CN106599359B - Design method of hollow blade filled by spherical net structure and engine - Google Patents
Design method of hollow blade filled by spherical net structure and engine Download PDFInfo
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Abstract
The invention provides a design method of a hollow blade filled by a spherical reticular structure, which comprises the following steps: 1) carrying out pneumatic design on the hollow blade to obtain the blade surface shape of the hollow blade; 2) replacing a solid structure with spherical units with different parameters at different positions in the solid blade model to obtain a spherical reticular hollow blade; 3) establishing a finite element model, and carrying out simulation calculation on the finite element model to obtain a simulation result; 4) optimizing the spherical reticular structure of the spherical reticular hollow blade based on the simulation result of the step 3); 5) repeating the simulation calculation of the step 3) on the optimized spherical reticular hollow blade obtained in the step 4), returning to the step 4) to readjust the spherical reticular structure if the performance requirement is not met, and performing the next step if the performance requirement is met; 6) and manufacturing the optimized spherical reticular hollow blade by an additive manufacturing method. The invention has the advantages of improving various performances of the blade and lightening the mass of the blade.
Description
Technical Field
The invention relates to a design method of a blade, in particular to a design method of a hollow blade filled by a spherical net structure and an engine.
Background
The blades in the aircraft engine comprise fan blades, compressor blades, turbine blades and the like, the development of the blades plays an important role in the development of the aircraft engine, and the blades are mainly applied to fans, compressors and turbines. In recent years, with the improvement of related technologies such as structural design, manufacturing process, material performance and the like, various advanced blade technologies such as hollow blades, composite blades and the like are developed and verified by world famous aeroengine design and manufacturing companies, and some of the advanced blade technologies are applied to fans and compressors of aeroengines in active service or in research and achieve good effects.
As additive manufacturing technologies are developed and mature, traditional structural designs, fabrication processes are being changed. The additive manufacturing technology is a technology for manufacturing solid parts by adopting a method of gradually accumulating materials, and is a manufacturing method from bottom to top compared with the traditional material removing-cutting processing technology. The technology can realize rapid, mold-free and near-net forming of the compact metal part with the high-performance complex structure, is particularly suitable for integral manufacturing of large-scale complex structure parts, and the limitation of the traditional machining process on mechanical design is overturned due to the appearance of additive manufacturing, so that the field of mechanical design is changed greatly. There are many advantages to manufacturing aircraft engines using additive manufacturing techniques, such as: the engine parts with high complexity can be integrally manufactured; the service temperature of the engine parts is improved; the performance of the additive manufacturing part is convenient to adjust; gradient materials can be developed, etc.
How to better improve various performances of the blade and reduce the mass of the blade can have a profound influence on the design and manufacture of an aeroengine.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a design method of a hollow blade filled with a spherical net structure and an engine.
The invention provides a design method of a hollow blade filled by a spherical reticular structure, which comprises the following steps:
1) carrying out pneumatic design on the hollow blade to obtain the blade surface shape of the hollow blade;
2) generating a solid blade model for the blade surface modeling of the hollow blade obtained in the step 1), performing a centrifugal force simulation experiment, and replacing a solid structure with spherical units with different parameters at different positions in the solid blade model according to the simulation result of the solid blade model to obtain a spherical reticular hollow blade;
3) establishing a finite element model for the spherical netted hollow blade obtained in the step 2), and carrying out simulation calculation on the finite element model to obtain a simulation result;
4) optimizing the spherical reticular structure of the spherical reticular hollow blade based on the simulation result of the step 3);
5) repeating the simulation calculation of the step 3) on the optimized spherical reticular hollow blade obtained in the step 4), returning to the step 4) to readjust the spherical reticular structure if the performance requirement is not met, and performing the next step if the performance requirement is met;
6) and manufacturing the optimized spherical reticular hollow blade by an additive manufacturing method.
