CN113408073A - Flow field data conversion structure between different components - Google Patents
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- CN113408073A CN113408073A CN202110716100.4A CN202110716100A CN113408073A CN 113408073 A CN113408073 A CN 113408073A CN 202110716100 A CN202110716100 A CN 202110716100A CN 113408073 A CN113408073 A CN 113408073A
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- 238000006243 chemical reaction Methods 0.000 title claims abstract description 52
- 238000003032 molecular docking Methods 0.000 claims description 6
- 238000005094 computer simulation Methods 0.000 claims description 5
- 230000010076 replication Effects 0.000 claims description 3
- 238000004364 calculation method Methods 0.000 abstract description 28
- 238000000034 method Methods 0.000 abstract description 6
- 210000001503 joint Anatomy 0.000 abstract description 3
- 230000003044 adaptive effect Effects 0.000 abstract 2
- 239000007921 spray Substances 0.000 description 7
- 230000003416 augmentation Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
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- 230000008859 change Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
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- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/08—Thermal analysis or thermal optimisation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The application belongs to the technical field of engine tests, and particularly relates to a flow field data conversion structure between different components. The data conversion structure comprises a data conversion inlet, a data conversion outlet and an intermediate section, wherein the cross section of the data conversion inlet is circular, the circular cross section of the data conversion inlet comprises a plurality of same first fan-shaped cross sections, the size of each first fan-shaped cross section is set to be adaptive to a butt joint front end part, the circular cross section of the data conversion outlet comprises a plurality of same second fan-shaped cross sections, the size of each second fan-shaped cross section is set to be adaptive to a butt joint rear end part, the intermediate section is arranged between the data conversion inlet and the data conversion outlet and used for rotationally copying to form circular cross section data and cutting the circular cross section data, and the front end part and the rear end part are two adjacent parts in the structure of an aircraft engine flow field. The method and the device ensure complete connection of data in different interface forms, ensure continuous calculation of the flow field of the aircraft engine, and improve the calculation efficiency.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to a flow field data conversion structure between different components.
Background
The engine model is complex, comprises a plurality of complex structures such as a rotating structure (blade), a complex air film hole cooling structure (combustion chamber), a plurality of small structures (oil injection rod) and the like, and pneumatic states of all parts are different, including rotating flow, a combustion field, subsonic flow, supersonic flow and the like.
The structure of each part calculation model in the engine numerical calculation is very different, for example, the stress application part model is a fan-shaped model (one-sixth or one-eighth sector), and the nozzle calculation model is a circumferential 360-degree model or a circumferential one-half model. In the numerical calculation process, data information (temperature and pressure) of different parts needs to be called, for example, outlet data of a force application part is an inlet parameter required by the calculation of the spray pipe. However, the data among the components is set to be a value, so that three-dimensional data distribution cannot be reflected, and the precision is poor; meanwhile, the models are inconsistent and cannot be directly called.
In the technical aspect, no special numerical value conversion structure exists at the present stage, and the traditional numerical value calculation method arranges an upstream part into a temperature value, a pressure value and a flow value, and uses the data as an inlet parameter to carry out numerical value calculation by using the data as a downstream part. The spatial distribution difference of each parameter cannot be reflected, the error is large, the calculation of the wall temperature is greatly influenced, and the evaluation of the temperature and the cooling measure has large error, so that the scheme design and the material selection are influenced.
Disclosure of Invention
In order to solve the technical problem, the application provides a flow field data conversion structure between different components, so that data transmission between different structures of different components is realized, data information under different position coordinates is reserved, efficient data transmission is ensured, numerical calculation accuracy can be greatly improved, and the structure has important significance for design and improvement of an engine.
The flow field data conversion structure between different components comprises a data conversion inlet with a circular section, a data conversion outlet and a middle section, the circular cross-section of the data conversion inlet includes a plurality of identical first fan-shaped cross-sections sized to fit into the docking front-end component, the circular cross-section of the data conversion outlet includes a plurality of identical second fan-shaped cross-sections sized to fit into the docking back end component, the intermediate section disposed between the data conversion inlet and the data conversion outlet, used for receiving the first sector section data, carrying out rotary replication to form circular section data, and cutting the circular section data according to the second sector section to form second sector section data, wherein the front end part and the back end part are two adjacent parts on the flow field structure of the aircraft engine.
