CN106354967A - Turbine disk structure design and analysis integrated method - Google Patents
Turbine disk structure design and analysis integrated method Download PDFInfo
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- CN106354967A CN106354967A CN201610815836.6A CN201610815836A CN106354967A CN 106354967 A CN106354967 A CN 106354967A CN 201610815836 A CN201610815836 A CN 201610815836A CN 106354967 A CN106354967 A CN 106354967A
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- 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
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
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- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
Abstract
A turbine disk structure design and analysis integrated method comprises the following steps: in the modeling design stage, the analysis characteristics of a model topological structure is constructed based on intrinsic properties; based on this, a designer can restrain or load the corresponding topological structure on the basis of the actual function of the structure, and a finite element analysis loading file is formed in the design stage; an entity model with analysis characteristics is analyzed by a boundary representation method (B-Rep), attribute information is allowed to be associated with geometric data, and then a geometric file which can be identified by a sub-network software is outputted, the attribute information is used for defining a self-adaptive sub-network strategy, so as to generate a gird model; the loading file and the grid model promote the finite element analysis, if the design requirement is not met, a design modification is needed, and after the design modification, geometric data is changed; the loading file is not affected by the change of geometric data due to the attribute association with the topological structure, and the grid automatic re-consitution of the gird model can be achieved through the self-adaptive sub-network strategy; and after the design modification, the integration of the design and the analysis is achieved.
Description
Technical field
The present invention is a kind of design and analysis method of aero-turbine rotatable parts structure, and it can help structure
Designer quickly carries out the assessment such as intensity, life-span in the design phase to structure, and by realizing analysis model and designing a model
Auto-associating it is ensured that design a model occur change in design when, the structure check results after change can be quickly obtained,
Greatly improve quality and the efficiency of design, belong to Aero-Space technical field of engines.
Background technology
The turbine disk is the structural key part of aero-engine, and its fault will produce sternly to the normal work of aero-engine
The impact of weight, the therefore good design of the turbine disk and safe and reliable work are to the durability ensureing electromotor and aircraft and reliability
Most important.Aero-engine turbine disk type face is usually relatively complex, need using the design phase just consider its performance,
Life-span and reliability it is necessary to be estimated so that " design-analysis-Amending design-weight by Finite Element Method to designing quality
This process of analysis " needs carrying out repeatedly, constantly looks for optimal design, the detached method for designing of traditional design and analysis is
Demand cannot be met.How to improve design efficiency and design accuracy is problem demanding prompt solution in Realism Design work.Although
Design and analysis are all in the face of same design object, but because the side of concern is different and the development of history, both use
Model make a big difference in itself.Design a model and be often primarily upon forming the geometric properties of design object, and analyze
Conventional FEM (finite element) model then more pays close attention to point analysis feature such as power and constraint on design object.As design upstream design a model by
In deletion analysises feature, cause to be difficult to the conversion between accurately and effectively Coordination Model between design tool and analytical tool, that is,
Make to couple together design tool and analytical tool using integrated platform, but integration to be realized also faces model difference and brought
Mesh dependence, data conversion stability, adaptive mesh quality the problems such as.Have in some mechanical design field at present
By cae software is carried out with the analytical system of structure of secondary development foundation, but aero-engine field relatively, its model structure is relatively
Simply, it is confined to specific situation it is difficult to directly apply to the analysis of aero-engine modular construction.
Content of the invention
The technology of the present invention solution: overcome the deficiencies in the prior art, a kind of turbine disc structure structural design analysis are provided
Integral method, by increasing analysis information and feature for designing a model, smoothes out the gully designing a model and analysis model between,
Making the design analysis model of one, thus will design to get up with analyzing and associating from model level, building during design
Vertical analysis model directly assesses design result, realizes Integrated design and analysis, is quickly obtained the structure check results after change,
Greatly improve quality and the efficiency of design.
The technology of the present invention solution: the invention mainly comprises 5 is most of: the turbine disk model with analysis feature for the foundation,
Form load document, turbine disk model conversion and grid model generation, structural strength/durability analysis, Amending design to reappraise.
