CN213063684U

CN213063684U - Turbine disc structure with double inner ring cavities

Info

Publication number: CN213063684U
Application number: CN202022142981.7U
Authority: CN
Inventors: 闫成; 赵超帆; 尤延铖; 范俊; 邱若凡; 陈策; 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 double inner ring cavities relates to the technical field of aero-engines and comprises a wheel disc, wherein two closed cavities which are communicated in the wheel disc along the circumferential direction are formed in the wheel disc; the two cavities are positioned between the center line of the wheel disc and the outer rim and distributed at two ends; one cavity is close to the edge surface of the wheel disc, and the caliber of the cavity is gradually increased from the inner side of the wheel disc to the outer rim; the other cavity is close to the wheel center, and the caliber of the other cavity is gradually reduced from the inner side of the wheel disc to the outer wheel rim. 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 double inner ring cavities

Technical Field

The utility model relates to an aeroengine technical field especially relates to a take turbine disc structure of two inner ring cavities.

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 two inner ring cavities, 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 double inner ring cavities comprises a wheel disc, wherein two closed cavities which are communicated in the wheel disc along the circumferential direction are formed in the wheel disc; the two cavities are positioned between the center line of the wheel disc and the outer rim and distributed at two ends; one cavity is close to the edge surface of the wheel disc, and the caliber of the cavity is gradually increased from the inner side of the wheel disc to the outer rim; the other cavity is close to the wheel center, and the caliber of the other cavity is gradually reduced from the inner side of the wheel disc to the outer wheel rim.

Two cavitys all are class isosceles triangle and set up, and two base angles constitute by 3mm circular arc chamfer, and two apex angles constitute by 3mm circular arc chamfer and 4mm circular arc chamfer respectively.

The outer contour of the wheel disc is provided with a plurality of annular grooves, each annular groove is composed of inward-concave arc curves, and the arc curves are in tangent connection with straight-line sections of the outer contour.

The original model volume of the turbine disk is 4.578 multiplied by 10⁶mm³The mass is 35.847kg, and the volume of the turbine disc structure with the double inner ring cavities is 3.071 multiplied by 10⁶mm³The mass was 24.045 kg.

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

1. the structure volume of the utility model is 3.071 multiplied by 10⁶mm³The mass is 24.045k, and the volume of the original turbine disk model is 4.578X 10⁶mm³The quality is 35.847kg, under the condition that stress all satisfies the requirement the utility model discloses more former turbine dish quality reduction 32.92%, and then alleviate aeroengine weight, reduce cost to improve the engine thrust-weight ratio.

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

Drawings

Fig. 1 is a schematic overall structure diagram of the turbine disk with double inner ring cavities.

FIG. 2 is a partial schematic view of the structure of the turbine disk with double inner ring cavities.

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

Fig. 4 is a schematic diagram of a 15 ° sector model extraction of a turbine disk.

FIG. 5 is a block size diagram of a sector model of a turbine disk.

FIG. 6 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 FIGS. 1-3, this embodiment includes rim plate 1, and the centre of a circle department of rim plate 1 is equipped with axial hole 3, and rim plate 1 is inside to be equipped with inclosed two inner ring cavity 2, and two inner ring cavity 2 link up along the circumferencial direction in rim plate 1.

Specifically, the cavities 2 of the double inner rings are distributed at two ends, one cavity is close to the rim surface 4 of the wheel disc, and the caliber of the cavity is gradually increased from the inner side of the wheel disc to the outer rim; the other cavity is close to the wheel center, and the caliber of the other cavity is gradually reduced from the inner side of the wheel disc to the outer wheel rim.

More specifically, two inner ring cavities 2 all are isosceles triangle-like and set up, and base angle 5 and base angle 8 of two inner ring cavities 2 constitute by 3mm circular arc chamfer, and apex angle 6 comprises 3mm circular arc chamfer, and apex angle 7 comprises 4mm circular arc chamfer. The arc chamfering mode can effectively avoid the problem of stress concentration.

The outer contour of the turbine disc structure with the double inner ring cavities 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, each annular groove is composed of inward-concave arc curves, and the arc curves are in tangent connection with straight-line sections of the outer contour.

Specifically, the outer contour of the turbine disk of the present embodiment is formed by connecting

straight line segments

9 and 12 with

circular arc curves

10, 11, 13, 14, 15 and 16. Wherein, the radius of the circular arc curve 10 is 6mm, the radius of the circular arc curve 11 is 10mm, the radius of the circular arc curve 13 is 27.09mm, the radius of the circular arc curve 14 is 50mm, the radius of the circular arc curve 15 is 30mm, and the radius of the circular arc curve 16 is 52.25 mm.

