CN109409016A - A kind of aero-engine compressor UNSTEADY FLOW method for visualizing - Google Patents
A kind of aero-engine compressor UNSTEADY FLOW method for visualizing Download PDFInfo
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Abstract
The invention discloses a kind of aero-engine compressor UNSTEADY FLOW method for visualizing, include the following steps: using single channel grid as input and output loopful grid, and marks the gas compressor blade row where each grid block；All grid blocks are spread to different processes, each process individually exports the flow field on the grid block that it is got when storing flow field, and establishes a file for each leaf row；The flow field data of each leaf row are successively read, flow field parameter is calculated；According to the interface standard of visual software Tecplot, flow-field visualized file is exported.The present invention has the unsteady magnanimity flow field data of multistage compressor visual ability on single machine；The present invention has the ability for extracting and individually handling any leaf row in multistage compressor；The present invention has the ability for automatically extracting two dimensional slice and flow field file size is reduced to the ability of about an order of magnitude.
Description
Technical field
The present invention relates to a kind of aero-engine compressor UNSTEADY FLOW method for visualizing, belong to aviation aircraft technology
Field.
Background technique
In the design and retrofitting process of aero-engine compressor, it is selective to release multiple compressor geometric shapes,
At this moment the global aeroperformance and internal flow details for needing to assess different shapes, provide reference for type selecting.The inside of compressor
It is extremely abundant to flow details, wherein unsteady interaction, blade pressure are distributed, on blade between blade tip leakage flow, corner region flow, leaf row
Shock/Boundary-Layer interference etc. directly influence the Local Property of compressor blade, and influence the global gas of compressor indirectly
Dynamic performance.The visualization of details is flowed by compressor, and intuitively these flowing details can be assessed.
Meanwhile with the propulsion that the progress of Aeronautics and national industry upgrade, industry is to aero-engine pressure
The performance requirement of mechanism of qi also steps up.In the technological means that academic circles at present and industry promote Capability of Compressor,
It has arrived thin scratch and has flowed details, found the stage in optimization direction.Compressor flowing details is visualized as searching optimization direction and provides
Means.
Method that there are two types of the visualizations of compressor internal flow details generallys use PIV method one is doing experiment both at home and abroad
It is disadvantageous in that with measuring techniques, this methods and techniques such as porous probes:
1) PIV method is also known as particle image velocimetry method, the main velocity profile information for measuring space flow field, but can not obtain
To the information such as the density of compressor inner air and pressure, and inner space more closed for compressor, intensive blade
Situations such as distribution, the blade rotation of high speed, the strong influence effect of PIV, and also equipment is expensive, and it is at high cost；
2) porous probe is extended into inside compressor, can measure the velocity magnitude of compressor interior flow field, direction and
The information such as stagnation pressure and static pressure, but it is unable to test the information of rotor flow regions, and other objects are added in compressor
Influence whether the authenticity in flow field, while the design and difficulty of processing of seven-hole probe are larger.
Second of method for visualizing of compressor internal flow details is to the Numerical-Mode for being based on CFD (Fluid Mechanics Computation)
Quasi- result is visualized, and in order to guarantee the simulation precision of flowing, carrying out the unsteady simulation of loopful to compressor is very
Close to Real Flow Field condition.When being visualized to this loopful unsteady gas flow simulation result, generally use both at home and abroad defeated
Meet the global flowing information of visual software interface out, the visualization flowed by visual software, this method
It is disadvantageous in that:
1) global flowing message file is too big, can not single machine show.Since the series of compressor is more, loopful is non-
Steady Flow is in the coordinate information 100G close with basis flowing message file total size at some moment, this is considerably beyond commonly
The memory size of single machine can not be shown in single machine, can only by the way that picture or data are handled and exported on supercomputer,
Complicated for operation, operating efficiency is lower, not enough intuitively, inflexible；
2) coordinate information and flowing information that can not individually export interested gas compressor blade row, also can not individually export certain
The coordinate information and flowing information of certain sections of one leaf row or certain several leaf row, also can not only export interested flowing and become
Amount；
3) lack the scheme for reducing global flowing message file size.