Realize step as follows:
1) geometric properties according to turbine disc structure and analysis feature, soft using the most frequently used modeling in aero-engine field
Part unigraphics nx sets up the physical model of turbine disc structure, to the turbine disk physical model set up, using ug open
The uf_attr_assign function that api provides is each topological structure such as point, line, surface of turbine disk physical model etc., sets up
Iccfd_family attribute, the turbine disk model obtaining after the completion of modeling has iccfd_family attribute；Described geometric properties
Refer to the geometry of turbine disk physical model, described analysis feature refers to turbine disk physical model various pieces in real work
In bear load restraint analysis characteristic；
By carrying out the establishment of physical model using modeling software, but the model that common business modeling software is built is not
With analysis information, so the api that modeling software is provided is that application programming interfaces are programmed and then realize in modeling process
Analysis information required for the middle establishment present invention, this is referred to as secondary development to the work that modeling software is programmed；
2) the ufsta entrance function utilizing ug open api to provide, is based in modeling software unigraphics nx
Mfc exploitation analysis information input interface, designer's function in real work according to each topological structure of the turbine disk, for each
The iccfd_family attribute of individual topological structure gives the analysis information of real work, including load, constraint etc., Suo Youyu
The analysis information output portion load document of iccfd_family Attribute Association；
3) utilize b-rep B reps by step 1) turbine disk entity mould with iccfd_family attribute set up
Type, the data form according to geometric model input file tertin in subnetting software icemcfd carries out model conversion, generates a
The subnetting input file of turbine disk model, utilizes iccfd_family attribute invariance in subnetting software ansys icemcfd
Principle, carries out stress and strain model to the subnetting input file formulation Gridding Method of turbine disk model, obtains grid model；
4) the ufsta entrance function utilizing ug open api to provide, is based in modeling software unigraphics nx
Mfc by finite element solving software ansys the most frequently used for turbine disc structure intensity durability analysis be integrated to modeling software formed limited
Unit solves module, by using step 2) load document that obtains and step 3) grid model that obtains carries out structural strength/tired
Labor restricted lifetime meta-analysis, obtain the Finite element analysis results of turbine disc structure；
5) according to step 4) the turbine disc structure finite element analyses fruit data that obtains, the designing quality of turbine disc structure is entered
Row assessment, if analyze meeting design requirement, complete design, otherwise according to feedback data Amending design, turbine disk model geometric
After sized data is modified, enter step 3) carry out model conversion, subsequently enter step 4) carry out finite element analyses, according to analysis
Result is in step 5) in rejudge, be met the turbine disk model of design requirement by way of iteration.
Present invention advantage compared with prior art is: a kind of integration of present invention turbine disc structure structural design analysis
Method, compared with traditional method, analyzes feature by increasing for designing a model, thus will design and analyzing and associating from model level
Get up, help designer, in the design phase, structure is quickly carried out with the assessment such as intensity, life-span, and pass through mesh adaption strategy
With automatic reloading technology it is ensured that when designing a model generation change in design, the structure school after change can be quickly obtained
Test result, greatly improve quality and the efficiency of design.
Brief description
Fig. 1 is a kind of present invention turbine disc structure Integrated design and analysis method flow diagram；
Fig. 2 is that the present invention sets up attribute when setting up turbine disk physical model for its analysis feature, as shown is installation
While with the addition of iccfd_family attribute；
Fig. 3 analyzes information input interface for the present invention, and each iccfd_family by being set up in physical model divides
Analysis attribute, according to the practical situation input corresponding analysis information of model；
Fig. 4 is the finite element analysis module interface schematic diagram in the structural design analysis integral system of the present invention.
Specific embodiment
Below in conjunction with the accompanying drawings, a kind of technical scheme of present invention turbine disc structure Integrated design and analysis method is done into one
Step explanation.
The structure design of the turbine disk is one again and repeatedly repeatedly designs the process constantly looking for optimal design, sets for structure
How to improve the problem of design efficiency and design accuracy, a kind of turbine disc structure of body of the present invention sets in meter personnel's practical work
Meter analysis integral method, its flow process is shown in Fig. 1.
