CN107977523A - A kind of turbine air cooling blade design method towards parameterized model - Google Patents
A kind of turbine air cooling blade design method towards parameterized model Download PDFInfo
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- CN107977523A CN107977523A CN201711339106.4A CN201711339106A CN107977523A CN 107977523 A CN107977523 A CN 107977523A CN 201711339106 A CN201711339106 A CN 201711339106A CN 107977523 A CN107977523 A CN 107977523A
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Abstract
The present invention relates to blade of aviation engine design, more particularly to a kind of turbine air cooling blade design method towards parameterized model, includes the following steps：Step 1: according to the blade profile coordinate data of acquisition heat exchange data, blade parameter computation model frame is established；Step 2: according to predetermined environmental condition, the basic cooling scheme form of the blade is determined；Step 3: based on parameterized model modeling pattern, using unit design as principle, by pipe network calculation procedure, three-dimensional temperature field result of calculation is obtained；Step 4: form initial scheme；Step 5: the optimization design of blade initial scheme.The turbine air cooling blade design method towards parameterized model of the present invention, the whole design cycle of blade can quickly form initial scheme, and final initial scheme is quickly obtained after optimization design by parametric control according to Calculated Results of Temperature Field.
Description
Technical field
The present invention relates to blade of aviation engine design, more particularly to a kind of turbine air-cooled blade towards parameterized model
Design method.
Background technology
In aero-engine combustion chamber high temperature high-pressure gas, big load centrifugal force, gas are born in turbine air cooling blade working
Power and thermal stress, its conceptual design difficulty is big, the cycle is long, manufacture is of high cost, it is necessary to real using rationally accurate design method
The quick design of existing turbine air-cooled blade.
Turbine air-cooled blade conceptual design need to complete multi-specialized cooperative evaluation --- assess blade according to Performance Parameters
Working environment, turbine pneumatic specialty provide blade profile and heat exchange data, intensity professional assessment blade strength reserve status；Multiprogram string
Connection analysis --- solid modelling, outer heat exchange calculating, cooling system calculating, Temperature calculating, Strength co-mputation are carried out successively；More rounds
Iteration optimization --- the iteration optimization of more rounds need to be completed, parameters and result of calculation is met design requirement.
Existing turbine air-cooled blade Design Method is divided into 5 steps, as shown in Figure 1.Step 1 is pneumatic modelling and changes
The processing of dsc data, step 2 preliminarily form cooling scheme by Parameter analysis, and step 3 carries out entity by frame of tentative programme
CAD is modeled, and step 4 carries out fluid interchange calculating for program model, and step 5 carries out leaf according to the result of step 3 and step 4
Piece strength check, forms initial scheme, and final scheme is formed after more wheel suboptimization are by evaluation.
The shortcomings that this Design Method, is：Turbine air-cooled blade schematic design phase core missions be calculate assessment and
Option screening, since turbine air cooling blade construction is complicated, step 3 is big for the entity CAD modeling time spans of tentative programme, if
It need to iterate, need more long period；Step 4 fluid interchange calculates the model of data and step 3 based on step 1, this process needs
Cutting process, and the structural parameters of each computing unit of manual extraction are carried out to blade physical model, artificial participation is higher, to knot
The extraction of structure parameter can not accomplish the uniformity of method and result, and heavy workload, easily cause the deviation of result of calculation；Formed more
After kind scheme, without clear and definite optimization aim and method, it may cause to screen direction deviation.
The content of the invention
It is existing to solve the object of the present invention is to provide a kind of turbine air cooling blade design method towards parameterized model
There is at least one problem existing for turbine air cooling blade design method.
The technical scheme is that：
A kind of turbine air cooling blade design method towards parameterized model, includes the following steps：
Step 1: according to the blade profile coordinate data of acquisition heat exchange data, blade parameter computation model frame is established；
Step 2: according to predetermined environmental condition, the basic cooling scheme form of the blade is determined；
Step 3: based on parameterized model modeling pattern, using unit design as principle, journey is calculated by pipe network
Sequence, obtains three-dimensional temperature field result of calculation；
Step 4: form initial scheme；
Step 5: the optimization design of blade initial scheme.