For this purpose, this method is not only the invention proposes a kind of aero-engine compressor UNSTEADY FLOW method for visualizing
The calculated result file of compressor loopful UNSTEADY FLOW can be automatically processed, moreover it is possible to the coordinate information for arranging each leaf and flowing
Information individually exports and carries out independent display, and the coordinate information that can be obtained by calculation under different sections and flowing letter
Breath, and can calculate and export interested flow parameter, moreover it is possible to flowing information file is reduced by about an order of magnitude.It is above this
A little advantages ensure that can arbitrarily show interested leaf row, the flow field parameter on section on single machine, flexible to operation,
Strong supplementary means is provided for the design of compressor, remodeling and optimization.
Summary of the invention
In order to overcome the disadvantages mentioned above of the prior art, the invention proposes a kind of aero-engine compressor UNSTEADY FLOWs
Method for visualizing.The UNSTEADY FLOW method for visualizing is to the model containing compressor at a time obtained based on numerical simulation
Coordinate information, spatial coordinated information and the flowing information in space data obtain the coordinate letter of each independent leaf row by post-processing
Breath and flowing information.Then, by further post-processing, interested leaf row, the flow field parameter on section are obtained, according to can
Interface standard depending on changing software, generates FLOW VISUALIZATION file, is used as FLOW VISUALIZATION.In case of need, by FLOW VISUALIZATION text
The space coordinate and object plane coordinate lattice point of part export, and also dot interlace exports the flow field parameter being attached in coordinate points, can be aobvious by flowing
Show that file is reduced to 1/8th before dot interlace output.
Purpose is to realize the bridge between numerical simulation result data and visual software, realize on single machine arbitrarily
Show interested leaf row in multistage compressor loopful flow field, the flow field parameter on section:
1) by technical treatment, compressor mass data flow field convenient flexible visualization means on single machine are realized；
2) Flow details are shown by various forms, provides foundation for type selecting in the design process of compressor；
3) Flow details are shown by various forms, the vane stress situation for being compressor under extreme operating conditions provides
Analysis means；
4) intuitive tool is provided for thin Flow details of scratching, to provide foundation for assessment remodeling result；
5) intuitive tool is provided for thin Flow details of scratching, thus to determine that optimization direction provides foundation.
The technical solution adopted by the present invention to solve the technical problems is: a kind of aero-engine compressor UNSTEADY FLOW
Method for visualizing includes the following steps:
Step 1: generating the multi-block structured grid in multistage compressor single blade channel；
Step 2: being input with the grid that step 1 generates, output loopful net after being rotated, determining opposite joining relation processing
Lattice, and mark the gas compressor blade row where each grid block；
Step 3: all grid blocks to be spread to different processes, when storing flow field, each process individually exports it
The flow field on grid block got, and a file is established for each leaf row；
Step 4: being successively read the flow field data of each leaf row, flow field parameter is calculated；
Step 5: exporting flow-field visualized file according to the interface standard of visual software Tecplot.
Compared with prior art, the positive effect of the present invention is: the present invention has the magnanimity that multistage compressor is unsteady
Data visual ability on single machine in flow field for convenience, flexibly, intuitively can be observed and analyze multistage compressor nonstationary flow
Dynamic details provides powerful measure；The present invention has the ability for extracting and individually handling any leaf row in multistage compressor, can remove
Irrelevant information improves analysis efficiency；The present invention has the ability for automatically extracting two dimensional slice and reduces flow field file size about
The ability of an order of magnitude drains the technology hand for the characteristics such as relating to and providing convenience easily to analyze gas compressor blade on single machine
Section.Specific manifestation is as follows:
1) it by splitting the grid of each leaf row of multistage compressor and flow field, realizes on single machine intuitively, flexibly, efficiently
Observation Flow details function, reduce manual operation, improve compressor internal flow details assessment and search direction analysis
Efficiency；
2) by splitting the grid of each leaf row of multistage compressor and flow field, individual or group between different leaf rows is realized
Flow visual under conjunction form；
3) by the way that information of flow to be interpolated on special section, it is not required to manual intervention, compressor is reduced and flows detail analysis
When cost of labor and time cost.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1 is the flow chart of the method for visualizing of aero-engine compressor UNSTEADY FLOW；
Fig. 2 is that single channel grid switchs to multichannel/loopful grid schematic diagram.