1) geometric properties according to turbine disc structure and analysis feature, soft using the most frequently used modeling in aero-engine field
Part unigraphics nx sets up the physical model of turbine disc structure, to the turbine disk physical model set up, (wherein modeling software
Unigraphics nx is provided and can be called by c/c++ language, thus realize User Defined operation with
The application programming interfaces tool kit of unigraphics nx modeling environment direct interaction, i.e. ug open api), in the present invention,
Each topology knot being turbine disk physical model using the attribute partition function uf_attr_assign providing in ug open api
Structure such as point, line, surface etc., (wherein iccfd_family is in subnetting software and finite element analyses to set up iccfd_family attribute
Software has the Data Identification variable of joint declaration, is kept in each transmittance process by the data that this attribute can ensure that model
Uniqueness), the turbine disk model obtaining after the completion of modeling has iccfd_family attribute, implements step and is:
1.1) in the present invention attribute is added to all faces of turbine disk model, the process of realizing of the present invention is that aviation is sent out
Motivation commonly use design setting model software unigraphics nx carry out secondary development, in the modeling process of the turbine disk by using
Ug open api provide searching loop function uf_obj_cycle_objs_in_part obtain turbine disk physical model each
No. tag of topological structure；
1.2) according to step 1.1) obtain No. tag, using the Access Model surface element traversal providing in ug open api
Function uf_modl_ask_body_faces finds turbine disk model all of face topological element；
1.3) according to step 1.2) the face topological element that obtains is face topological element wound using uf_attr_assign function
Build iccfd_family attribute, the installation side of the turbine disk as shown in Figure 2 with the addition of iccfd_family in modeling process, with
Reason, turbine disk others face also all establishes iccfd_family attribute in modeling process, and iccfd_family attribute is dividing
The turbine that recognition marks as subnetting and loading, this step are set up by net software icemcfd and finite element analysis software ansys
Disk model is the physical model with analysis attribute；
2) the ufsta entrance function utilizing ug open api to provide, is based in modeling software unigraphics nx
Mfc exploitation analysis information input interface, designer's function in real work according to each topological structure of the turbine disk, for each
The iccfd_family attribute of individual topological structure gives the analysis information of real work, including load, constraint etc., Suo Youyu
The analysis information output portion load document of iccfd_family Attribute Association, as shown in figure 3, designer ties according to the turbine disk
Structure installs side to be needed to add displacement constraint in analysis, and the analysis attribute for installing side feature gives corresponding displacement constraint, and
Need at tongue-and-groove add centrifugal force, then for tongue-and-groove feature analysis attribute give corresponding centrifugal force numerical value, other kinds of about
In the same manner, all storage in the way of text with iccfd_family Attribute Association load information forms portion for bundle or load
Load document；
3) utilize b-rep B reps by step 1) turbine disk entity mould with iccfd_family attribute set up
Type, (wherein, the data form according to geometric model input file tertin in subnetting software icemcfd carries out model conversion
Tertin is the geometry input file of subnetting software icemcfd, and tertin file is used for preserving the point, line, surface with TRANSFER MODEL
With 4 kinds of data of iccfd_family attribute, these data are used for icemcfd subnetting and carry analysis information), generate a whirlpool
The subnetting input file of wheel disc model, utilizes iccfd_family attribute invariance former in subnetting software ansys icemcfd
Then, Gridding Method is formulated to the subnetting input file of turbine disk model and carry out stress and strain model, obtain grid model, specifically real
Existing step is:
3.1) according to step 1) the middle turbine disk physical model set up, using offer physical model side in ug open api
Topological structure access function uf_brep_ask_topology under boundary's representation acquires each topology of turbine disk model
Structure；
3.2) utilize in ug open api and attribute data access function uf_attr_read_value accessing step is provided
3.1) the iccfd_family attribute information of the topological structure obtaining；
3.3) utilize the geometric data access function uf_ that physical model boundary representation FAXIA is provided in ug open api
Brep_ask_geometry accessing step 3.1) geometric data accompanying by topological structure that obtains；
3.4) attribute information of turbine disk model and geometric data are pressed subnetting input file in subnetting software icemcfd
The form of tertin preserves；
3.5) according to step 3.4) the tertin file that obtains, in tertin file, there is iccfd_ in all of face of model
Family attribute, in subnetting software icemcfd, the shape that all these faces surround is the entity mould of former turbine disk model
Type, due to changing the change that only can cause geometric data on face after the size of model, and all geometric datas on face all with genus
Property association, and Amending design can't cause the change of attribute, so by the iccfd_family attribute in tertin file
Invariance principle, to turbine disk model subnetting strategy generating grid model in icemcfd, and this subnetting strategy is in mould
Type turbine disk model geometric size changes, but when topological structure does not change, model meshes self-adaptative adjustment is to adapt to
The change of turbine disc structure size, and the modification of topological structure is often little in the structure design of aero-engine turbine disk,
More situations are the adjustment of size, so the adaptive strategy that the present invention is carried can realize grid automatically divide, very well again
The demand meeting Integrated design and analysis.
