A turbine disk fiber forming structure adapted to stress distribution
By setting a fiber-formed structure adapted to the stress distribution on the turbine disk, and utilizing the properties of carbon fiber and glass fiber, a multi-layered interlaced and reinforcing layer was designed. This solved the problem of mismatch between fiber layup and stress distribution, improved the stress load-bearing capacity and structural stability of the turbine disk, and extended its service life.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- NORTHWESTERN POLYTECHNICAL UNIV
- Filing Date
- 2026-05-26
- Publication Date
- 2026-07-14
AI Technical Summary
In the existing turbine disk fiber forming process, the actual stress distribution law of the disk is not taken into account for targeted structural design, resulting in a serious mismatch between the strength distribution and stress distribution of the fiber layup. In particular, the fiber load-bearing capacity is insufficient in the inner radius area, which becomes the weak point of the turbine disk structure strength, affecting its stability and service life.
A turbine disk fiber molding structure adapted to stress distribution is adopted. By setting circumferential and radial fiber dense winding layers on the turbine disk body, and utilizing the high tensile and compressive strength characteristics of carbon fiber and glass fiber, an equidistant spiral winding and staggered winding structure is designed to enhance the fiber layup density and overall connectivity in the inner radius area, forming a multi-layer fiber reinforcement layer to adapt to stress distribution.
It effectively improves the circumferential and radial stress bearing capacity of the turbine disk, increases the fiber bearing capacity in the inner radius area by more than 30%, and improves the circumferential stress dispersion effect in the outer radius area by 25%, thus extending the fatigue life of the turbine disk and avoiding local failure.
Smart Images
Figure CN122379061A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of turbine disk manufacturing technology, specifically to a turbine disk fiber molding structure adapted to stress distribution. Background Technology
[0002] As a core rotating component in aerospace, power machinery, and other fields, the turbine disk operates at high speeds, subjecting the disk to significant circumferential and radial stresses. A noticeable stress concentration occurs in the inner radius R0 = 0.1m region, while the outer radius Ra = 0.27m region exhibits a gradient characteristic dominated by circumferential stress. At speeds of 1000 rad / s, traditional structures are prone to localized failure due to insufficient stress bearing capacity. In the existing fiber forming process of turbine disks, in terms of circumferential fiber winding, a uniformly laid-up fiber winding method is generally adopted. In terms of radial fiber arrangement, the radial fibers are only used in a single method of overall wrapping, without strengthening the stress concentration area of the inner radius near the mandrel. Due to insufficient fiber load-bearing capacity, this area becomes a weak point in the structural strength of the turbine disk, which greatly reduces the structural stability and service life of the turbine disk. The failure to conduct targeted structural design based on the actual stress distribution of the disk resulted in a serious mismatch between the strength distribution and stress distribution of the fiber layup, which became a key technical problem restricting the structural stability and service life of the turbine disk. To address these issues, we propose a turbine disk fiber molding structure adapted to stress distribution. Summary of the Invention
[0003] The purpose of this invention is to provide a turbine disk fiber molding structure that adapts to stress distribution, so as to solve the problems mentioned in the background art.
[0004] To achieve the above objectives, the present invention provides the following technical solution: a turbine disk fiber molding structure adapted to stress distribution, comprising a turbine disk body, wherein a circumferential fiber tightly wound layer and a radial fiber tightly wound layer are provided on the turbine disk body; The circumferential fiber tightly wound layer is formed by an equidistant spiral winding manner; The radial fiber dense layer includes a radial fiber surrounding layer A, a radial fiber surrounding layer B, and a two-way blade radial fiber supplementary reinforcement layer filling the gap between the two. The radial fiber surrounding layer A and the radial fiber surrounding layer B are arranged in a double layer in the radial region inside the turbine disk. The coverage density of the two-way blade radial fiber supplementary reinforcement layer in the radial region outside the turbine disk is twice that of the radial fiber surrounding layer.
[0005] In a preferred embodiment of the present invention, the radial fiber tightly wound layer is provided for the stress concentration area with an inner radius R0 = 0.1m of the turbine disk body.
[0006] In a preferred embodiment of the present invention, the circumferential fiber tightly wound layer is wound in an equidistant spiral manner in the outer radius region of the turbine disk body, and the spiral spacing is 10mm.
[0007] In a preferred embodiment of the present invention, the fibers of the circumferential fiber-wound layer 2 are carbon fibers, which utilize their high tensile strength to meet the circumferential stress bearing requirements.
[0008] In a preferred embodiment of the present invention, the fibers of the radial fiber tightly wound layer are glass fibers, which utilize their high compressive strength to meet the radial stress bearing requirements.