As a further improvement of the invention, the method also comprises the following steps:
7) according to design requirements, carrying out heat treatment and surface processing on the spherical netted hollow blade obtained by the additive manufacturing in the step 6);
8) and (3) testing the spherical netted hollow blade subjected to heat treatment and surface processing by using an experimental method, returning to the step 1 if the requirement is not met, and completing design if the requirement is met.
As a further improvement of the present invention, in step 4), the number of the spherical units is added or deleted, the parameters of each spherical unit are adjusted, and the contact relationship among the plurality of spherical units is adjusted, so as to optimize the spherical net structure.
As a further improvement of the invention, the spherical unit in step 4) comprises any one of a sphere, a sphere shell, a sphere containing a hole, a sphere shell containing a hole, a sphere topology structure or any combination thereof.
As a further improvement of the present invention, the parameters of the spherical unit in step 4) include an inner diameter, an outer diameter, position coordinates, a material, a density, whether there are holes on the surface of the spherical shell, and a topological structure of the spherical shell.
As a further improvement of the invention, the contact relationship among the plurality of spherical units in the step 4) comprises intersection, tangency and separation, and if the plurality of spherical units are in an intersection relationship, the intersection part is totally deleted or totally reserved or partially reserved.
As a further improvement of the invention, in the step 3), a finite element model is established for the spherical netted hollow blade obtained in the step 2), and the performance simulation calculation of strength, vibration, heat transfer and fatigue life is carried out on the spherical netted hollow blade.
As a further improvement of the invention, the establishing of the finite element model of the spherical netted hollow blade in the step 3) comprises the steps of simplifying spherical units by using a super-unit technology, establishing a spherical unit database, forming standard basic super-units, simplifying a modeling process through the relation between the super-units, reducing the total number of degrees of freedom of the model and shortening the time required by calculation.
As a further improvement of the invention, the spherical reticular structure extends to the surface of the spherical reticular hollow blade, so that the spherical reticular hollow blade is formed by the spherical reticular structure alone.
The invention also provides an engine which comprises the spherical reticular hollow blade designed by adopting the design method of the hollow blade filled by the spherical reticular structure.
The invention has the beneficial effects that: through the scheme, the spherical grid structure designed aiming at the additive manufacturing technology is provided, the butt joint of the aero-engine blade from the structural design to the model establishment to the simulation analysis and to the manufacturing is realized, the spherical units have the characteristics of simple structure and excellent mechanical property, the reticular structure formed by arranging and stacking the spherical units can be greatly improved in the aspects of weight, strength, vibration property, heat transfer and the like by adjusting various parameters of the spherical units, various properties of the blade are improved, and the quality of the blade is reduced.
Drawings
FIG. 1 is a schematic diagram of a spherical netted hollow blade designed by the method for designing a hollow blade filled with a spherical netted structure according to the present invention.
Detailed Description
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
As shown in fig. 1, a method for designing a hollow blade filled with a spherical mesh structure is based on an additive manufacturing technology, and forms a three-dimensional hollow mesh structure instead of a solid structure or other conventional hollow structures by arranging hollow spherical units, and optimizes the weight, strength, vibration, heat transfer, aerodynamics, and other properties of the blade by designing parameters such as the position, outer diameter, inner diameter, material, and the like of each hollow spherical unit and the contact relationship among a plurality of spherical units. The spherical net structure designed by the method can be realized by using an additive manufacturing technology, and the performance of the blade can be obviously improved and the weight of the blade can be reduced. Under the current situation that no existing special simulation tool exists, the method can adopt the super-unit technology to process the ball unit structure and establish a finite element model, and time required by blade structural design, modeling simulation and structural optimization is greatly shortened. The invention also comprises the blade designed by using the method, and an aircraft engine and a gas turbine comprising the blade.