Optionally, in the unit design in the step 3, including：
Step 3.1, thickness design：
Control blade radial wall thickness by two root, top sections, by leading edge, string, the position of three points of trailing edge and wall
Thick state modulator blade basin dorsal part wall thickness, designs so as to fulfill the change wall thickness of turbine air-cooled blade, forms blade inner-cavity structure frame
Frame；
Step 3.2, topology design：
Based on predetermined design unit, the inner-cavity structure frame formed using step 3.1 is object, to the snakelike logical of blade
Road carries out topology unit division, and by setting the geometrical characteristic parameter of each unit, by the serpentine channel of blade, several topologys are single
Member connects into pipe network computation model, and then carries out Temperature calculating.
Optionally, it is the bag based on 11 kinds of general design cells in the topology design step of the step 3.2
Include radial passage, turning channel, interconnection, stagnation passage.
Optionally, in the step 5, the optimization design of blade initial scheme includes：
By carrying out strength check to the blade for forming initial scheme in the step 4, judge whether to meet the requirements；It is full
When foot requires, final scheme is formed；Otherwise, return to step three optimizes the control parameter in unit design.
Optionally, it is by changing section chord length control point position in thickness design procedure when strength check is unsatisfactory for
Parameter and control point wall thickness parameter are put to optimize；Wherein
Control point positional representation is represented from leading edge to trailing edge along the percentage of chord length shared by molded line control point, control point wall thickness
The control point wall thickness value.
Optionally, in institute's step 1, the blade profile coordinate data heat exchange data include temperature and the coefficient of heat transfer.
Optionally, in the step 2, the predetermined environmental condition include residing fuel gas temperature, stress level and
Temperature, the stress level of cold air are provided.
Optionally, in the step 2, the basic cooling scheme form of blade includes returning using several passages of several chambers
Turn methods for cooling, and whether use air film hole, stream rib and the cooling structure of turbulence columns.
Invention effect：
The turbine air cooling blade design method towards parameterized model of the present invention, the whole design cycle of blade pass through
Parametric control, can quickly form initial scheme according to Calculated Results of Temperature Field, and quickly be obtained finally after optimization design
Initial scheme.
Brief description of the drawings
Fig. 1 is existing turbine air cooling blade design method flow chart；
Fig. 2 is turbine air cooling blade design method flow chart of the present invention towards parameterized model；
Fig. 3, Fig. 4 are blade inner-cavity structures in the difference turbine air cooling blade design method of the invention towards parameterized model
The schematic diagram at two visual angles of frame；
Fig. 5 is that the present invention divides schematic diagram towards topology unit in the turbine air cooling blade design method of parameterized model；
Fig. 6 is the design cell that the turbine of the present invention towards parameterized model is gas-cooled in blade design method one embodiment
Structure diagram.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
Below in conjunction with the accompanying drawings 2 to Fig. 6 to the present invention towards parameterized model turbine air cooling blade design method do into
One step describes in detail.
The present invention provides a kind of turbine air cooling blade design method towards parameterized model, as shown in Fig. 2, can wrap
Include following steps：
Step S101, according to the blade profile coordinate data of acquisition heat exchange data, blade parameter computation model frame is established.
Wherein, step one of the invention and subsequent step can carry out in predetermined software program；Software can be with
It is automatic to read blade profile coordinate data heat exchange data, establish blade parameter computation model frame.Further, preferred blade profile number of coordinates
Include temperature and the coefficient of heat transfer according to heat exchange data.
Step S102, according to predetermined environmental condition, the basic cooling scheme form of the blade is determined.
In the present embodiment, preferably predetermined environmental condition includes fuel gas temperature, the stress level residing for blade, and provides cold
The temperature of gas, stress level；Further, the basic cooling scheme form of blade includes the revolution cooling shape using several passages of several chambers
Formula, if using air film hole, stream the cooling structures such as rib, turbulence columns and arrangement.
Step S103, based on parameterized model modeling pattern, using unit design as principle, journey is calculated by pipe network
Sequence, obtains three-dimensional temperature field result of calculation.
Wherein, thickness design and topology design are included towards the turbine air cooling blade unit design method of parameterized model.