4) (wherein ufsta function is for providing in ug open api for the ufsta entrance function utilizing ug open api to provide
Internal processes entrance function, internal processes refer to the executable program of embedded ug modeling software, and external program refers to take off
From the executable program of ug modeling environment independent operating, in the present invention, using the development mode of internal processes, develop gained
Program can directly be run in modeling software ug, and then realizes modeling and analyzing carrying out in unified environment), soft modeling
Based on mfc by finite element solving software ansys the most frequently used for turbine disc structure intensity durability analysis in part unigraphics nx
It is integrated to modeling software and form finite element solving module, by using step 2) load document that obtains and step 3) net that obtains
Lattice model carries out structural strength/limited fatigue life meta-analysis, obtains the Finite element analysis results of turbine disc structure；
5) according to step 4) the turbine disc structure finite element analyses fruit data that obtains, the designing quality of turbine disc structure is entered
Row assessment, if analyze meeting design requirement, complete design, otherwise according to feedback data Amending design, turbine disk model geometric
After sized data is modified, enter step 3) carry out model conversion, subsequently enter step 4) carry out finite element analyses, according to analysis
Result is in step 5) in rejudge, be met the turbine disk model of design requirement by way of iteration.
There is provided above example to be used for the purpose of the description purpose of the present invention, and be not intended to limit the scope of the present invention.This
The scope of invention is defined by the following claims.Various equivalents made without departing from spirit and principles of the present invention and repairing
Change, all should cover within the scope of the present invention.
Claims (3)
1. a kind of turbine disc structure Integrated design and analysis method it is characterised in that: include set up band analyze feature the turbine disk
Model, formation load document, turbine disk model conversion and grid model generation, structural strength/durability analysis, Amending design are again
Assessment, implements step as follows:
(1) geometric properties according to turbine disc structure and analysis feature, set up turbine using modeling software unigraphics nx
The physical model of dish structure, to the turbine disk physical model set up, the uf_attr_assign letter being provided using ug open api
Number is the point, line, surface of each topological structure of turbine disk physical model, sets up iccfd_family attribute, after the completion of modeling
To turbine disk model there is iccfd_family attribute；Described geometric properties refer to the geometry of turbine disk physical model,
Described analysis feature refers to the load restraint analysis characteristic that turbine disk physical model various pieces are born in real work；
(2) the ufsta entrance function utilizing ug open api to provide, is opened based on mfc in modeling software unigraphics nx
Send out analysis information input interface, designer's function in real work according to each topological structure of the turbine disk, open up for each
The iccfd_family attribute flutterring structure gives the analysis information of real work, including load, constraint, all and iccfd_
The analysis information output portion load document of family Attribute Association；
(3) turbine disk physical model with iccfd_family attribute step (1) set up using b-rep B reps,
Data form according to geometric model input file tertin in subnetting software icemcfd carries out model conversion, generates a whirlpool
The subnetting input file of wheel disc model, utilizes iccfd_family attribute invariance principle, to whirlpool in subnetting software icemcfd
The subnetting input file of wheel disc model is formulated Gridding Method and is carried out stress and strain model, obtains grid model；
(4) utilize the ufsta entrance function that ug open api provides, being based on mfc in modeling software unigraphics nx will
The most frequently used finite element solving software ansys of turbine disc structure intensity durability analysis is integrated to modeling software and forms finite element solving
The grid model that module, the load document obtaining by using step (2) and step (3) obtain carries out structural strength/fatigue longevity
Life finite element analyses, obtain the Finite element analysis results of turbine disc structure；
(5) the turbine disc structure finite element analyses fruit data being obtained according to step (4), is carried out to the designing quality of turbine disc structure
Assessment, if analyze meeting design requirement, complete design, otherwise according to feedback data Amending design, turbine disk model geometric chi
After very little data is modified, enters step (3) and carry out model conversion, subsequently enter step (4) and carry out finite element analyses, according to analysis
Result rejudges in step (5), is met the turbine disk model of design requirement by way of iteration.