A design method of a hollow blade filled by a spherical reticular structure specifically comprises the following steps:
1) and carrying out pneumatic design on the hollow blades to obtain the blade surface shapes of the hollow blades, specifically, carrying out pneumatic design on the fan, the compressor blades or the turbine blades to obtain the blade surface shapes of the blades. The design can be less considering the limitation of factors such as processing technology, strength, vibration, heat transfer and the like of the blade;
2) generating a solid blade model for the blade surface modeling of the hollow blade obtained in the step 1), performing a centrifugal force simulation experiment, and replacing a solid structure with spherical units with different parameters at different positions in the solid blade model according to the simulation result of the solid blade model to obtain a spherical reticular hollow blade;
3) establishing a finite element model for the spherical netted hollow blade obtained in the step 2), and carrying out simulation calculation on the finite element model to obtain a simulation result;
4) optimizing the spherical reticular structure of the spherical reticular hollow blade based on the simulation result of the step 3);
5) repeating the simulation calculation of the step 3) on the optimized spherical reticular hollow blade obtained in the step 4), returning to the step 4) to readjust the spherical reticular structure if the performance requirement is not met, and performing the next step if the performance requirement is met, specifically, repeating the simulation calculation of the step 3) on the optimized blade model obtained in the step 4), and returning to the step 4 to readjust the parameters of the spherical reticular structure until the requirements of weight, strength, vibration and heat transfer are met if the performance requirement is not met;
6) and manufacturing the optimized spherical reticular hollow blade by an additive manufacturing method.
Further comprising the steps of:
7) according to design requirements, carrying out heat treatment and surface processing on the spherical netted hollow blade obtained by the additive manufacturing in the step 6);
8) and (3) testing the spherical netted hollow blade subjected to heat treatment and surface processing by using an experimental method, returning to the step 1 if the requirement is not met, and completing design if the requirement is met.
In step 4), the number of the spherical units is added or deleted, the parameters of each spherical unit are adjusted, and the contact relation among a plurality of spherical units is adjusted, so that the spherical net structure is optimized.
The spherical unit in the step 4) comprises any one or any combination of a sphere, a spherical shell, a sphere with a hole, a spherical shell with a hole and a topological structure of the sphere.
The parameters of the spherical unit in the step 4) comprise the inner diameter, the outer diameter, the position coordinates, the material quality and the density of the spherical unit, whether holes exist on the surface of the spherical shell or not and the topological structure of the spherical shell.
The contact relation among the spherical units in the step 4) comprises intersection, tangency and phase separation, and if the spherical units are in an intersection relation, the intersected part is completely deleted or completely reserved or partially reserved.
In the step 3), a finite element model is established for the spherical netted hollow blade obtained in the step 2), and the performance simulation calculation of strength, vibration, heat transfer and fatigue life is carried out on the spherical netted hollow blade.
The establishing of the finite element model of the spherical netted hollow blade in the step 3) comprises the steps of simplifying spherical units by using a super-unit technology, establishing a spherical unit database, forming standard basic super-units, simplifying a modeling process through the relation between the super-units, reducing the total number of degrees of freedom of the model and shortening the time required by calculation.
The spherical net-shaped structure extends to the surface of the spherical net-shaped hollow blade, so that the spherical net-shaped hollow blade is formed by the spherical net-shaped structure alone.
An engine comprising a spherical netted hollow blade designed by the method for designing a hollow blade filled with a spherical netted structure as set forth in any one of the above, preferably an aircraft engine or a gas turbine.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (6)
1. A design method of a hollow blade filled with a spherical reticular structure is characterized by comprising the following steps:
1) carrying out pneumatic design on the hollow blade to obtain the blade surface shape of the hollow blade;
2) generating a solid blade model for the blade surface modeling of the hollow blade obtained in the step 1), performing a centrifugal force simulation experiment, and replacing a solid structure with spherical units with different parameters at different positions in the solid blade model according to the simulation result of the solid blade model to obtain a spherical reticular hollow blade;
3) establishing a finite element model for the spherical netted hollow blade obtained in the step 2), and carrying out simulation calculation on the finite element model to obtain a simulation result;
4) optimizing the spherical reticular structure of the spherical reticular hollow blade based on the simulation result of the step 3);
5) repeating the simulation calculation of the step 3) on the optimized spherical reticular hollow blade obtained in the step 4), returning to the step 4) to readjust the spherical reticular structure if the performance requirement is not met, and performing the next step if the performance requirement is met;
6) manufacturing the optimized spherical netted hollow blade by an additive manufacturing method;
wherein the content of the first and second substances,
in the step 4), the number of the spherical units is added or deleted, the parameters of each spherical unit are adjusted, and the contact relation among a plurality of spherical units is adjusted, so that the spherical net structure is optimized;
the spherical unit in the step 4) comprises any one or any combination of a sphere, a spherical shell, a sphere with a hole, a spherical shell with a hole and a topological structure of the sphere;
the parameters of the spherical unit in the step 4) comprise the inner diameter, the outer diameter, the position coordinates, the material and the density of the spherical unit, whether a hole is formed on the surface of the spherical shell or not and the topological structure of the spherical shell;
the contact relation among the spherical units in the step 4) comprises intersection, tangency and phase separation, and if the spherical units are in an intersection relation, the intersected part is completely deleted or completely reserved or partially reserved.
