CN104881543B - A kind of the combustion gas main flow and disk chamber Secondary Flow coupling calculation of directly subregion - Google Patents
A kind of the combustion gas main flow and disk chamber Secondary Flow coupling calculation of directly subregion Download PDFInfo
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- CN104881543B CN104881543B CN201510279650.9A CN201510279650A CN104881543B CN 104881543 B CN104881543 B CN 104881543B CN 201510279650 A CN201510279650 A CN 201510279650A CN 104881543 B CN104881543 B CN 104881543B
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Abstract
The invention discloses a kind of coupling calculation of directly subregion, the simulation of Complex Flows inside turbine part in aero-engine or gas turbine is directly divided into this method into combustion gas main flow area and Pan Qiang Secondary Flows area is carried out respectively, two regions are passed through subarea management interface and are carried out data exchange using the turbulence model in different but most suitable respective region.Compared to the method using single turbulence model, the present invention improves coupling Simulation result precision, can improve the engineering design flow of existing turbine part, shortens the design cycle.
Description
Technical field
The present invention relates in Fluid Mechanics Computation and Numerical Simulation of Turbulent field, especially aero-engine or gas turbine
The combustion gas main flow of turbine part and the numerical computation method of disk chamber Secondary Flow coupled problem.
Background technology
Aero-engine and gas turbine are a kind of important industrial equipments, and its core engine includes high-pressure compressor, burning
Three big part of room and high-pressure turbine.As shown in figure 1, single-stage high voltage turbine is by static stator 3 and 4 two blades of movable vane of rotation
Row is formed, and the high-temperature high-pressure fuel gas of combustor exit impact the rotation acting of movable vane 4, structure at an appropriate angle after the water conservancy diversion of stator 3
Into the mainstream channel 1 of combustion gas.The structure of supporting stator 3 and movable vane 4 is known respectively as stator disk 5 and rotor disk 6, therebetween
Cavity be referred to as turning a quiet disk chamber 2, because rotor disk 6 rotates with movable vane 4 together, its pump efficiency should be with the pressure inside and outside rim clearance 7
Difference may all cause the high-temperature fuel gas in mainstream channel 1 enters to turn quiet disk chamber 2, and the combustion gas of intrusion disk chamber can cause turbine disk mistake
Heat, cause part heat fatigue, reduce rotor life.In order to maintain to turn the normal work of quiet disk chamber 2, on the one hand, in rim clearance 7
The appropriate seal structure of Position Design, reduce the air-flow inside and outside gap and exchange；On the other hand, the cold gas one from compressor
Part is introduced into disk chamber, and the turbine disk is cooled down, and after through rim clearance 7 enter main flow, the flowing quilt inside turn quiet disk chamber 2
Referred to as disk chamber Secondary Flow.
In considerable time in past, academia and industrial quarters all flows combustion gas main flow and disk chamber secondary flow is regarded
Two independent objects are analyzed, and with deepening continuously for research, people gradually recognize：Combustion gas main flow and disk chamber Secondary Flow
It is a complicated Coupled Flow system, therebetween there is strong interaction, wants further to improve turbine part
Performance and the life-span, must just be accounted for them as an entirety.With the operational speed of a computer and memory capacity
Continuous improvement and the continuous development of Fluid Mechanics Computation technology, are simulated using method for numerical simulation to Complex Flows problem
Possibility is increasingly becoming, numerical computations also turn into three big technologies of Study of Fluid mechanics problem side by side with experiment test, theory analysis
One of approach, then turn into a natural thinking with numerical Method Research combustion gas main flow and disk chamber Secondary Flow coupled problem.
Because Reynolds number is higher, mainstream channel 1 and the flowing turned inside quiet disk chamber 2 are all turbulent flows, if selection work
The permanent Reynolds average method being most widely used in journey is simulated to the coupled problem, then is related to the choosing of turbulence model
Take：It is well known that the scope of application of different turbulent models and differing, it selects that first may be produced to the precision of result of calculation
The influence of position.Existing numerous studies show, for combustion gas main flow and disk chamber secondary flow, in the premise that other specification is constant
Under, it is often different to obtain the turbulence model selected by optimal simulation result, and this just brings a problem, when we are to upper
When stating Coupled Flow and being simulated, which turbulence model this selects according to what standard actuallyAt this stage, difference is ground
The person's of studying carefully choices made simultaneously differs：Such as《The Influence of HPT Forward Disc Cavity Platform
Axial Overlap Geometry on Mainstream Ingestion》(ASME turbine meetings, 2012, paper was compiled
Number GT2012-68429) in have chosen the Spalart-Allmaras models (abbreviation S-A models) of an equation and carry out coupling calculating,
And《Numerical Investigation of the Interaction Between Upstream Purge Flow and
Mainstream in a Highly-Loaded Turbine》(ASME turbine meetings, 2014, paper number GT2014-
25501) the shear stress transport k- ω models (abbreviation SST k- ω models) of two equations are then have chosen in.Though above-mentioned processing scheme
The result of calculation of a certain precision can be so obtained, but because selected turbulence model is only suitable for coupling the part area in flow field
Domain, thus optimal precision of prediction can not be obtained, computational methods how are improved, improve the quality of simulation result, it is clear that are worth
The problem of conscientiously studying.
