CN112177677B - Turbine disk structure with inner ring cavity and expanded domain and design method thereof - Google Patents
Turbine disk structure with inner ring cavity and expanded domain and design method thereof Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
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- 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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- 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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Abstract
The structure of the expanded turbine disk with the inner ring cavity and the design method thereof comprise the following steps: 1) Carrying out region expansion on the original model of the turbine disc and carrying out sector model segmentation and extraction; 2) Selecting a reasonable model block size according to stress field distribution; 3) Setting material properties, carrying out blocking processing and grid division processing on the model, and setting corresponding load conditions and stress analog simulation calculation on the model; 4) Setting corresponding topological optimization constraint conditions and optimization targets to carry out topological optimization; 5) Based on a topological optimization result, model reconstruction is carried out, and the key size of a structure removal part is selected as a design variable; 6) Carrying out size optimization on the reconstructed model, and carrying out statics analysis; 7) And comparing the analysis result with the yield limit value of the material of the turbine disc, verifying whether the model stress is smaller than the yield limit of the material after size optimization, and repeating the step 6) until the requirement is met if the model stress is not smaller than the yield limit of the material, namely designing the turbine disc structure with the inner ring cavity and the expanded domain.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a domain-expanded turbine disk structure with an inner ring cavity and a design method thereof.
Background
The aircraft engine is used as a power device of the aircraft, is the heart of the aircraft, and is the key for ensuring the normal operation of the aircraft. With the continuous development of the aviation industry, in the design and research and development processes of an aircraft engine, in order to improve the working performance of the engine, such as high thrust-weight ratio, high reliability, high safety and the like, and reduce flight accidents caused by engine faults, the performance of core parts of the aircraft engine, such as a turbine disc, a turbine blade and a turbine shaft, should be improved first, so that the core parts can stably work under a more severe environment. Therefore, the performance of the core parts of the aircraft engine becomes an important factor for restricting the overall performance of the aircraft engine.
The turbine disc is a core part of an aircraft engine, and the quality and the stress level of the turbine disc have important influence on the improvement of the thrust-weight ratio, the reliability, the safety and the like of the engine. Under the condition of ensuring that the wheel disc stress meets the allowable material stress, the mass of the turbine disc is reduced, the weight of the aero-engine can be reduced, the cost is reduced, and the thrust-weight ratio of the engine is improved. The structure optimization design of the turbine disk is an effective way for reducing the mass of the turbine disk.
Disclosure of Invention
The invention aims to solve the problems in the prior art, provides a domain expansion turbine disk structure with an inner ring cavity and a design method thereof, and simultaneously obtains the domain expansion turbine disk structure with a single inner ring cavity and the domain expansion turbine disk structure with three inner ring cavities based on the method.
In order to achieve the purpose, the invention adopts the following technical scheme:
the design method of the turbine disk structure with the inner ring cavity of the domain expansion comprises the following steps:
1) Carrying out region expansion on the original model of the turbine disc;
2) Carrying out sector model segmentation on the expanded turbine disk model in the step 1) and extracting a sector model;
3) Selecting a reasonable model block size according to the stress field distribution of the original model of the turbine disc;
4) Setting material properties, carrying out blocking processing and grid division processing on the model, further setting corresponding load conditions on the model, and carrying out equivalent stress, radial stress and circumferential stress analog simulation calculation after the corresponding load conditions are set;
5) Setting corresponding topological optimization constraint conditions and an optimization target for topological optimization, wherein the optimization target has minimum flexibility;
6) Based on a topological optimization result, model reconstruction is carried out, and the key size of a structure removal part is selected as a design variable;
7) Selecting a reasonable variation range of the design variables according to the step 6), carrying out size optimization on the reconstructed model, and carrying out statics analysis;
8) Comparing the analysis result obtained in the step 7) with the yield limit value of the material of the turbine disc, verifying whether the equivalent stress, the radial stress and the circumferential stress of the model after size optimization are smaller than the yield limit value of the material, and if the equivalent stress, the radial stress and the circumferential stress are not smaller than the yield limit value of the material, repeating the step 7) until the requirements are met, namely designing the turbine disc structure with the inner ring cavity and the expanded domain.