Thickness designs：
Control blade radial wall thickness by two root, top sections, by leading edge, string, the position of three points of trailing edge and wall
Thick state modulator blade basin dorsal part wall thickness is formed as shown in Figure 3 and Figure 4, it can be achieved that the change wall thickness design of turbine air-cooled blade
Blade inner-cavity structure frame.
Topology design：
Based on predetermined design unit, the inner-cavity structure frame to be formed is designed using thickness as object, to the snakelike of blade
Passage carries out topology unit division, by setting the geometrical characteristic parameter of each unit, by several topologys of the serpentine channel of blade
Unit connects into pipe network computation model, and then carries out Temperature calculating.
Further, in the present embodiment, as shown in fig. 6, be based on 11 kinds of design cells, including radial passage 1, turn
Passage (3,4,5,6, -3, -4, -5, -6), interconnection 2,0 (not shown) of stagnation passage；As shown in figure 5, designed again with thickness
The inner-cavity structure frame that step is formed is object, and topology unit division is carried out to the serpentine channel of blade；Finally, it is each by setting
The geometrical characteristic parameter of unit, several topology units can connect into pipe network computation model, Jin Erjin by the serpentine channel of blade
Trip temperature field computation.
Step S104, initial scheme is formed.
Step S105, the optimization design of blade initial scheme.
Wherein, the optimization design of blade initial scheme includes：
By carrying out strength check to the blade for forming initial scheme in the step 4, judge whether to meet the requirements；It is full
When foot requires, final scheme is formed；Otherwise, return to step three optimizes the control parameter in unit design.
Specifically, it is by changing section chord length control point position in thickness design procedure when strength check is unsatisfactory for
Parameter and control point wall thickness parameter are put to optimize；Wherein, control point positional representation is controlled from leading edge to trailing edge along molded line
The percentage of chord length, control point wall thickness represent the control point wall thickness value shared by point.
In other words, step 4 and the optimization design that step 5 is blade initial scheme, pass through cured design cycle, weight
The design process of multiple step 3, can quickly obtain the temperature computation of kinds of schemes as a result, program can realize that crucial calculate is tied automatically
The interpretation of fruit parameter, realizes the more round optimization designs of blade scheme in the shorter cycle.
In the turbine air cooling blade design method towards parameterized model of the present invention, the whole design cycle of blade is logical
Parametric control is crossed, therefore according to Calculated Results of Temperature Field, it is only necessary to the control parameter of topology unit is optimized, you can quick
To improved Calculated Results of Temperature Field, without design iterations flow.
By taking wall thickness designs as an example, if after a wheel design is completed, strength assessment is thought wall thickness need to be thinned to increase intensity
Deposit, complete design iterations flow is, it is necessary to a complete design cycle conventional method is needed three since Fig. 1 the step of.And
The turbine air cooling blade design method of invention only need to change the section chord length control point parameter in platform interface, as shown in table 1, control
For system point positional representation along the percentage of chord length shared by molded line control point from leading edge to trailing edge, control point wall thickness represents the control point wall
Thickness is worth, and the wall thickness value at control point is changed in 1 squadron's string of table, and result of calculation can be exported immediately for by force after preserving modification
Degree assessment, is rapidly completed Curve guide impeller.
1 blade wall thickness control parameter of table
In the turbine air cooling blade design method towards parameterized model of the present invention, joined by establishing turbine air-cooled blade
Numberization model, and with special parameter form control cooling structure, realize that boundary condition loads automatically, complete blades flows heat exchange point
Analysis, realizes that turbine air-cooled blade scheme quickly designs.In the blade schematic design phase, towards the turbine air cooling leaf of parameterized model
Piece topology unit design method realizes blade in the case of incorporeity model, using unit design as principle, passes through parameter
Change modeling pattern and establish blade computation model, automatically extract calculating data, quickly obtain Calculated Results of Temperature Field.Blade it is whole
Design cycle is by parametric control, therefore according to Calculated Results of Temperature Field, it is only necessary to the control parameter of topology unit is carried out excellent
Change and (to the setting key parameter control of each cooling structure, the blade parameter model for calculating can be established within a short period of time),
Improved Calculated Results of Temperature Field can be quickly obtained, without design iterations flow, significantly reduces the optimization design cycle.
