CN213063683U

CN213063683U - Turbine disc structure with single inner ring cavity

Info

Publication number: CN213063683U
Application number: CN202022142947.XU
Authority: CN
Inventors: 闫成; 赵超帆; 米栋; 尤延铖; 邱若凡; 范俊; 彭泽
Original assignee: Xiamen University
Current assignee: Xiamen University
Priority date: 2020-09-25
Filing date: 2020-09-25
Publication date: 2021-04-27
Anticipated expiration: 2030-09-25

Abstract

A turbine disc structure with a single inner ring cavity relates to the technical field of aero-engines and comprises a wheel disc, wherein the wheel disc is internally provided with a closed single inner ring cavity which is communicated with the wheel disc along the circumferential direction; 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; 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 structure greatly reduces the mass of the turbine of the engine, and further improves the thrust-weight ratio of the aero-engine.

Description

Turbine disc structure with single inner ring cavity

Technical Field

The utility model relates to an aeroengine technical field especially relates to a turbine disc structure of single inner ring cavity in area.

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 the aviation 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 the flight accidents caused by engine faults, the performance of core parts of the aviation engine, such as a turbine disc, a turbine blade and a turbine shaft, should be improved firstly, so that the core parts can stably work in 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

An object of the utility model is to solve the above-mentioned problem among the prior art, provide a take turbine disc structure of single inner ring cavity, this structure makes engine turbine quality reduce by a wide margin, further promotes aeroengine thrust-weight ratio.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a turbine disc structure with a single inner ring cavity comprises a wheel disc, wherein the wheel disc is internally provided with a closed single inner ring cavity which is communicated with the wheel disc along the circumferential direction; the single inner ring cavity is arranged like an isosceles triangle, and the caliber of the single inner ring cavity is gradually increased from the inner side of the wheel disc to the outer rim.

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, each annular groove is composed of inward-concave arc curves, each annular boss is composed of outward-convex arc curves, the partial arc curves are in tangent connection, and the partial arc curves are in tangent connection with straight-line segments of the outer contour.

The volume of the turbine disk structure with the single inner ring cavity is 3.215 multiplied by 10⁶mm³The mass was 25.179 kg.

Compared with the prior art, the utility model discloses technical scheme obtains beneficial effect is:

1. the volume of the utility model is 3.215 multiplied by 10⁶mm³The mass is 25.179kg, and the original turbine disk model volume is 4.578 multiplied by 10⁶mm³The mass is 35.847kg, and the mass is reduced by 29.76% compared with the mass of the original turbine disc under the condition that the stress meets the requirement, so that the weight of the aircraft engine is reduced, the cost is reduced, and the thrust-weight ratio of the engine is improved.

2. The utility model discloses not only there is the structure of inner ring cavity in inside, and the outer structure also has reasonable change moreover, and the quality of the reduction turbine dish of maximize obtains more valuable configuration.

Drawings

FIG. 1 is a schematic view of the overall structure of a turbine disk with a single inner ring cavity.

FIG. 2 is a partial schematic view of a turbine disk configuration with a single inner ring cavity.

FIG. 3 is a schematic cross-sectional view of the overall structure of a turbine disk with a single inner ring cavity.

FIG. 4 is a schematic diagram illustrating the expansion of the original model region of the turbine disk.

Fig. 5 is a schematic diagram of a 15 ° sector model extraction of a turbine disk.

FIG. 6 is a block size diagram of a sector model of a turbine disk.

FIG. 7 is a schematic diagram of the corresponding load conditions of a turbine disk sector model.

Detailed Description

In order to make the technical problem, technical solution and beneficial effects to be solved by the present invention clearer and more obvious, the following description is made in detail with reference to the accompanying drawings and embodiments.

As shown in fig. 1 to 3, the present embodiment includes a wheel disc 1, an axial hole 3 is provided at a center of the wheel disc 1, a closed single inner ring cavity 2 is provided inside the wheel disc 1, and the single inner ring cavity 2 penetrates through the wheel disc 1 in a 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 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 annular groove consists of inward-concave circular arc curves, the annular boss consists of outward-convex circular arc curves, and the circular arc curves are in tangent connection or the circular arc curves are in tangent connection with straight-line segments of the external 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 radius of the

circular arc curves

9 and 10 is 30mm, and the radius of the

circular arc curves

11 and 12 is 5 mm.

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 arc curve 11 is tangent to the straight line segment, and the other end is tangent to the 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.