The content of the invention
The invention aims to solve the above problems, a kind of the combustion gas main flow and disk chamber Secondary Flow of directly subregion are proposed
Coupling calculation., can be in combustion gas main flow area and disk chamber secondary flow, region respectively using different but most using this method
It is adapted to the turbulence model in respective region, the precision of coupling Simulation result is improved with this.
The combustion gas main flow and disk chamber Secondary Flow coupling calculation of a kind of directly subregion of the present invention, as shown in Fig. 2 specifically
Comprise the following steps：
Step 1：To some turbine part, it is determined that the computational fields that coupling calculates, including the import of mainstream channel 1, outlet and
Blending face position, turn the entrance location of quiet disk chamber 2, and mainstream channel 1 and the coupled interface position for turning quiet disk chamber 2, couple boundary
Face is generally arranged at rim clearance 7, and should be ensured that blending face and coupled interface are non-intersect.
Step 2：Generate mainstream channel 1 respectively from Grid Generation Software and turn the calculating grid of quiet disk chamber 2, grid matter
Amount should meet the requirement of cfdrc described in step 3 and selected turbulence model, should along the grid of coupled interface both sides
Ensure matching as far as possible.
Step 3：From cfdrc, the flowing of combustion gas main flow and the simulation of disk chamber secondary flow are respectively completed
Parameter setting, including the content such as turbulence model, numeric format, boundary condition, flow field initialization.
Step 4：According to the difference of turbulence model selected by combustion gas main flow and the secondary flow field simulation of disk chamber, enter along coupled interface
The exchange of row flow field data and turbulent flow data, complete the renewal of coupled interface boundary condition.
Step 5：Cfdrc is run, the flowing of combustion gas main flow and disk chamber secondary flow are specified respectively
The permanent simulation of step number.
Step 6：Judge whether the flow field in two regions restrains, if being satisfied by the condition of convergence, carry out step 7, it is no
Then jump to step 4 execution.
Step 7：Coupling calculating terminates, and preserves result of calculation.
The advantage of the invention is that：
Compared to the method simulated using single turbulence model, direct subarea management method of the invention can be in combustion gas
Main flow and disk chamber secondary flow, region use turbulence model that is different but being best suitable for the region, improve the essence of coupling Simulation result
Degree, existing aero-engine or the engineering design flow of Gas Turbine part can be improved, shorten the design cycle.
Brief description of the drawings
Fig. 1 is the schematic diagram of high-pressure turbine part.
Fig. 2 is the flow chart of direct subarea management computational methods.
Embodiment
For certain specific high-pressure turbine part, technical solution of the present invention comprises the following steps when realizing：
Step 1：Combustion gas main flow and disk chamber Secondary Flow are simulated respectively using business software Fluent, assess different rapidss
The precision of prediction of flow model, by it was found that, there is best precision of prediction to combustion gas main flow S-A models, it is secondary to disk chamber
It is optimal to flow the performance of SST k- ω models, based on this, in subarea management calculating, combustion gas main flow and disk chamber secondary flow, region are distinguished
Select S-A models and SST k- ω models.
Step 2：Subregion is developed using Python, with reference to business software Fluent User-Defined Functions (UDF)
Coupling Simulation platform, Fluent calling, the data exchange of coupled interface, convergent judgement etc. is entered by coupling Simulation platform
Row control.
Step 3：To high-pressure turbine part, it is determined that the computational fields that coupling calculates, rim clearance is arranged on most by coupled interface
Small position, generated with business software IGG/Autogrid and calculate grid, the grid of coupled interface both sides keeps matching.
Step 4：Combustion gas main flow and the parameter setting of the secondary flow field simulation of disk chamber are completed in Fluent.
Specially：
(1) turbulence model of combustion gas main flow area is S-A models, and main flow import gives stagnation temperature, stagnation pressure and flow angle, and main flow goes out
The given back pressure of mouth, coupled interface is speed import, and relevant parameter is configured by UDF.
(2) turbulence model of disk chamber secondary flow, region is SST k- ω models, and import given flow, coupled interface is pressure
Outlet, relevant parameter are configured by UDF.