In the step 1), the region is expanded in a manner of connecting the lower end point of the thickness of the rim with the upper end point of the thickness of the hub.
In the step 3), the size of the model block is selected to be divided into four blocks by the center of the turbine disk towards the direction of the edge surface of the disk, and the four blocks are divided into three different radius values of small, medium and large.
In step 4), the corresponding load conditions include: temperature field load, rotational speed, blade centrifugal load, axial displacement constraint and circumferential displacement constraint.
And 4), applying axial displacement constraint and circumferential displacement constraint to the wheel center surface, or applying axial displacement constraint to the axial end of the wheel center surface and applying circumferential displacement constraint to the circumferential end of the wheel center surface.
In step 5), the corresponding topology optimization constraints include: mass retention constraints, blocked local stress constraints, and non-optimized regions.
In step 6), the removing part comprises an inner ring cavity removing part of the turbine disc and an outer contour removing part of the turbine disc.
The turbine disc structure with the inner ring cavity comprises a wheel disc, wherein a single inner ring cavity or a three inner ring cavity which is hermetically communicated with the wheel disc along the circumferential direction is arranged in the wheel disc; the single inner ring cavity is arranged in an isosceles triangle-like shape, and the caliber of the single inner ring cavity is gradually increased from the inner side of the wheel disc to the outer wheel rim; the three inner ring cavities are composed of two isosceles triangle-like cavities and an isosceles trapezoid-like cavity, wherein the caliber of the isosceles triangle-like inner ring cavity close to the edge surface of the wheel disc is gradually increased from the inner side of the wheel disc to the outer rim, the caliber of the isosceles triangle-like inner ring cavity close to the wheel center is gradually decreased from the inner side of the wheel disc to the outer rim, and the caliber of the isosceles trapezoid-like inner ring cavity is gradually decreased from the inner side of the wheel disc to the outer rim.
In the three inner ring cavities, two bottom angles of the isosceles triangle-like inner ring cavity close to the disc edge surface are formed by 3mm circular arc chamfers, and a top angle is formed by 3mm circular arc chamfers; two bottom angles of the isosceles triangle-like inner ring cavity close to the wheel center are formed by 3mm arc chamfers, and the top angle is formed by 3mm arc chamfers; two base angles of the isosceles trapezoid-like inner ring cavity are formed by 6mm circular arc chamfers, and the top angle is formed by 6mm circular arc chamfers.
Two bottom angles of the single inner ring cavity are formed by 3mm arc chamfers, and the top angle is formed by 2.5mm arc chamfers.
The outer contour of the wheel disc is provided with a plurality of annular grooves and an annular boss, the annular grooves are formed by inward-concave arc curves, and the annular boss is formed by outward-convex arc curves.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
1. in the design method of the invention, the original turbine disk model has the volume of 4.578 multiplied by 10 6 mm 3 The mass is 35.847kg, and the volume of the turbine disc structure with the single inner ring cavity obtained through multiple optimization design is 3.215 multiplied by 10 6 mm 3 The mass of the turbine disc is 25.179kg, the mass of the turbine disc is reduced by 29.76 percent compared with that of the original turbine disc under the condition that the stress meets the requirement, and the volume of the turbine disc structure with the three inner ring cavities obtained through multiple optimization design is 3.557 multiplied by 10 6 mm 3 The mass is 27.850kg, the mass is reduced by 22.31 percent compared with the mass of the original turbine disc under the condition that the stress meets the requirement, the two structures reduce the weight of the aircraft engine, reduce the cost and improve the thrust-weight ratio of the engine.
2. According to the method, reasonable model block sizes are selected according to stress field distribution of the original model of the turbine disc, and block processing is carried out on the original model of the turbine disc before topology optimization is carried out, so that stress operation is more reasonably carried out during topology optimization calculation, and a more reasonable model can be obtained. Meanwhile, the novel turbine disk structure provided by the invention not only has a structure with an inner ring cavity in the inner part, but also has a reasonable change in the outer structure, so that the quality of the turbine disk is reduced to the maximum extent, and a more valuable configuration is obtained.