In addition, in the turbine air cooling blade design method towards parameterized model of the present invention, for heat analysis and flowing
The calculating data of analysis, each cooling structure key parameter extraction of blade that can be directly inputted in the modeling process based on parametrization
Or conversion, without carrying out any processing to model.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can readily occur in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (7)
- The blade design method 1. a kind of turbine towards parameterized model is gas-cooled, it is characterised in that include the following steps：Step 1: according to the blade profile coordinate data of acquisition heat exchange data, blade parameter computation model frame is established；Step 2: according to predetermined environmental condition, the basic cooling scheme form of the blade is determined；Step 3: based on parameterized model modeling pattern, using unit design as principle, by pipe network calculation procedure, obtain To three-dimensional temperature field result of calculation；Step 4: form initial scheme；Step 5: the optimization design of blade initial scheme.
- The blade design method 2. turbine according to claim 1 is gas-cooled, it is characterised in that the unit in the step 3 In design, including：Step 3.1, thickness design：Control blade radial wall thickness by two root, top sections, by leading edge, string, the position of three points of trailing edge and wall thickness join Number control blade basin dorsal part wall thickness, designs so as to fulfill the change wall thickness of turbine air-cooled blade, forms blade inner-cavity structure frame；Step 3.2, topology design：Based on predetermined design unit, the inner-cavity structure frame formed using step 3.1 as object, to the serpentine channel of blade into Row topology unit divides, and by setting the geometrical characteristic parameter of each unit, by the serpentine channel of blade, several topology units connect Pipe network computation model is connected into, and then carries out Temperature calculating.
- The blade design method 3. turbine according to claim 2 is gas-cooled, it is characterised in that in the step 5, at the beginning of blade The optimization design of beginning scheme includes：By carrying out strength check to the blade for forming initial scheme in the step 4, judge whether to meet the requirements；Meeting will When asking, final scheme is formed；Otherwise, return to step three optimizes the control parameter in unit design.
- The blade design method 4. turbine according to claim 3 is gas-cooled, it is characterised in that when strength check is unsatisfactory for, It is to be optimized in thickness design procedure by changing section chord length control point location parameter and control point wall thickness parameter； WhereinControl point positional representation represents the control from leading edge to trailing edge along the percentage of chord length shared by molded line control point, control point wall thickness System point wall thickness value.
- The blade design method 5. turbine according to claim 1 is gas-cooled, it is characterised in that in institute's step 1, the leaf Type coordinate data heat exchange data include temperature and the coefficient of heat transfer.
- The blade design method 6. turbine according to claim 5 is gas-cooled, it is characterised in that described in the step 2 Predetermined environmental condition includes residing fuel gas temperature, stress level and provides the temperature of cold air, stress level.
- The blade design method 7. turbine according to claim 6 is gas-cooled, it is characterised in that described in the step 2 The basic cooling scheme form of blade includes the revolution methods for cooling using several passages of several chambers, and whether uses air film hole, streams The cooling structure of rib and turbulence columns.