Step 5：Flow field data (velocity component, thermodynamic variable) and turbulent flow data (turbulent viscosity are carried out along coupled interface
Than, tubulence energy k, rapids can be than dissipative shock wave ω) exchange, pass through UDF complete coupled interface boundary condition renewal.
Step 6：Coupling Simulation platform calls Fluent, combustion gas main flow and disk chamber secondary flow, region is carried out specifying step respectively
Several permanent calculating.
Step 7：Coupling Simulation platform judges whether the flow field in two regions restrains, if being satisfied by the condition of convergence, enters
Row step 8, otherwise jump to step 5 and perform.
Step 8：Terminate coupling to calculate, preserve result.
For it is obvious for a skilled person that, it is also possible to make other embodiments with reference to described above.On
Embodiment in text is exemplary rather than limitation.The sheet of all claim technical schemes in the present invention
Modification within matter belongs to its scope claimed.
Claims (4)
1. a kind of the combustion gas main flow and disk chamber Secondary Flow coupling calculation of directly subregion, it is characterised in that this method includes following
Step：
Step 1：To some turbine part, it is determined that the computational fields that coupling calculates, include import, outlet and the blending of mainstream channel
Face position, turn the entrance location of quiet disk chamber, and mainstream channel and the coupled interface position for turning quiet disk chamber, coupled interface are arranged on
At rim clearance, and it should be ensured that blending face and coupled interface are non-intersect；
Step 2：Generate mainstream channel respectively from Grid Generation Software and turn the calculating grid of quiet disk chamber, mesh quality should expire
The requirement of cfdrc and selected turbulence model described in sufficient step 3, it should ensure that along the grid of coupled interface both sides
Match somebody with somebody；
Step 3：From cfdrc, the parameter that combustion gas main flow is flowed and disk chamber secondary flow is simulated is respectively completed
Set, including turbulence model, numeric format, boundary condition, flow field initialization content；
Step 4：According to the difference of turbulence model selected by combustion gas main flow and the secondary flow field simulation of disk chamber, flowed along coupled interface
The exchange of field data and turbulent flow data, complete the renewal of coupled interface boundary condition；
Step 5：Cfdrc is run, respectively the flowing of combustion gas main flow and disk chamber secondary flow are carried out specifying step number
Permanent simulation；
Step 6：Judge whether the flow field in two regions restrains, if being satisfied by the condition of convergence, carry out step 7, otherwise jump
Go to step 4 execution；
Step 7：Coupling calculating terminates, and preserves result of calculation.
2. the combustion gas main flow and disk chamber Secondary Flow coupling calculation of a kind of directly subregion according to claim 1, it is special
Sign is, in step 1, subarea management interface setting is in the minimum position of rim clearance.
3. the combustion gas main flow and disk chamber Secondary Flow coupling calculation of a kind of directly subregion according to claim 1, it is special
Sign is, in step 3, combustion gas main flow area selects S-A models, and Pan Qiang Secondary Flows area selects SST k- ω models.
4. the combustion gas main flow and disk chamber Secondary Flow coupling calculation of a kind of directly subregion according to claim 1, it is special
Sign is that subarea management emulation platform uses Python, the User-Defined Functions (UDF) with reference to business software Fluent
Realize.
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| CN109145335B (en) * | 2017-06-28 | 2023-05-30 | 中国航发贵阳发动机设计研究所 | Method for improving low cycle fatigue life of wheel disc through pre-rotation |
| CN111539159B (en) * | 2020-03-31 | 2023-07-14 | 中国航天空气动力技术研究院 | Distributed multi-physical field coupling control system for simulating sweating cooling |
| CN112417783A (en) * | 2020-11-20 | 2021-02-26 | 西安热工研究院有限公司 | Mixing turbulence calculation method |
| CN112906322B (en) * | 2021-03-17 | 2024-03-15 | 中国航空发动机研究院 | Method for calculating internal parameters of disk cavity of gas turbine engine |
| CN114673844B (en) * | 2022-03-30 | 2022-11-25 | 重庆大学 | Self-sealing separating joint for preventing aircraft fuel system from crash |
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Non-Patent Citations (4)
| Title |
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| NUMERICAL INVESTIGATION OF THE INTERACTION BETWEEN UPSTREAM;Wei Jia;《Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition》;20140620;第1-15页 * |
| The Influence of HPT Forward Disc Cavity Platform Axial Overlap;A.V. Mirzamoghadam;《Proceedings of ASME Turbo Expo 2012》;20120615;第1-12页 * |
| 液体推进剂火箭发动机推力室再生冷却;吴峰;《航空动力学报》;20050915;第20卷(第4期);第1-6页 * |
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