Drawings
FIG. 1 is a flow chart of the design method of the present invention.
FIG. 2 is a schematic diagram of the expansion of the original model region of the turbine disk.
Fig. 3 is a schematic diagram of a 15 ° sector model extraction of a turbine disk.
FIG. 4 is a block size schematic of a turbine disk sector model.
FIG. 5 is a schematic diagram of a meshing division of a sector model of a turbine disk.
FIG. 6 is a schematic view of the turbine disk structure with a single inner ring cavity under corresponding load conditions.
FIG. 7 is a schematic view of the turbine disk structure with three inner ring cavities under corresponding load conditions.
Fig. 8 is a schematic diagram of a topological optimization result of a turbine disk structure with a single inner ring cavity, which is obtained by calculating a turbine disk sector model based on ansys workbench software.
Fig. 9 is a schematic diagram of a topological optimization result of a turbine disk structure with three inner ring cavities, which is obtained by a turbine disk sector model calculated based on ansys workbench software.
Fig. 10 is a schematic diagram of a reconstruction model of a turbine disk structure with a single inner ring cavity in UG software after topology optimization of a turbine disk sector model.
Fig. 11 is a schematic model diagram of a reconstructed turbine disk structure with three inner ring cavities in UG software after topology optimization of a turbine disk sector model.
FIG. 12 is a schematic view of a turbine disk configuration with a single inner ring cavity.
FIG. 13 is a schematic view of a turbine disk configuration with three inner ring cavities.
FIG. 14 is the equivalent stress calculation for a turbine disk configuration with a single inner ring cavity.
FIG. 15 is a radial stress calculation for a turbine disk structure with a single inner ring cavity.
FIG. 16 is a circumferential stress calculation for a turbine disk structure with a single inner ring cavity.
FIG. 17 is the equivalent stress calculation for a turbine disk configuration with three inner ring cavities.
FIG. 18 is a radial stress calculation for a turbine disk configuration with three inner ring cavities.
FIG. 19 is a circumferential stress calculation for a turbine disk structure with three inner ring cavities.
FIG. 20 is a schematic view of the overall structure of a turbine disk with a single inner ring cavity.
FIG. 21 is a schematic cross-sectional view of the overall structure of a turbine disk with a single inner ring cavity.
FIG. 22 is a schematic view of the overall structure of a turbine disk with a three inner ring cavity.
FIG. 23 is a schematic cross-sectional view of the overall structure of a turbine disk with three inner ring cavities.
Detailed Description
In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer and clearer, the present invention is further described in detail below with reference to the accompanying drawings and embodiments.
The design process of the domain-expanded turbine disk structure with the inner ring cavity is shown in fig. 1, and specifically includes the following steps:
the first step is as follows: and carrying out region expansion on the original turbine disk model in UG software, wherein the region expansion mode is as shown in figure 2, and the lower end point of the disk edge thickness is connected with the upper end point of the disk hub thickness for expansion, so that the original turbine disk model is expanded, and a more novel topology optimization result is obtained.
The second step is that: the model obtained in the first step is subjected to sector model segmentation in UG software and a sector model is extracted, and the domain-expanded turbine disk structure with an inner ring cavity is based on the extracted 15 ° sector model, as shown in fig. 3. Because the wheel disc model is of a circular symmetrical structure, the sector model can be analyzed and optimized independently. The operation of the step aims to reduce the software optimization time in the later period and improve the software optimization efficiency.
The third step: the 15 ° sector model extracted by the second step is exported in UG software as parasolid file, file type is in the format of x _ t.
The fourth step: and selecting a reasonable model block size according to the stress field distribution of the original model of the turbine disk. As shown in fig. 4, in this embodiment, three different radius values are reasonably selected to partition the center of the turbine disk toward the disk rim surface, which are R3, R4 and R5, where R3 is the minimum partition size radius value, R4 is the middle partition size radius value, and R5 is the maximum partition size radius value. And taking the three radius values as the basis for completing the blocking treatment on the model in the fifth step. This step aims at providing conditions for topology optimization to set the corresponding local stress constraints.