Specific embodiment
A kind of aero-engine compressor UNSTEADY FLOW method for visualizing, as shown in Figure 1, including the following steps:
Step 1: generating the muti-piece in multistage compressor single blade channel using business software NUMECA or Pointwise etc.
Structured grid, the grid amount for needing to generate in this way is small, and formation speed is fast, cumbersome manual operation is greatly reduced, to individual
The request memory of computer is relatively low.
Step 2: being input with single channel grid by axial flow compressor loopful Grid Generation Software SCTMC, rotated,
Loopful grid is exported after determining the processing such as opposite joining relation, marks the gas compressor blade row where each grid block.Due to loopful net
Lattice data file size can be carried out up to tens of GB, this step on supercomputer, not need manual intervention, without examining
Consider the limitation of personal computer memory, it is easy to operate, required loopful grid file can be directly acquired.
Step 3: using axial flow compressor aerodynamics software for calculation ASPAC again, by Finite Volume Method, solve
Aerodynamics governing equation, and grid exchange of skills data are overlapped by dynamic between the leaf of multistage compressor row, thus right
Multistage compressor carries out the unsteady simulation of loopful.By simulation, the three-dimensional loopful of available different moments, compressor instantaneously flow
?.Flow field parameter includes density, speed and pressure etc..
In the parallel computation of ASPAC, all grid blocks are dispersed into different processes, and can input an information,
I.e. some grid block is located at which process and its number in all grid blocks that the process is got.It is flowed in storage
When field, each process individually exports the flow field on the grid block that it is got at a time, although loopful grid data amount pole
Greatly, the data volume that each process is got be it is smaller, by parallel output, improve the IO efficiency of calculating, reduce I O error hair
Raw probability.Therefore, when collecting the flow field of some leaf row, the grid block positioned at leaf row is extracted first, then from the net
In the output file of process where lattice block, the flow field on the grid block is extracted, finally summarizes to obtain the gridding information of leaf row
And corresponding information of flow, and be output to each leaf and arrange under corresponding file.
Step 4: respectively under the file where each leaf row, the coordinate information of grid block of leaf row and right is read in
Relation information is connect, and reading is located at the flow field data of the cell of the grid block in the heart, then inserts the flow field data of lattice in the heart
It is worth on lattice point.For interested compressor section, such as S1 stream interface, S2 stream interface, S3 stream interface etc., by the cell of grid block
On coordinate and flow field data interpolating to section on point.It does so and breaches existing business the poster processing soft and can only be interpolated into plane
Limitation on section, the flow field on available arbitrary surface.Meanwhile this flow field data that can be arranged each leaf is located respectively
Reason, reduces the demand to personal computer memory.
If necessary to show three-dimensional space information of flow, then by flow field parameter, including density, speed, pressure, sense is calculated
The combination parameter of interest obtains the corresponding coordinate information in interested section (or three-dimensional space) and interested flow field parameter letter
Breath:
Default compressor shaft is x-axis:
ρ: density；U, v, w: along x, the velocity component in tri- directions y, z；Velocity vector；P: static pressure；
R: ideal gas constant；Cp: specific heat at constant pressure；Cv: specific heat at constant volume；Pref: refer to static pressure；ρref: reference density；
ω: rotating speed of gas compressor；X, y, z: coordinate；Specific heat ratio:Static temperature:The velocity of sound:
Speed absolute value:Mach number: Ma=V/a；
Stagnation pressure:
Total temperature:Entropy:Y is to relative velocity: vr=v+ ω z；
Z is to relative velocity: wr=w- ω y；Vorticity:
Step 5: exporting flow-field visualized file according to the interface standard of visual software Tecplot:
The output of grid data point dot interlace will be calculated, is respectively decreased to 1/2 along three grid index directions, total data file reduces
To 1/8.