The design method of the embodiment is specifically as follows:

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 4, 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 turbine disk structure with the single inner ring cavity is based on the extraction of a 15-degree sector model, as shown in fig. 5. 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. 6, in this embodiment, three different radius values are reasonably selected to partition the center of the turbine disk toward the disk edge 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 processing of the model in the fifth step. This step aims to provide conditions for setting the corresponding local stress constraints for topology optimization.

The fifth step: running asys workbench software, establishing a static structural module, setting material attributes in engineering data, and importing a parasolid file exported by UG software in geometry, wherein the material attributes of the structure of the turbine disk with the inner ring cavity are set according to a material GH4169 in the embodiment. Entering geometry to perform blocking processing on the imported model, as shown in fig. 6, 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. 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, R₁Radius of the rim surface, R₂Radius of the wheel center plane, T (R)_i) Is at R_iThe temperature value at the radius.

Wherein, when the axial displacement and the circumferential displacement are both restricted to be applied to the wheel center surface, as shown in fig. 7, the turbine disk structure with a single inner ring cavity can be obtained.

And after the corresponding load conditions are set, performing equivalent stress, radial stress and circumferential stress simulation calculation.

And a sixth step: returning to the 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. 5; the optimization goal is minimum compliance. The specific formula is as follows:

min： λ

w.r.t.： ρ_e

wherein λ is compliance, ρ_eFor optimizing the pseudo-density of the grid cells in the region, M is the model quality after topology optimization, M₀For the original turbine disk model quality, σ_i(i ═ 1, 2, 3, 4) is the local stress.

And after the corresponding constraint conditions and the optimization targets are set, carrying out topology optimization, and obtaining a topology optimization result after software calculation. The topological optimization result is considered to be extremely sensitive to the temperature field, and whether the material directly determines the existence of the thermal stress, so that the topological optimization research considering the temperature field load and neglecting the temperature field load is respectively carried out, the results are compared, and the optimal scheme of the result is finally selected.

The seventh step: and based on the topological optimization result in the sixth step, model reconstruction is carried out in UG software, and the reconstructed turbine disk structure with the single inner ring cavity is obtained. 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 turbine disc material, 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, repeating the eighth step if the equivalent stress, the radial stress and the circumferential stress are not smaller than the yield limit value of the material, and finally obtaining the turbine disc structure with the single inner ring cavity of the reasonable optimization model until the requirements are met. The structural material of the turbine disk with the single inner ring cavity provided by the embodiment adopts GH 4169.

Based on above optimization operation step, can obtain the turbine disc structure of single inner ring cavity in area.

The original turbine disk model has the volume of 4.578 multiplied by 10⁶mm³35.847kg in mass; the utility model has a structure volume of 3.215 multiplied by 10⁶mm³The mass is 25.179kg, and the mass is reduced by 29.76 percent compared with the mass of the original turbine disc under the condition that the stress meets the requirement.

The utility model discloses a hollow inclosed single inner ring cavity of internal design at the rim plate saves the consumptive material of rim plate to make the structural efficiency of rim plate obtain greatly improving, the quality of greatly reduced turbine dish under the condition that all satisfies the requirement of stress, with the maximize alleviates the whole weight of rim plate, avoid the stress concentration of rim plate, thereby reach the weight that alleviates the rim plate and improve the engine and push away the weight ratio, and reduce cost.

According to the stress field distribution of the original model of the turbine disk, reasonable model block sizes are selected, block processing is carried out on the original model of the turbine disk before topology optimization is carried out, and therefore stress operation is more reasonably carried out during topology optimization calculation, and further a more reasonable model can be obtained. And simultaneously, the utility model discloses not only there is the structure of single inner ring cavity in inside, the outer structure also has reasonable optimization moreover, and the maximize reduces the quality of turbine dish, obtains more valuable configuration.

Claims

1. The utility model provides a take turbine disc structure of single inner ring cavity which characterized in that: the wheel disc comprises a wheel disc, wherein a closed single inner ring cavity which is communicated with the wheel disc along the circumferential direction is formed in the wheel disc; the single inner ring cavity is arranged like an isosceles triangle, and the caliber of the single inner ring cavity is gradually increased from the inner side of the wheel disc to the outer rim.

2. A turbine disk structure with a single inner ring cavity as claimed in claim 1, wherein: 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.

3. A turbine disk structure with a single inner ring cavity as claimed in claim 1, wherein: 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, the partial arc curves are in tangent connection, and the partial arc curves are in tangent connection with straight-line segments of the outer contour.

4. A turbine disk structure with a single inner ring cavity as claimed in claim 1, wherein: the volume of the turbine disk structure with the single inner ring cavity is 3.215 multiplied by 10⁶mm³The mass was 25.179 kg.