This embodiment saves rim plate 1's consumptive material through the two inner ring cavity 2 of the hollow inclosed of interior design at rim plate 1 to make the structural efficiency of rim plate 1 obtain greatly improving, alleviate the whole weight of rim plate 1 with the maximize, avoid the stress concentration of rim plate 1, thereby reach the weight that alleviates rim plate 1 and improve the engine and push away the weight ratio.

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 3.071 multiplied by 10⁶mm³The quality is 24.045kg, the utility model discloses all satisfy under the condition of requirement than former turbine dish quality reduction 32.92% at stress, and then alleviate aeroengine weight, reduce cost to improve the engine and push away the weight ratio, embody the utility model discloses a value place.

The structure design method of the utility model is as follows:

the first step is as follows: the original turbine disk model is subjected to sector model segmentation in UG software, and a sector model is extracted, wherein the turbine disk structure with the double inner ring cavities is based on the extraction of a 15-degree sector model, as shown in FIG. 4. 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 second step is that: the 15 ° sector model extracted from the first step is exported in UG software as parasolid file, file type is in the format of x.

The third 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. 5, 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 treatment of the model in the fourth step. This step aims to provide conditions for setting the corresponding local stress constraints for topology optimization.

The fourth step: running ansys workbench software, establishing a static structural module, setting material attributes in engineering data, and importing a parasolid file exported by UG software in the second step into geometry, wherein the material attributes of the turbine disk structure with the double-inner-ring cavity are set according to a material GH4169 in the embodiment. Entering a geometry to perform blocking processing on the imported model, and then entering a model module to perform mesh division processing on the model, wherein the size of a mesh unit is 2.5mm, and the number of the mesh units is 12688. 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. 6. 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.

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

The fifth 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: the mass retention 50% constrained, blocked local stress 800MPa constrained, and non-optimized regions are the rim and hub faces, which are shown in fig. 4; 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. Consider that topological optimization result is very sensitive to the temperature field, and the material has or not directly decides whether or not of thermal stress, so the utility model discloses the topological optimization research of considering temperature field load and neglecting temperature field load has been developed respectively to contrast its result, finally select the better scheme of result.

And a sixth step: and performing model reconstruction in UG software based on a topological optimization result of the ansys workbench software. 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.

The seventh step: and selecting a reasonable variation range of the design variables according to the sixth step, carrying out size optimization on the reconstructed model in UG software, and importing the established model into ansys workbench software for statics analysis, wherein the specific method is as described in the fourth step.

Eighth step: and comparing the analysis result obtained in the seventh 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 seventh step until the requirements are met, and finally obtaining a reasonable optimization model. The embodiment provides a novel structural material of a turbine disk with double inner ring cavities, which adopts GH 4169.

And selecting a reasonable model block size according to the stress field distribution of the original model of the turbine disc, and performing block processing on the original model of the turbine disc before topology optimization, as shown in the third step. The operation is beneficial to more reasonably carrying out stress operation during topology optimization calculation, and further more reasonable models can be obtained. And simultaneously, the utility model discloses not only there is the structure of two inner ring cavities 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 two inner ring cavities which characterized in that: the device comprises a wheel disc, wherein two closed cavities which are communicated in the wheel disc along the circumferential direction are formed in the wheel disc; the two cavities are positioned between the center line of the wheel disc and the outer rim and distributed at two ends; one cavity is close to the edge surface of the wheel disc, and the caliber of the cavity is gradually increased from the inner side of the wheel disc to the outer rim; the other cavity is close to the wheel center, and the caliber of the other cavity is gradually reduced from the inner side of the wheel disc to the outer wheel rim.

2. The turbine disk structure with dual inner ring cavities of claim 1, wherein: two cavitys all are class isosceles triangle and set up, and two base angles constitute by 3mm circular arc chamfer, and two apex angles constitute by 3mm circular arc chamfer and 4mm circular arc chamfer respectively.

3. The turbine disk structure with dual inner ring cavities of claim 1, wherein: the outer contour of the wheel disc is provided with a plurality of annular grooves, each annular groove is composed of inward-concave arc curves, and the arc curves are in tangent connection with straight-line sections of the outer contour.

4. The turbine disk structure with dual inner ring cavities of claim 1, wherein: the volume of the turbine disk structure with the double inner ring cavities is 3.071 multiplied by 10⁶mm³The mass was 24.045 kg.