[0009] As a preferred embodiment of the present invention, the radial fiber surrounding layer A is a concentric surrounding structure that starts from the outer edge, is pulled straight to the center, and wraps around the inner diameter edge of the turbine disk. The radial fibers surrounding layer A are evenly distributed in the circumferential direction and form corresponding gaps at the inner diameter edge of the turbine disk.
[0010] As a preferred embodiment of the present invention, the radial fiber surrounding layer B is a concentric surrounding structure that starts from the outer edge, is pulled straight to the center, and wraps around the inner diameter edge of the turbine disk. The radial fibers surrounding layer B are evenly distributed in the circumferential direction and form corresponding gaps at the inner diameter edge of the turbine disk. The radial fibers surrounding layer B and the radial fibers surrounding layer A are arranged alternately.
[0011] In a preferred embodiment of the present invention, the fibers of the radial fiber supplementary reinforcement layer of the two-way blade are linear structures bridging the circumference and intersecting each other to form a dense mesh distribution with the outer edges pulled out in opposite directions.
[0012] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. This turbine disk fiber molding structure, adapted to stress distribution, optimizes the partitioned and densely wound design of circumferential fibers. The winding spacing of the circumferential fibers is adjusted differently according to the stress distribution, with dense winding in the inner area and sparse winding in the outer area. This effectively limits the winding path of the circumferential fibers, achieving uniform distribution of the circumferential fibers. This allows the load-bearing capacity of the circumferential fibers to be precisely matched with the circumferential stress gradient changes in the outer radius area of the turbine disk. Tests have shown that the circumferential stress dispersion effect in the outer radius area is improved by more than 25%, effectively avoiding the problem of disk cracking caused by circumferential stress concentration.
[0013] 2. This turbine disk fiber molding structure adapted to stress distribution, through the design of a zoned and densely reinforced radial fiber structure, adopts a structure with a double-layer radial fiber surround and bidirectional blades to supplement the stress concentration area in the inner radius. This increases the fiber coverage density in this area to twice that of the conventional area, effectively improving the local fiber load-bearing capacity. Tests show that the radial stress load-bearing capacity in the inner radius is increased by more than 30%, completely solving the problem of insufficient local strength in the inner radius area in traditional processes. At the same time, the supplementary reinforcement layer also improves the integrity of the fiber layer and avoids the risk of delamination failure. Attached Figure Description
[0014] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0015] Figure 1 This is a schematic diagram of the circumferential fiber tightly wound layer of the present invention; Figure 2 This is a schematic diagram of the structure in this invention where radial fibers surround layer A; Figure 3 This is a schematic diagram of the structure of the radial fiber supplementary reinforcement layer for the two-way blade in this invention; Figure 4 This is a circumferential stress distribution cloud diagram of the turbine disk of the present invention; Figure 5 This is a radial stress distribution cloud diagram of the turbine disk of the present invention; Figure 6 This is a schematic diagram of the three-dimensional stress distribution of the turbine disk of the present invention; Figure 7 This is a graph showing the stress of the turbine disk as a function of radius in this invention. Figure 8 This is a schematic diagram of the fiber winding device in this invention.
[0016] In the figure: 1. Turbine disk body; 2. Circumferential fiber tightly wound layer; 3. Radial fiber tightly wound layer; 31. Radial fiber surrounding layer A; 32. Radial fiber surrounding layer B; 33. Radial fiber supplementary reinforcement layer for two-way blades; 4. Mounting base plate; 5. Circumferential fiber winding fiber disc; 6. Mandrel; 7. Warp hook; 8. Servo motor. Detailed Implementation
[0017] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0018] like Figure 1-8 As shown, the present invention provides a turbine disk fiber molding structure adapted to stress distribution, including a turbine disk body 1, on which a circumferential fiber tightly wound layer 2 and a radial fiber tightly wound layer are disposed; The circumferential fiber tightly wound layer 2 is composed of an equidistant spiral winding manner; The radial fiber dense layer includes a radial fiber surrounding layer A 31, a radial fiber surrounding layer B 32, and a two-way blade radial fiber supplementary reinforcement layer 33 filling the gap between the two. The radial fiber surrounding layer A 31 and the radial fiber surrounding layer B 32 are arranged in a double layer in the inner radius region of the turbine disk body 1. The layup density of the two-way blade radial fiber supplementary reinforcement layer 33 in the outer radius region of the turbine disk body 1 is twice that of the radial fiber surrounding layer.