Step 6: the visualization file that different leaves are arranged is assembled in the visualization file such as Tecplot or Ensight
Together, multistage compressor loopful flow field can be shown.Due to the visualization file very little of each leaf row at this time, assemble
File data amount generally in 1GB hereinafter, can very easily observe on a personal computer compressor Field Characteristics
And analysis.
Claims (5)
1. a kind of aero-engine compressor UNSTEADY FLOW method for visualizing, characterized by the following steps:
Step 1: generating the multi-block structured grid in multistage compressor single blade channel；
Step 2: being input with the grid that step 1 generates, output loopful grid after being rotated, determining opposite joining relation processing, and
Mark the gas compressor blade row where each grid block；
Step 3: all grid blocks to be spread to different processes, when storing flow field, each process individually exports it and divides
The flow field on grid block obtained, and a file is established for each leaf row；
Step 4: being successively read the flow field data of each leaf row, flow field parameter is calculated；
Step 5: exporting flow-field visualized file according to the interface standard of visual software Tecplot.
2. a kind of aero-engine compressor UNSTEADY FLOW method for visualizing according to claim 1, it is characterised in that:
The method for establishing a file described in step 3 for each leaf row is: when collecting the flow field of some leaf row, mentioning first
The grid block for being located at leaf row is taken out, then from the output file of the process where the grid block, extracts the stream on the grid block
, finally summarize to obtain the gridding information and corresponding information of flow of leaf row, and be output to each leaf and arrange corresponding file
Under folder.
3. a kind of aero-engine compressor UNSTEADY FLOW method for visualizing according to claim 1, it is characterised in that:
The method of flow field parameter is calculated described in step 4 are as follows: respectively under the file where each leaf row, read in the grid of leaf row
The coordinate information and opposite joining relation information of block, and reading is located at the flow field data of the cell of the grid block in the heart, then by lattice
On flow field data interpolating to lattice point in the heart；For interested compressor section, by the coordinate on the unit lattice point of grid block
On the data interpolating to section of flow field.
4. a kind of aero-engine compressor UNSTEADY FLOW method for visualizing according to claim 1, it is characterised in that:
The flow field parameter includes:
Compressor shaft is x-axis；
ρ: density；U, v, w: along x, the velocity component in tri- directions y, z；Velocity vector；P: static pressure；
R: ideal gas constant；Cp: specific heat at constant pressure；Cv: specific heat at constant volume；Pref: refer to static pressure；ρref: reference density；
ω: rotating speed of gas compressor；X, y, z: coordinate；Specific heat ratio:Static temperature:The velocity of sound:
Speed absolute value:Mach number: Ma=V/a；
Stagnation pressure:
Total temperature:Entropy:Y is to relative velocity: vr=v+ ω z；
Z is to relative velocity: wr=w- ω y；Vorticity:
5. a kind of aero-engine compressor UNSTEADY FLOW method for visualizing according to claim 1, it is characterised in that:
When exporting flow-field visualized file, the output of grid data point dot interlace will be calculated, is respectively decreased to 1/ along three grid index directions
2, total data file is decreased to 1/8.
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| CN113420379A (en) * | 2021-06-29 | 2021-09-21 | 西北工业大学 | Method for extracting surface-average pressure distribution from CFL3D calculation result |
| CN113515902A (en) * | 2021-06-23 | 2021-10-19 | 中国人民解放军国防科技大学 | Method and device for initializing full-loop unsteady simulation of inner flow of gas compressor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113408073B (en) * | 2021-06-24 | 2023-12-15 | 中国航发沈阳发动机研究所 | Flow field data conversion structure among different components |
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| CN117521563A (en) * | 2024-01-08 | 2024-02-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Pneumatic data processing method based on impeller mechanical turbulence wall distance calculation |
| CN117521563B (en) * | 2024-01-08 | 2024-03-15 | 中国空气动力研究与发展中心计算空气动力研究所 | Pneumatic data processing method based on impeller mechanical turbulence wall distance calculation |
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