2. The method of designing a hollow blade filled with a spherical mesh structure according to claim 1, wherein: further comprising the steps of:
7) according to design requirements, carrying out heat treatment and surface processing on the spherical netted hollow blade obtained by the additive manufacturing in the step 6);
8) and (3) testing the spherical netted hollow blade subjected to heat treatment and surface processing by using an experimental method, returning to the step 1 if the requirement is not met, and completing design if the requirement is met.
3. The method of designing a hollow blade filled with a spherical mesh structure according to claim 1, wherein: in the step 3), a finite element model is established for the spherical netted hollow blade obtained in the step 2), and the performance simulation calculation of strength, vibration, heat transfer and fatigue life is carried out on the spherical netted hollow blade.
4. The method of designing a hollow blade filled with a spherical mesh structure according to claim 1, wherein: the establishing of the finite element model of the spherical netted hollow blade in the step 3) comprises the steps of simplifying spherical units by using a super-unit technology, establishing a spherical unit database, forming standard basic super-units, simplifying a modeling process through the relation between the super-units, reducing the total number of degrees of freedom of the model and shortening the time required by calculation.
5. The method of designing a hollow blade filled with a spherical mesh structure according to claim 1, wherein: the spherical net-shaped structure extends to the surface of the spherical net-shaped hollow blade, so that the spherical net-shaped hollow blade is formed by the spherical net-shaped structure alone.
6. An engine, characterized in that: the spherical netted hollow blade designed by the method for designing a hollow blade filled with a spherical netted structure according to any one of claims 1 to 5.
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112628195B (en) * | 2019-10-09 | 2023-04-25 | 中国航发商用航空发动机有限责任公司 | Fan blade and aeroengine |
| CN112329138A (en) * | 2020-10-29 | 2021-02-05 | 深圳意动航空科技有限公司 | Spherical shell structure generation method and device, storage medium and electronic equipment |
| CN114082988A (en) * | 2021-10-28 | 2022-02-25 | 浙江意动科技股份有限公司 | Method for repairing aero-engine cold and hot end blade |
| CN115688314B (en) * | 2022-11-03 | 2024-01-23 | 北京全四维动力科技有限公司 | Method and device for pre-twisting simulation design of turbine blade based on finite element analysis |
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| CN103778271A (en) * | 2013-09-06 | 2014-05-07 | 上海大学 | Multi-hole structure modeling method based on grid assembly |
| CN105808838A (en) * | 2016-03-04 | 2016-07-27 | 西北工业大学 | Multi-inner-cavity structure design method for hollow fan blade |
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| GB2418460A (en) * | 2004-09-22 | 2006-03-29 | Rolls Royce Plc | Aerofoil with low density |
| CN101078354A (en) * | 2007-06-06 | 2007-11-28 | 北京航空航天大学 | Porous metal vane coupling design method |
| CN103470312A (en) * | 2013-09-06 | 2013-12-25 | 北京航空航天大学 | Gas turbine engine blade with inner meshed structure |
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