[0019] Among them, the radial fiber tightly wound layer 3 is set for the stress concentration area with an inner radius R0=0.1m of the turbine disk body 1.
[0020] The circumferential fiber dense winding layer 2 is wound in an equidistant spiral manner in the outer radius region of the turbine disk body 1, with a spiral spacing of 10mm.
[0021] Specifically, in the stress concentration area of the inner radius, that is, the area 0 to 0.1m away from the center of the disk, this area is a stress concentration area. The design incorporates a double-layer radial fiber surround A and B, plus a two-way blade radial fiber supplementary reinforcement layer 33. The fiber layup density of the reinforcement layer is twice that of the conventional area, achieving multi-layer fiber reinforcement in this area. This effectively improves the local fiber load-bearing capacity, increasing the radial stress load-bearing capacity of the inner radius by more than 30%, and completely solving the problem of insufficient local strength in the inner radius area in traditional processes.
[0022] Furthermore, the fibers of the circumferential fiber-wound layer 2 are carbon fibers, which utilize their high tensile strength to meet the circumferential stress bearing requirements.
[0023] Specifically, carbon fiber was chosen as the material for the circumferential fiber because it has extremely high tensile strength, reaching over 3500 MPa, far exceeding that of ordinary metals and glass fibers. This perfectly matches the tensile stress bearing requirements of circumferential stress, maximizing the performance advantages of the fiber material. At the same time, carbon fiber has a very low density, only about 1.7 g / cm³, far lower than that of steel. Using carbon fiber as the circumferential fiber can significantly reduce the overall weight of the turbine disk, which is a very important advantage for aerospace applications, effectively improving the thrust-to-weight ratio of the engine.
[0024] Furthermore, the radial fiber tightly wound layer is made of glass fiber, which utilizes its high compressive strength to meet the radial stress bearing requirements.
[0025] Specifically, glass fiber was chosen as the material for the radial fibers because it has high compressive and shear strength, which perfectly matches the bearing requirements of radial compressive and shear stresses. At the same time, glass fiber is much cheaper than carbon fiber. Using it as radial fibers can effectively control the overall cost of the turbine disk, balancing performance and cost.
[0026] Among them, the radial fiber surrounding layer A 31 is a concentric winding structure that starts from the outer edge, is pulled straight to the center, and wraps around the inner diameter edge of the turbine disk body 1. That is, the fiber starts from the outer edge, is pulled to the center, wraps around the inner diameter edge of the turbine disk body 1, and then is pulled to the outer edge of the turbine disk body 1 on the opposite side. This forms a concentric radial fiber. By completing all the concentric windings in sequence, the radial fiber surrounding layer A 31 is formed. The fibers in this layer are all radial and are mainly used to bear the radial compressive stress, just like the warp threads of a spider web, bearing the radial force of the entire disk body. The radial fibers surrounding layer A 31 are evenly distributed in the circumferential direction and form corresponding gaps at the inner diameter edge of the turbine disk body 1.
[0027] The radial fiber surrounding layer B 32 is a concentric surrounding structure that starts from the outer edge, is pulled straight to the center, and wraps around the inner diameter edge of the turbine disk body 1. The radial fibers surrounding layer B 32 are evenly distributed in the circumferential direction and form corresponding gaps at the inner diameter edge of the turbine disk 1. The radial fibers surrounding layer B 32 and the radial fibers surrounding layer A 31 are arranged alternately. The radial fibers surrounding layer B 32 are an offset staggered structure, which works in conjunction with the radial fibers surrounding layer A 31. This structure can effectively cope with the complex shear stress during turbine disk operation. This is because, in addition to radial and circumferential stress, turbine disks also experience shear stress during operation. Pure radial fibers cannot effectively bear shear stress, but this offset staggered fiber structure can make up for this deficiency and improve the shear resistance of the disk.
[0028] The fibers of the two-way blade radial fiber supplementary reinforcement layer 33 are linear structures straddling the circumference, and they intersect to form a dense mesh distribution with the outer edges pulled out in opposite directions, effectively improving the radial load-bearing capacity of this area and solving the problem of insufficient local strength caused by stress concentration. At the same time, this two-way blade radial fiber supplementary reinforcement layer 33 also plays a connecting role, connecting the radial fibers surrounding layer A 31 and the radial fibers surrounding layer B 32 into a whole. In this way, when subjected to stress, there will be no relative slippage between the two layers, nor will there be any delamination problem, improving the integrity of the entire fiber layer. This is very important for the fatigue performance of the turbine disk, because the turbine disk rotates at high speed for a long time. Under long-term cyclic stress, traditional two-layer fibers without connection are prone to delamination, leading to structural failure. The supplementary reinforcement layer of this invention solves this problem and significantly improves the fatigue life of the turbine disk.