The fifth step: running ansys workbench software, establishing a static structural module, setting material attributes in engineering data, and importing a parasolid file derived from UG software in the third step into a geometry, wherein the material attributes of the turbine disk structure with the inner ring cavity are set according to a material GH4169. Entering geometry to perform blocking processing on the imported model, as shown in fig. 4, and then entering a model module to perform grid division processing on the model, wherein the grid unit size is 3mm, and the number is 11200, as shown in fig. 5. And further setting corresponding load conditions for the model, wherein the corresponding load conditions comprise: temperature field load, rotational speed n, blade centrifugal load P, axial displacement constraint, and circumferential displacement constraint (axial displacement constraint is applied to the axial end of the hub face, circumferential displacement constraint is applied to the circumferential end of the hub face), as shown in fig. 4. The specific formula of the temperature field load is as follows:
wherein R is a radius, R 1 Radius of the rim surface, R 2 Radius of the wheel center plane, T (R) i ) Is at R i The temperature value at the radius.
Wherein, when the axial displacement and the circumferential displacement constraint are both applied to the wheel center surface, as shown in fig. 6, the turbine disk structure with a single inner ring cavity provided by the invention can be obtained; when the axial displacement constraint is applied to the axial end of the hub surface and the circumferential displacement constraint is applied to the circumferential end of the hub surface, as shown in fig. 7, a turbine disk structure with three inner ring cavities can be obtained.
After the corresponding load conditions are set, equivalent stress, radial stress and circumferential stress are subjected to analog simulation calculation.
And a sixth step: returning to ansys workbench software, and establishing a topology optimization module based on the solution item in the static structure module. Entering a topology optimization module setup item to set corresponding topology optimization constraint conditions and optimization targets. The respective topology optimization constraints include: mass retention 30% constrained, blocked local stress 800MPa constrained, and non-optimized regions are the rim and hub faces, which are shown in fig. 3; the optimization goal is to minimize compliance. The specific formula is as follows:
wherein λ is compliance ρ e For optimizing the pseudo-density of the grid cells of the region, M is the model quality after topology optimization, M 0 For original turbine disk model quality, σ i (i =1,2,3,4) is the local stress.
After the corresponding constraint conditions and the optimization targets are set, topology optimization is performed, and a topology optimization result is obtained after software calculation, wherein a turbine disc structure with a single inner ring cavity is shown in fig. 8, and a turbine disc structure with three inner ring cavities is shown in fig. 9. Considering that the topological optimization result is extremely sensitive to the temperature field, and whether the material directly determines the thermal stress or not, the invention respectively carries out the topological optimization research considering the temperature field load and neglecting the temperature field load, compares the results and finally selects a better scheme of the result.
The seventh step: and based on the topology optimization result in the sixth step, model reconstruction is carried out in UG software, the reconstructed turbine disk structure with the single inner ring cavity is shown in fig. 10, and the reconstructed turbine disk structure with the three inner ring cavities is shown in fig. 11. And selecting the key size of the structure removal part as a design variable, and exporting the exp format file. The removing part comprises an inner ring cavity removing part of the turbine disc and an outer contour removing part of the turbine disc. This step aims at achieving parametric modeling of the reconstructed model.
Eighth step: and selecting a reasonable variation range of the design variables according to the seventh step, carrying out size optimization on the reconstructed model in UG software, and importing the established model into ansys workbench software for static analysis, wherein the specific method is as described in the fifth step.
The ninth step: and comparing the analysis result obtained in the eighth step with the yield limit value of the material of the turbine disc, verifying whether the equivalent stress, the radial stress and the circumferential stress of the model after size optimization are smaller than the yield limit value of the material, if not, repeating the eighth step until the requirements are met, and finally obtaining the structure of the turbine disc with the single inner ring cavity of the reasonable optimization model as shown in figure 12, and the structure of the turbine disc with the three inner ring cavities as shown in figure 13. The embodiment provides a novel domain expansion turbine disk structure material with an inner ring cavity, which adopts GH4169.