Preferably, the first fan-shaped cross-section is dimensioned to be covered by at least the trailing outlet of the leading end member.
Preferably, the second fan-shaped cross-section is dimensioned to cover at least the inlet of the back end part.
Preferably, the first and second sector cross-sectional data include temperature.
Preferably, the first and second sector cross-sectional data include pressure.
Preferably, the front end part is an aircraft engine force application part calculation model, and the first fan-shaped section is a circular sector with one-sixth or one-eighth of the cross section.
Preferably, the rear end part is a nozzle calculation model, and the second fan-shaped cross section is a half circular sector or a 360 ° circle.
The application provides a data conversion structure, which can improve the precision of data conversion in the process of multi-component numerical calculation analysis and the precision of flow field calculation. The method has the advantages that the difficulty that the connection calculation cannot be carried out due to the shape and the size of different calculation interfaces is eliminated, the sector data are converted into the circumferential 360-degree data, the sector data at different angles or a specific structure through the conversion structure, the complete connection of the data in different interface forms is ensured, the flow field connection calculation of the aircraft engine (including thrust augmentation and spray pipe) is ensured, compared with the mode that a thrust augmentation spray pipe model is combined for direct calculation, the grid quantity and the difficulty are greatly reduced, and the calculation efficiency is improved.
Drawings
Fig. 1 is a schematic structural diagram of a preferred embodiment of a flow field data conversion structure between different components of the present application.
Fig. 2 is a schematic diagram of the data of the force model flow field according to the embodiment shown in fig. 1 of the present application.
FIG. 3 is a schematic view of the inlet sector data of the embodiment of FIG. 1 of the present application.
FIG. 4 is a 360 circular data diagram of the embodiment of FIG. 1 of the present application.
FIG. 5 is a graphical illustration of the exit sector data for the embodiment of FIG. 1 of the present application.
FIG. 6 is a schematic view of nozzle computational model flow field data according to the embodiment of FIG. 1 of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a flow field data conversion structure among different components, as shown in figure 1, which mainly comprises a data conversion inlet, a data conversion outlet and a middle section, wherein the cross section of the data conversion inlet is circular, the circular cross-section of the data conversion inlet includes a plurality of identical first fan-shaped cross-sections sized to fit into the docking front-end component, the circular cross-section of the data conversion outlet includes a plurality of identical second fan-shaped cross-sections sized to fit into the docking back end component, the intermediate section disposed between the data conversion inlet and the data conversion outlet, used for receiving the first sector section data, carrying out rotary replication to form circular section data, and cutting the circular section data according to the second sector section to form second sector section data, wherein the front end part and the back end part are two adjacent parts on the flow field structure of the aircraft engine.
The application provides a conversion model, realizes that fan-shaped to circular data or fan-shaped to fan-shaped conversion, and special-shaped cross section data also can adopt similar conversion model to convert data simultaneously. The method can also realize the conversion of the data with the special-shaped cross section, realize the conversion of different parts and different types of data forms and realize the joint simulation calculation.
In some alternative embodiments, the front end component is an aircraft engine thrust augmentation component computational model, and the first sector cross-section is a circular sector of one-sixth or one-eighth.
Fig. 2 shows a schematic diagram of flow field data of a boost model, a tail end outlet of a calculation model of a boost component of an aircraft engine is similar to a sector, and a corresponding first sector section is a circular sector with one sixth or one eighth of the cross section, as shown in fig. 3, after the first sector section is in butt joint with the tail end outlet of the calculation model of the boost component of the aircraft engine, the first sector section is used for receiving the flow field data output by the calculation model of the boost component of the aircraft engine.