[0029] Specifically, the geometric parameters of turbine disk 1 are: outer radius Ra = 0.27m, inner radius R0 = 0.1m, thickness 2mm, material density 7800kg / m³, and operating speed ω = 1000rad / s. Under this condition, through finite element analysis (see...) Figure 4-7 The stress cloud diagram and curves show that the circumferential stress is distributed in a gradient along the radial direction, with the maximum stress occurring near the inner radius and the stress level in the outer radius region being higher and changing more gradually; the radial stress shows a significant stress concentration peak at the inner radius and decays rapidly outward.
[0030] To address the aforementioned stress characteristics, the circumferentially tightly wound fiber layer 2 is constructed using carbon fibers wound in equidistant spirals. Specific winding parameters are as follows: loose winding is used in the outer radius region (0.15m to Ra), with a spiral spacing of 10mm. This winding method ensures that the carbon fiber distribution density aligns with the circumferential stress gradient, providing a larger fiber load-bearing cross-section in the high-stress outer radius region. The radial fiber tightly wound layer 3 is made of glass fiber and has a three-layer structure: radial fiber surrounding layer A 31, radial fiber surrounding layer B 32, and a two-way blade radial fiber supplementary reinforcement layer 33. Both radial fiber surrounding layer A 31 and radial fiber surrounding layer B 32 are arranged in a double-layer configuration within the inner radius region (a ring-shaped band approximately 0.02m wide and around R0=0.1m). Specifically, the radial fiber surrounding layer A 31 is the first layer, with fibers originating from the outer edge warp hooks 7, drawn straight towards the center, wrapping around the sidewall of the mandrel 6, and then drawn towards the opposite warp hook 7, forming a roughly radial fiber bundle. Gaps are formed between adjacent fiber bundles at the inner diameter edge. The radial fiber surrounding layer B 32 is the second layer, with fibers also originating from the outer edge warp hooks 7, but staggered from the anchor points of layer A, forming an alternating winding arrangement.
[0031] A radial fiber supplementary reinforcement layer 33 for the two-way blades fills the gap between the radial fibers surrounding layer A 31 and layer B 32. The fibers in this supplementary reinforcement layer are chopped or partially laid-up glass fibers, arranged in a linear structure bridging the circumference, intersecting to form a dense network distribution. Its lay-up density is twice that of the radial fiber lay-up density in the outer radius region. This supplementary layer not only fills the gap between layers A and B but also significantly increases the fiber volume fraction in the inner radius region, forming a dense annular reinforcement band.
[0032] The formed turbine disk passed the strength test at a speed of 1000 rad / s. The radial stress bearing capacity of the inner radius area was improved by 32%, and the circumferential stress dispersion effect of the outer radius area was improved by 27%. No local cracking or deformation occurred, and the overall structural performance was better than that of the traditional uniform ply structure.
[0033] The present invention also provides an apparatus for fiber winding, which comprises five core components: a mandrel 6, a servo motor 8, a circumferential fiber winding limiting disc 5, a warp hook 7, and a mounting base plate 4. The mounting base plate 4 is made of stainless steel, providing stable support for the entire device. The mandrel 6 is vertically fixed at the center of the mounting base plate 4. The outer diameter of the mandrel 6 is matched with the inner radius R0=0.1m of the turbine disk. Its function is to serve as the inner diameter boundary during fiber winding and to form the center hole of the turbine disk after curing. The servo motor 8 is an adjustable speed motor, which is connected to the mandrel 6 and drives the mandrel 6 to rotate at a speed of 50-60r / min, providing power for the dense winding of circumferential fibers. The circumferential fiber winding limiting disk 5 is made of lightweight alloy and is coaxially sleeved with the mandrel 6. Its outer diameter is slightly larger than the outer radius of the turbine disk. It is used to limit the radial position of the turbine disk body 1 and prevent the fibers from deviating during winding. There are 8 warp hooks 7, which are evenly distributed in a ring along the outer side of the circumferential fiber winding limiting disk 5. They are used for hanging and guiding the radial fibers.
[0034] When the circumferential fibers are tightly wound, firstly, the servo motor 8 drives the entire mounting base plate 4 and the mandrel 6 to rotate at a constant speed. The fiber feed head moves slowly in the radial direction (from the inside to the outside or from the outside to the inside). The fibers are tightly attached to the turbine disk body 1 one circle at a time. The fiber lines are evenly wound around the turbine disk body 1 in the circumference to ensure that the spacing of each fiber is consistent and to avoid uneven spacing.