Based on the optimized operation steps, the turbine disk structure with the single inner ring cavity and the turbine disk structure with the three inner ring cavities can be obtained.
The original turbine disk model has a volume of 4.578 x 10 6 mm 3 The mass is 35.847kg; the volume of the turbine disk structure with the single inner ring cavity provided by the invention is 3.215 multiplied by 10 6 mm 3 The mass is 25.179kg, and is reduced by 29.76% compared with the mass of the original turbine disk under the condition that the stress meets the requirement, the equivalent stress calculation result is shown in fig. 14, the radial stress calculation result is shown in fig. 15, and the circumferential stress calculation result is shown in fig. 16;
the volume of the turbine disk structure with the three inner ring cavities provided by the invention is 3.557 multiplied by 10 6 mm 3 The mass is 27.850kg, the mass is reduced by 22.31 percent compared with the mass of the original turbine disc under the condition that the stress meets the requirement, the equivalent stress calculation result is shown in FIG. 17, and the radial stress calculation result isThe results are shown in fig. 18, and the results of the circumferential stress calculation are shown in fig. 19.
Based on the optimization method, the turbine disc structure with the single inner ring cavity is obtained, as shown in fig. 20-21, the turbine disc structure comprises a wheel disc 1, an axial hole 3 is formed in the center of the wheel disc 1, a closed single inner ring cavity 2 is formed in the wheel disc 1, and the single inner ring cavity 2 penetrates through the wheel disc 1 in the circumferential direction;
specifically, the single inner ring cavity 2 is arranged in a similar isosceles triangle shape, and the caliber of the single inner ring cavity is gradually increased from the inner side of the wheel disc to the disc edge surface 4, so that the mass of the wheel disc 1 is reduced to the maximum extent, and the structural efficiency of the wheel disc 1 is optimized; two base angles 6 of the single inner ring cavity are formed by 3mm arc chamfers, and the top angle 5 is formed by 2.5mm arc chamfers, so that the problem of stress concentration can be effectively avoided by adopting an arc chamfer form.
The outer contour of the turbine disc structure with the inner ring cavity is completely different from that of the original turbine disc. The outer contour of the wheel disc is provided with a plurality of annular grooves and an annular boss, each annular groove is composed of inward-concave arc curves, each annular boss is composed of outward-convex arc curves, part of the arc curves are in tangent connection, and part of the arc curves are in tangent connection with straight-line segments of the outer contour;
specifically, the outer contour of the turbine disk is formed by connecting a straight line segment 7 with circular arc curves 8, 9, 10, 11 and 12. Wherein, the radius of the circular arc curve 8 is 3mm, the radii of the circular arc curves 9 and 10 are 30mm, and the radii of the circular arc curves 11 and 12 are 5mm.
More specifically, two ends of the circular arc curve 8 are tangentially connected with the straight line segment; two ends of the circular arc curve 9 are tangentially connected with the straight line segment; two ends of the arc curve 10 are tangentially connected with the straight line segment; one end of the circular arc curve 11 is in tangent connection with the straight line segment, and the other end of the circular arc curve is in tangent connection with the circular arc curve 12; one end of the circular arc curve 12 is connected with the circular arc curve 11 in a tangent mode, and the other end of the circular arc curve is connected with the straight line section in a tangent mode.
Based on the optimization method, the turbine disc structure with three inner ring cavities is obtained, and as shown in fig. 22-23, the turbine disc structure comprises a wheel disc 13, wherein an axial hole 15 is formed in the center of the wheel disc 13, a closed three inner ring cavity 14 is formed in the wheel disc 13, and the three inner ring cavity 14 penetrates through the wheel disc 13 along the circumferential direction;
specifically, the three inner ring cavities 14 are composed of two isosceles triangle-like cavities and one isosceles trapezoid-like cavity, wherein the aperture of the isosceles triangle-like inner ring cavity close to the rim surface 16 gradually increases from the inner side of the wheel disc to the outer rim, the aperture of the isosceles triangle-like inner ring cavity close to the wheel center gradually decreases from the inner side of the wheel disc to the outer rim, and the aperture of the isosceles trapezoid-like inner ring cavity gradually decreases from the inner side of the wheel disc to the outer rim.