In alternative embodiments, the inlet sector partitions of the flow field data conversion structure may be freely arranged according to the structural features of the front end component, such as eight, four, sixteen, or may be arranged as a circular outlet, and the outlet sector partitions may also be freely arranged according to the structural features of the rear end component, such as 8 sectors with 45 ° inlet surfaces and 15 sectors with 24 ° outlet surfaces. It will be appreciated that, since the front end part and the back end part are irregularly shaped, in principle, said first fan-shaped cross-section is dimensioned to be at least covered by the outlet of the back end of said front end part, thereby facilitating the reception of data of the front end part, and correspondingly said second fan-shaped cross-section is dimensioned to cover at least the inlet of said back end part, thereby outputting data. In some alternative embodiments, the first fan-shaped cross-section may also be larger in size than the trailing-end outlet of the leading-end part, and for some edge locations of the first fan-shaped cross-section not being completely covered by the trailing-end outlet of the leading-end part, data padding may be performed, for example, for vacant locations according to a trend of change of data in the plane of the first fan-shaped cross-section.
In some alternative embodiments, the first and second sector cross-sectional data comprise temperature or pressure.
In the application, the middle section of the flow field data conversion structure is a data conversion part, as shown in fig. 4, the middle section is used for rotationally copying the extracted data, a 360-degree circular data is spliced, and the purpose of setting the middle section is to perform data conversion.
In some alternative embodiments, the aft end component is a nozzle computational model and the second fan-shaped cross-section is one-half of a circular sector or 360 ° of a circle.
As shown in fig. 5 and 6, numerical calculation is performed, numerical distribution consistent with the inlet surface is obtained on the outlet surface, outlet surface data, which can be 360-degree circular data or sector data, is extracted, and the converted data is used as an inlet of numerical calculation of the rear-end component for calculation, so that data conversion between complex component models is completed.
In some alternative embodiments, the first and second sector cross-sectional data comprise temperature or pressure.
The thrust augmentation data conversion and jet flow temperature simulation analysis can be popularized and applied to the fine analysis of the spray pipe temperature field, and a foundation is laid for the subsequent spray pipe cooling design, cold air distribution and the design of special-shaped spray pipes such as binary spray pipes.
The data conversion model can be popularized to the design of each engine component, comprehensive data of each component interface is used as an inlet parameter, the calculation precision of the components is improved, and the design method of each component of the engine is improved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A flow field data conversion structure between different components is characterized by comprising a data conversion inlet with a circular section, a data conversion outlet and a middle section, the circular cross-section of the data conversion inlet includes a plurality of identical first fan-shaped cross-sections sized to fit into the docking front-end component, the circular cross-section of the data conversion outlet includes a plurality of identical second fan-shaped cross-sections sized to fit into the docking back end component, the intermediate section disposed between the data conversion inlet and the data conversion outlet, used for receiving the first sector section data, carrying out rotary replication to form circular section data, and cutting the circular section data according to the second sector section to form second sector section data, wherein the front end part and the back end part are two adjacent parts on the flow field structure of the aircraft engine.
2. A flow field data transfer arrangement between different components as claimed in claim 1 wherein said first fan-shaped cross-section is dimensioned to be covered by at least a trailing outlet of said front component.
3. A flow field data transfer arrangement between different components as claimed in claim 1 wherein said second scalloped cross-section is sized to at least cover an inlet of said back end component.
4. A flow field data transfer arrangement between different components as claimed in claim 1 wherein said first and second sector cross-sectional data includes temperature.
5. A flow field data transfer arrangement between different components as claimed in claim 1 wherein said first sector cross-sectional data and said second sector cross-sectional data comprise pressure.
6. A flow field data transfer arrangement between different components as claimed in claim 1 wherein said front end component is an aircraft engine force component computational model and said first sector cross-section is a one-sixth or one-eighth circular sector.
7. A structure for data transfer between flow fields according to claim 6, wherein said back end part is a nozzle computational model of an engine and said second sector cross-section is a one-half circular sector or a 360 ° circle.
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2021
- 2021-06-24 CN CN202110716100.4A patent/CN113408073B/en active Active
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