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| CN110096776A (en) * | 2019-04-22 | 2019-08-06 | 西北工业大学 | The parametric modeling of shaped air film hole and orientations optimized method on single crystal turbine blade |
| 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 |
| CN111783306A (en) * | 2020-07-06 | 2020-10-16 | 中国航发湖南动力机械研究所 | Turbine blade cold air quantity and cold effect characteristic analysis method |
| CN112035981A (en) * | 2020-09-08 | 2020-12-04 | 北京航空航天大学 | Modeling method for turbine blade laminate cooling structure |
| CN112380651A (en) * | 2020-11-13 | 2021-02-19 | 中国航发沈阳发动机研究所 | Method for extracting topological data of turbine cooling blade pipe network |
| CN113172726A (en) * | 2021-04-09 | 2021-07-27 | 西安交通大学 | Hollow turbine blade ceramic casting mold based on 3D printing and precision control method and application thereof |
| CN114151139A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Method for simulating flow of air film hole cold air layer on surface of turbine blade by adopting permeation model |
| CN114676533A (en) * | 2022-05-26 | 2022-06-28 | 中国航发四川燃气涡轮研究院 | Turbine moving blade cooling sensitivity analysis method coupled with air system |
| CN115688327A (en) * | 2022-12-27 | 2023-02-03 | 中国航发沈阳发动机研究所 | Turbine blade temperature field calculation method with subareas and variable-thickness thermal barrier coating |
| CN115788598A (en) * | 2023-02-10 | 2023-03-14 | 中国航发四川燃气涡轮研究院 | Turbine blade air film hole parametric control and design method |
| CN116976201A (en) * | 2023-07-10 | 2023-10-31 | 哈尔滨工业大学 | Self-programming parameterized modeling method and modeling system for micro turbine blade of breathing machine, computer readable storage medium and electronic equipment |
| CN117436344A (en) * | 2023-11-10 | 2024-01-23 | 沈阳工业大学 | Wind turbine blade structure optimization design method based on parameterization description |
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| CN110096776B (en) * | 2019-04-22 | 2022-07-19 | 西北工业大学 | Parametric modeling and orientation optimization method for special-shaped air film holes on single-crystal turbine blade |
| CN110096776A (en) * | 2019-04-22 | 2019-08-06 | 西北工业大学 | The parametric modeling of shaped air film hole and orientations optimized method on single crystal turbine blade |
| CN111274730B (en) * | 2020-01-22 | 2022-06-28 | 南京航空航天大学 | Iterative optimization design method for turbine blade disc of air turbine starter |
| 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 |
| CN111783306A (en) * | 2020-07-06 | 2020-10-16 | 中国航发湖南动力机械研究所 | Turbine blade cold air quantity and cold effect characteristic analysis method |
| CN111783306B (en) * | 2020-07-06 | 2022-11-18 | 中国航发湖南动力机械研究所 | Turbine blade cold air quantity and cold effect characteristic analysis method |
| CN112035981B (en) * | 2020-09-08 | 2021-06-22 | 北京航空航天大学 | Modeling method for turbine blade laminate cooling structure |
| CN112035981A (en) * | 2020-09-08 | 2020-12-04 | 北京航空航天大学 | Modeling method for turbine blade laminate cooling structure |
| CN112380651A (en) * | 2020-11-13 | 2021-02-19 | 中国航发沈阳发动机研究所 | Method for extracting topological data of turbine cooling blade pipe network |
| CN112380651B (en) * | 2020-11-13 | 2022-09-20 | 中国航发沈阳发动机研究所 | Method for extracting topological data of turbine cooling blade pipe network |
| CN113172726A (en) * | 2021-04-09 | 2021-07-27 | 西安交通大学 | Hollow turbine blade ceramic casting mold based on 3D printing and precision control method and application thereof |
| CN114151139A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Method for simulating flow of air film hole cold air layer on surface of turbine blade by adopting permeation model |
| CN114151139B (en) * | 2021-10-20 | 2023-09-19 | 中国航发四川燃气涡轮研究院 | Method for simulating cold air layer flow of air film holes on surface of turbine blade by adopting permeation model |
| CN114676533B (en) * | 2022-05-26 | 2022-08-02 | 中国航发四川燃气涡轮研究院 | Turbine moving blade cooling sensitivity analysis method coupled with air system |
| CN114676533A (en) * | 2022-05-26 | 2022-06-28 | 中国航发四川燃气涡轮研究院 | Turbine moving blade cooling sensitivity analysis method coupled with air system |
| CN115688327A (en) * | 2022-12-27 | 2023-02-03 | 中国航发沈阳发动机研究所 | Turbine blade temperature field calculation method with subareas and variable-thickness thermal barrier coating |
| CN115788598A (en) * | 2023-02-10 | 2023-03-14 | 中国航发四川燃气涡轮研究院 | Turbine blade air film hole parametric control and design method |
| CN115788598B (en) * | 2023-02-10 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Turbine blade air film hole parameterization control and design method |
| CN116976201A (en) * | 2023-07-10 | 2023-10-31 | 哈尔滨工业大学 | Self-programming parameterized modeling method and modeling system for micro turbine blade of breathing machine, computer readable storage medium and electronic equipment |
| CN117436344A (en) * | 2023-11-10 | 2024-01-23 | 沈阳工业大学 | Wind turbine blade structure optimization design method based on parameterization description |
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