More specifically, in the three inner ring cavities, two bottom angles 17 of the isosceles triangle-like inner ring cavity close to the disc edge surface are formed by 3mm circular arc chamfers, and a top angle 18 is formed by 3mm circular arc chamfers; two bottom angles 20 of the cavity of the inner ring of the isosceles triangle-like shape close to the wheel center are formed by 3mm arc chamfers, and the top angle 19 is formed by 3mm arc chamfers; two base angles 22 of class isosceles trapezoid inner ring cavity comprise 6mm circular arc chamfer, and apex angle 21 comprises 6mm circular arc chamfer, so adopt the circular arc chamfer form can effectively avoid stress concentration problem.
The outer contour of the turbine disc structure with the three-ring cavity is completely different from that of the original turbine disc; the outer contour of the wheel disc is provided with a plurality of annular grooves and an annular boss, the annular grooves are formed by inward-concave arc curves, and the annular boss is formed by outward-convex arc curves;
specifically, the outer contour of the turbine disk is formed by connecting straight line segments 23 with circular arc curves 24, 25, 26, 27 and 28. Wherein the radiuses of the circular arc curve 24 and the circular arc curve 28 are both 5mm, and the radiuses of the circular arc curves 25, 26 and 27 are all 30mm; both ends of each arc curve are tangentially connected with the straight line segment.
According to the invention, the hollow closed single inner ring cavity and the three inner ring cavities are designed in the wheel disc, so that the material consumption of the wheel disc is saved, the structural efficiency of the wheel disc is greatly improved, the mass of the turbine disc is greatly reduced under the condition that the stress meets the requirement, the overall weight of the wheel disc is maximally reduced, the stress concentration of the wheel disc is avoided, the weight of the wheel disc is reduced, the thrust-weight ratio of an engine is improved, and the cost is reduced.
According to the method, reasonable model block sizes are selected according to stress field distribution of the original model of the turbine disc, and block processing is carried out on the original model of the turbine disc before topology optimization is carried out, so that stress operation is more reasonably carried out during topology optimization calculation, and a more reasonable model can be obtained. Meanwhile, the novel turbine disk structure provided by the invention not only has a structure with an inner ring cavity in the inner part, but also has a reasonable optimization on the outer structure, so that the mass of the turbine disk is reduced to the maximum extent, and a more valuable configuration is obtained.
Claims (8)
1. The design method of the turbine disk structure with the inner ring cavity and the expanded domain is characterized by comprising the following steps of:
1) Carrying out region expansion on the original model of the turbine disc;
2) Carrying out sector model segmentation on the expanded turbine disk model in the step 1) and extracting a sector model;
3) Selecting a reasonable model block size according to the stress field distribution of the original model of the turbine disc;
4) Setting material properties, carrying out blocking processing and grid division processing on the model, further setting corresponding load conditions on the model, and carrying out equivalent stress, radial stress and circumferential stress analog simulation calculation after the corresponding load conditions are set;
5) Setting corresponding topological optimization constraint conditions and an optimization target to perform topological optimization, wherein the optimization target has minimum flexibility;
6) Based on a topological optimization result, model reconstruction is carried out, and the key size of a structure removal part is selected as a design variable;
7) Selecting a reasonable variation range of the design variables according to the step 6), carrying out size optimization on the reconstructed model, and carrying out statics analysis;
8) Comparing the analysis result obtained in the step 7) with the yield limit value of the material of the turbine disc, verifying whether the equivalent stress, the radial stress and the circumferential stress of the model after size optimization are smaller than the yield limit value of the material, and if the equivalent stress, the radial stress and the circumferential stress are not smaller than the yield limit value of the material, repeating the step 7) until the requirements are met, namely designing the turbine disc structure with the inner ring cavity and the expanded domain.
