outlet stagnation temperature for indicating entry guide vane can be respectively by formula (5) and formulas (6):
TGV, 02=TGV, 01 (6)
In formula: PGV, 02Indicate that entry guide vane exports stagnation pressure, Pa；TGV, 02Entry guide vane exports stagnation temperature, K；Indicate revised entry guide vane total pressure loss coefficient；
By the outlet parameter Ma of guide vaneGV, 2, PGV, 02, TGV, 02Entry condition as grade model.
Specific embodiment 3:
Unlike specific embodiment two, a kind of compressor model for helium turbine of present embodiment is modeled
Method, in the step five, the parameter for utilizing step 3 to extract carries out the modeling process tool of the stator blade module of compressor model
Body are as follows: the concept for introducing the tangential Mach number of rotor, as shown in formula (7):
Assuming that flowing of the helium in movable vane is steady-flow, speed triangle is imported and exported according to Eulerian equation and moving blades
Shape can obtain shown in the outlet and entrance stagnation temperature such as formula (3-67) of moving blades:
In formula: TR, 01Indicate rotor inlet stagnation temperature, K；TR, 02Indicate rotor outlet stagnation temperature, K；CR, s1It indicates to turn
Sub- entrance velocity axial component, m/s；CR, s2Indicate rotor outlet speed axial component, m/s；βR, 2Indicate rotor outlet with respect to gas
Flow angle；βGV, 2Indicate that entry guide vane exports absolute air flow angle；MaR, 1Indicate the absolute inflow Mach number of rotor；It is defined by Mach number
Rotor inlet relative Mach number is shown in formula (9) out:
In formula:Indicate rotor inlet relative Mach number；WR, 1Indicate rotor inlet relative velocity, m/sTR, 1It indicates
Rotor inlet static temperature degree, K；
Therefore, the opposite stagnation pressure ratio of rotor can be acquired by formula (10):
In formula, PR, 1Indicate rotor inlet static pressure, Pa；Indicate rotor inlet with respect to stagnation pressure, Pa；Indicate rotor outlet with respect to stagnation pressure, Pa；Indicate revised rotor total pressure loss coefficient；
In formula, MaR, 2The absolute Mach number of rotor outlet；CR, 2Indicate rotor outlet absolute velocity, m/s；TR, 2Indicate that rotor goes out
Mouth static temperature degree, K；
In formula: PR, 01Indicate the absolute stagnation pressure of rotor inlet, Pa；PR, 02Indicate the absolute stagnation pressure of rotor outlet, P；It is dynamic
The outlet parameter Ma of bladeR, 2, PR, 02, TR, 02Entry condition as next stage stator blade；
Then stator blade model computation model is as follows:
In formula, PS, 1Indicate stator input static pressure power, Pa；PS, 01Indicate stator entrance stagnation pressure, Pa；MaS, 1Indicate quiet
Sub- entrance Mach number；
In formula: PS, 02Indicate that stator exports stagnation pressure, Pa；Indicate revised stator pitot loss system
Number
βS, 2Indicate stator outlet flow angle；MaS, 2Indicate stator exit Mach number.
The present invention can also have other various embodiments, without deviating from the spirit and substance of the present invention, this field
Technical staff makes various corresponding changes and modifications in accordance with the present invention, but these corresponding changes and modifications all should belong to
The protection scope of the appended claims of the present invention.
Claims (3)
1. a kind of compressor model modeling method for helium turbine, it is characterised in that: the modeling method includes following
Step:
Step 1: designing compressor impeller using CAD software；
Geometry pre-treatment is carried out in BladeModeler Step 2: the compressor impeller model of design is imported；
Step 3: to treated, compressor impeller model carries out impeller parameters extraction using BladeGen software；
Step 4: carrying out the modeling process of the entry guide vane module of compressor model using the parameter that step 3 is extracted；
Step 5: carrying out the modeling process of the stator blade module of compressor model using the parameter that step 3 is extracted；
Step 6: above-mentioned model is written as Fortran program, under 6 running environment of Compaq Visual Fortran,
It is verified using the design parameter and operating parameter of helium turbine closed circuit system, respectively to each submodule simulated program
Stable state and dynamic authentication are carried out, determines final model and program.