2. a kind of turbine disc structure design integration method according to claim 1 it is characterised in that: described step (1)
In, establish analysis feature in the modelling phase by the way of model iccfd_family attribute, described iccfd_family belongs to
Property establishment step is as follows:
(11) the searching loop function uf_obj_ providing by using ug open api in the modeling process of the turbine disk
Cycle_objs_in_part obtains No. tag of the turbine disk each topological structure of physical model；
(12) No. tag being obtained according to step (11), finds turbine disk model using uf_modl_ask_body_faces and owns
Face topological element；
(13) the face topological element being obtained according to step (12), is created for face topological element using uf_attr_assign function
Iccfd_family attribute.
3. a kind of turbine disc structure design integration method according to claim 1 it is characterised in that: described step (3)
In, it is as follows that b-rep method realizes step:
(31) each topological structure of turbine disk model is acquired using uf_brep_ask_topology；
(32) the iccfd_family attribute letter of the topological structure being obtained using uf_attr_read_value accessing step (31)
Breath；
(33) geometric data accompanying by topological structure being obtained using uf_brep_ask_geometry accessing step (31)；
(34) attribute information of turbine disk model and geometric data are pressed subnetting input file tertin in subnetting software icemcfd
Form preserve；
(35) the corresponding geometric data of iccfd_family attribute in the tertin file being obtained according to step (34), formulates subnetting
Strategy carries out stress and strain model and obtains grid model, after model is modified, former according to iccfd_family attribute invariance
Then, grid model divides automatically according to subnetting strategy again.
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| CN108629092A (en) * | 2018-04-20 | 2018-10-09 | 北京航空航天大学 | One kind being based on the modified turbine disk subregion analysis method for reliability of dimensional effect |
| CN110851121A (en) * | 2019-10-30 | 2020-02-28 | 中国航空工业集团公司西安飞行自动控制研究所 | Gridding flight management system man-machine interaction design and realization method |
| CN111274730A (en) * | 2020-01-22 | 2020-06-12 | 南京航空航天大学 | Iterative optimization design method for turbine blade disc of air turbine starter |
| CN111353249A (en) * | 2020-03-02 | 2020-06-30 | 厦门大学 | Non-circular vent hole integrated design optimization method for turbine sealing disc |
| CN111382529A (en) * | 2019-10-30 | 2020-07-07 | 上海核工程研究设计院有限公司 | Method for converting support Modeller support hanger design model into analysis model |
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| CN111274730A (en) * | 2020-01-22 | 2020-06-12 | 南京航空航天大学 | Iterative optimization design method for turbine blade disc of air turbine starter |
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| CN111353249A (en) * | 2020-03-02 | 2020-06-30 | 厦门大学 | Non-circular vent hole integrated design optimization method for turbine sealing disc |
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Effective date of registration: 20211222 Address after: Room 902A, floor 9, building 2, Xin 2, East Third Ring North Road, Chaoyang District, Beijing 100027 Patentee after: YUNYI SUPERCOMPUTING (BEIJING) SOFTWARE TECHNOLOGY CO.,LTD. Address before: 100027 room 902B, 9 / F, building 2, xin2, North East Third Ring Road, Chaoyang District, Beijing Patentee before: Beijing Chuanglian smart Soft Technology Co.,Ltd. |
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