2. The method of designing a domain expansion turbine disk structure with an inner ring cavity as claimed in claim 1, wherein: in the step 1), the region is expanded in a manner of connecting the lower end point of the thickness of the rim with the upper end point of the thickness of the hub.
3. The method of claim 1 for designing a domain expansion turbine disk structure with an inner annular cavity, wherein: in the step 3), the size of the model block is selected to divide the model block into blocks in the direction from the center of the turbine disk to the edge surface of the disk, and the four blocks are divided into three different radius values of small, medium and large.
4. The method of designing a domain expansion turbine disk structure with an inner ring cavity as claimed in claim 1, wherein: in step 4), the corresponding load conditions include: temperature field load, rotational speed, blade centrifugal load, axial displacement constraint and circumferential displacement constraint.
5. The method of designing a domain expansion turbine disk structure with an inner ring cavity as claimed in claim 4, wherein: in the step 4), both axial displacement and circumferential displacement constraints are applied to the wheel center surface, or the axial displacement constraints are applied to the axial end of the wheel center surface, and the circumferential displacement constraints are applied to the circumferential end of the wheel center surface.
6. The method of designing a domain expansion turbine disk structure with an inner ring cavity as claimed in claim 1, wherein: in step 5), the corresponding topology optimization constraints include: and the mass retention constraint, the blocking local stress constraint and the non-optimization area are a disc edge surface and a wheel center surface.
7. The method of designing a domain expansion turbine disk structure with an inner ring cavity as claimed in claim 1, wherein: in step 6), the removing part comprises an inner ring cavity removing part of the turbine disc and an outer contour removing part of the turbine disc.
8. The extended-domain turbine disk structure with an inner ring cavity obtained by the design method according to any one of claims 1 to 7, wherein: the device comprises a wheel disc, wherein a single inner ring cavity or a three inner ring cavity which is sealed and penetrates through the wheel disc along the circumferential direction is arranged in the wheel disc; the single inner ring cavity is arranged in an isosceles triangle-like shape, and the caliber of the single inner ring cavity is gradually increased from the inner side of the wheel disc to the outer wheel rim; the three inner ring cavities consist of two isosceles triangle-like cavities and an isosceles trapezoid-like cavity, wherein the caliber of the isosceles triangle-like inner ring cavity close to the rim surface of the wheel disc is gradually increased from the inner side of the wheel disc to the outer rim, the caliber of the isosceles triangle-like inner ring cavity close to the wheel center is gradually decreased from the inner side of the wheel disc to the outer rim, and the caliber of the isosceles trapezoid-like inner ring cavity is gradually decreased from the inner side of the wheel disc to the outer rim;
in the three inner ring cavities, two bottom angles of the isosceles triangle-like inner ring cavity close to the edge surface of the disc are formed by 3mm circular arc chamfers, and a vertex angle is formed by 3mm circular arc chamfers; two bottom angles of the isosceles triangle-like inner ring cavity close to the wheel center are formed by 3mm arc chamfers, and the top angle is formed by 3mm arc chamfers; two bottom angles of the isosceles trapezoid-like inner ring cavity are formed by 6mm circular arc chamfers, and a vertex angle is formed by 6mm circular arc chamfers; two bottom angles of the single inner ring cavity are formed by 3mm arc chamfers, and a top angle is formed by 2.5mm arc chamfers;
the outer contour of the wheel disc is provided with a plurality of annular grooves and an annular boss, each annular groove is composed of inward-concave arc curves, and each annular boss is composed of outward-convex arc curves.
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| CN108920836A (en) * | 2018-07-04 | 2018-11-30 | 北京航空航天大学 | Geometric dimension probability statistics characteristic analysis method in a kind of turbine disk probability and reliability analysis |
| 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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| 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 |
| CN108920836A (en) * | 2018-07-04 | 2018-11-30 | 北京航空航天大学 | Geometric dimension probability statistics characteristic analysis method in a kind of turbine disk probability and reliability analysis |
| CN108563917A (en) * | 2018-07-19 | 2018-09-21 | 北京航空航天大学 | A kind of turbine disc mortise crack propagation modeling part design 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 |
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