2. a kind of compressor model modeling method for helium turbine according to claim 1, it is characterised in that: described
The step of four in, utilize step 3 extract parameter carry out compressor model entry guide vane module modeling process specifically:
The parameter of the entrance helium temperature, entrance helium pressure and entrance helium gas flow that are extracted according to step 3, by Mach number
Definition can obtain:
In formula: GGVIndicate entry guide vane inlet mass flow, kg/s；AGV, 1Indicate entry guide vane inlet flow area, m2；PGV, 1
Indicate entry guide vane entrance helium pressure；TGV, 1Indicate entry guide vane entrance helium temperature；MaGVIndicate entry guide vane entrance Mach
Number；
The Mach number for obtaining guide vane exit flow with adiabatic process is defined by continuity equation, stagnation temperature to be shown below:
In formula: βGV, 2Entry guide vane exports absolute air flow angle；MaGV, 2Entry guide vane exit Mach number；
Then entry guide vane inlet pressure, i.e. compressor inlet stagnation pressure can be asked with entrance stagnation temperature by formula (3) and formula (4)
:
In formula: PGV, 01Indicate entry guide vane entrance stagnation pressure, MPa；TGV, 01Indicate entry guide vane entrance stagnation temperature, K is indicated
The outlet stagnation pressure and outlet stagnation temperature of entry guide vane can be respectively by formula (5) and formulas (6):
TGV, 02=TGV, 01 (6)
In formula: PGV, 02Indicate that entry guide vane exports stagnation pressure, Pa；TGV, 02Entry guide vane exports stagnation temperature, K；Indicate revised entry guide vane total pressure loss coefficient；
By the outlet parameter MA of guide vaneGV, 2, PGV, 02, TGV, 02Entry condition as grade model.
3. a kind of compressor model modeling method for helium turbine according to claim 1 or 2, it is characterised in that:
In the step five, the modeling process of the stator blade module of compressor model is carried out using the parameter that step 3 is extracted specifically:
The concept for introducing the tangential Mach number of rotor, as shown in formula (7):
Assuming that flowing of the helium in movable vane is steady-flow, it can according to Eulerian equation and moving blades inlet and outlet speed triangle
It obtains shown in the outlet and entrance stagnation temperature such as formula (3-67) of moving blades:
In formula: TR, 01Indicate rotor inlet stagnation temperature, K；TR, 02Indicate rotor outlet stagnation temperature, K；CR, s1Indicate that rotor enters
Mouth speed axial component, m/s；CR, s2Indicate rotor outlet speed axial component, m/s；βR, 2Indicate rotor outlet relative wind
Angle；βGV, 2Indicate that entry guide vane exports absolute air flow angle；MaR, 1Indicate the absolute inflow Mach number of rotor；It is defined and is obtained by Mach number
Rotor inlet relative Mach number is shown in formula (9):
In formula:Indicate rotor inlet relative Mach number；WR, 1Indicate rotor inlet relative velocity, m/sTR, 1Indicate that rotor enters
Mouth static temperature degree, K；
Therefore, the opposite stagnation pressure ratio of rotor can be acquired by formula (10):
In formula, PR, 1Indicate rotor inlet static pressure, Pa；Indicate rotor inlet with respect to stagnation pressure, Pa；Table
Show rotor outlet with respect to stagnation pressure, Pa；Indicate revised rotor total pressure loss coefficient；
In formula, MaR, 2The absolute Mach number of rotor outlet；CR, 2Indicate rotor outlet absolute velocity, m/s；TR, 2Indicate that rotor outlet is quiet
Temperature, K；
In formula: PR, 01Indicate the absolute stagnation pressure of rotor inlet, Pa；PR, 02Indicate the absolute stagnation pressure of rotor outlet, P；Movable vane piece
Outlet parameter MaR, 2, PR, 02, TR, 02Entry condition as next stage stator blade；
Then stator blade model computation model is as follows:
In formula, PS, 1Indicate stator input static pressure power, Pa；PS, 01Indicate stator entrance stagnation pressure, Pa；MaS, 1Indicate stator entrance
Mach number；
In formula: PS, 02Indicate that stator exports stagnation pressure, Pa；Indicate revised stator total pressure loss coefficient
βS, 2Indicate stator outlet flow angle；MaS, 2Indicate stator exit Mach number.
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| CN113740021A (en) * | 2021-08-27 | 2021-12-03 | 大连透平机械技术发展有限公司 | Centrifugal compressor performance test experiment table |
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