[0035] During this process, if the turbine disk has a double-sided structure, after completing the circumferential winding on one side, the turbine disk needs to be flipped so that the other side faces upwards, and the above circumferential winding operation is repeated. It is crucial to ensure that the winding thickness on both sides is consistent, and the starting points of the circumferential fibers and the fibers on the other side must be based on design requirements.
[0036] During the radial fiber winding process, after the circumferential fiber winding is completed, the radial fiber winding stage begins. The starting end of the glass fiber is fixed to a warp hook 7, and then wound according to a preset path: First, radial fibers are wound around layer A 31. The fiber starts from the hook, is pulled towards the side wall of the mandrel 6 and runs along it, and then is pulled towards the opposite hook for fixation. This process is repeated to complete the first layer of radial fiber mesh. Next, radial fibers are wound around layer B 32: The fiber path of the radial fibers around layer B 32 intersects with layer A. Starting from one hook, it runs around the mandrel and is biased towards another hook, forming a tangentially drawn fiber layer. After completing one side, the warp needs to be specifically treated, the core of which is the cutting and trimming operation. Then, the turbine disk body 1 is flipped over, and the other side is wound. Finally, a two-way blade radial fiber supplementary reinforcement layer 33 is wound: In this layer, glass fibers are densely filled between the gaps of the radial fibers around layer A 31 and the radial fibers around layer B 32 using a short-cut or continuous cross-lay method to form a mesh structure.
[0037] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. A turbine disk fiber-molded structure adapted to stress distribution, comprising a turbine disk body (1), characterized in that: The turbine disk body (1) is provided with a circumferential fiber dense winding layer (2) and a radial fiber dense winding layer; The circumferential fiber tightly wound layer (2) is formed in an equidistant spiral winding manner; The radial fiber dense layer includes a radial fiber surrounding layer A (31), a radial fiber surrounding layer B (32), and a two-way blade radial fiber supplementary reinforcement layer (33) filling the gap between the two. The radial fiber surrounding layer A (31) and the radial fiber surrounding layer B (32) are arranged in a double layer in the inner radius region of the turbine disk body (1). The coverage density of the two-way blade radial fiber supplementary reinforcement layer (33) in the outer radius region of the turbine disk body (1) is twice that of the radial fiber surrounding layers (31, 32).
2. The turbine disk fiber molding structure adapted to stress distribution according to claim 1, characterized in that: The radial fiber tightly wound layer (3) is set for the stress concentration area with an inner radius R0=0.1m of the turbine disk body (1).
3. The turbine disk fiber molding structure adapted to stress distribution according to claim 2, characterized in that: The circumferential fiber dense winding layer (2) is wound in an equidistant spiral pattern in the outer radius region of the turbine disk body (1), with a spiral spacing of 10mm.
4. The turbine disk fiber molding structure adapted to stress distribution according to claim 3, characterized in that: The fibers of the circumferential fiber-wound layer (2) are carbon fibers, which are used to adapt to the circumferential stress bearing requirements by utilizing their high tensile strength.
5. The turbine disk fiber molding structure adapted to stress distribution according to claim 4, characterized in that: The radial fiber tightly wound layer is made of glass fiber, which utilizes its high compressive strength to meet the radial stress bearing requirements.
6. The turbine disk fiber molding structure adapted to stress distribution according to claim 5, characterized in that: The radial fiber surrounding layer A (31) is a concentric surrounding structure that starts from the outer edge, is pulled straight to the center, and fits the inner diameter edge of the turbine disk body (1). The radial fibers surrounding layer A (31) are evenly distributed in the circumferential direction and form corresponding gaps at the inner diameter edge of the turbine disk body (1).
7. The turbine disk fiber molding structure with adaptive stress distribution according to claim 6, characterized in that: The radial fiber surrounding layer B (32) is a concentric surrounding structure that starts from the outer edge, is pulled straight to the center, and fits the inner diameter edge of the turbine disk body (1). The radial fibers surrounding layer B (32) are evenly distributed in the circumferential direction and form corresponding gaps at the inner diameter edge of the turbine disk body (1). The radial fibers surrounding layer B (32) and the radial fibers surrounding layer A (31) are arranged alternately.
8. The turbine disk fiber molding structure adapted to stress distribution according to claim 7, characterized in that: The fibers of the radial fiber supplementary reinforcement layer (33) of the two-way blade are linear structures that are bridging the circumference and intersecting each other to form a dense mesh distribution with the outer edges pulled out in opposite directions.