A turbine disk and an aircraft engine

Abstract

The application discloses a turbine disc and an aero-engine, and relates to the technical field of turbine discs, and specifically discloses a turbine disc and an aero-engine, which comprises a disc body, wherein the disc body comprises a main disc body and a disc rim, the disc rim is arranged around the outer diameter side of the main disc body, the axial dimension of the main disc body gradually decreases along the radial direction of the main disc body from the inner diameter side of the main disc body to the outer diameter side of the main disc body, the annular cavities are arranged in the main disc body, the annular cavities are arranged around the disc core of the main disc body, and a plurality of annular cavities are arranged along the radial direction of the main disc body. The hollow structure is arranged in the disc body, so that the weight of the disc body is reduced, meanwhile, a plurality of annular cavities with gradually decreasing axial dimensions are arranged according to the structural features of the disc body, so that the disc body has high rigidity and stability, and each part of the disc body can be sufficiently cooled, so that the cooling effect is improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft engines, and more specifically, to a turbine disk and an aircraft engine. Background Technology

[0002] Lightening the turbine disk is a powerful measure to improve the thrust-to-weight ratio of an engine. To this end, those skilled in the art have designed turbine disks with hollow structures. However, the hollow structure reduces the stiffness and stability of the turbine disk. The hollow structure of the turbine disk is used for cooling air circulation; if the stiffness and stability of the turbine disk are improved simply by reducing the volume of the hollow structure, then a smaller volume hollow structure will affect the cooling effect of the cooling air.

[0003] Therefore, how to achieve a lightweight turbine disk while improving its rigidity and stability, as well as the cooling efficiency of the cooling gas, is a key problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0004] The objective of this invention is to achieve both lightweight turbine disks and improved turbine disk rigidity and stability, while also enhancing the cooling efficiency of the cooling air. To achieve these objectives, this invention provides the following technical solution:

[0005] A turbine disk includes a disk body, the disk body including a main disk body and a disk rim, the disk rim being disposed around the outer diameter side of the main disk body, and the axial dimension of the main disk body gradually decreasing along the radial direction of the main disk body and from the inner diameter side of the main disk body to the outer diameter side of the main disk body;

[0006] The main disk body is provided with an annular cavity, which surrounds the center of the main disk body. There are multiple annular cavities, which are arranged radially along the main disk body.

[0007] An exhaust channel is provided inside the rim of the disc. The annular cavity closest to the rim of the disc is connected to the exhaust channel. The annular cavity closest to the inner diameter side of the main disc body is connected to the center of the main disc body. The center of the main disc body is used for air intake. The multiple annular cavities are connected to each other in a radial direction.

[0008] The annular cavity is cut by a plane passing through the axis of the main disk, and the cross-section is a trapezoidal cross-section. The upper and lower bases of the trapezoidal cross-section are arranged radially along the main disk. The upper base is farther away from the center of the main disk relative to the lower base, and the size of the upper base is smaller than the size of the lower base. In two adjacent annular cavities, the size of the lower base of the trapezoidal cross-section of the annular cavity farther from the center of the main disk is smaller than the size of the upper base of the trapezoidal cross-section of the annular cavity closer to the center of the main disk.

[0009] Preferably, a venting annular groove is provided in the main disc body, the venting annular groove is arranged around the center of the main disc body, and two adjacent annular cavities are connected through the venting annular groove;

[0010] The cross-section of the ventilation ring groove, obtained by the plane passing through the axis of the main disc, is a rectangular cross-section. The axial dimension of the ventilation ring groove is smaller than the dimension of the lower base of the trapezoidal cross-section of the annular cavity connected to it, and the annular cavity connected to it is far away from the center of the main disc relative to the ventilation ring groove.

[0011] Preferably, in two adjacent annular cavities, the volume of the annular cavity farther from the center of the main disk is greater than the volume of the annular cavity closer to the center of the main disk.

[0012] Preferably, the annular cavity closest to the inner diameter side of the main disc body is connected to the center of the main disc body through the venting annular groove.

[0013] Preferably, the ventilation ring groove is provided with a partition block, and in the axial direction of the main disc, the two opposite walls of the partition block are in contact with the two opposite walls of the ventilation ring groove; the partition block is a plurality of partition blocks arranged circumferentially around the ventilation ring groove.

[0014] Preferably, the spacing between two adjacent partitions in each of the ventilation ring grooves increases sequentially along the direction from the inner diameter side of the main disc to the outer diameter side of the main disc.

[0015] Preferably, the disk rim is provided with a plurality of exhaust channels, the plurality of exhaust channels are arranged around the center of the main disk body, and the plurality of exhaust channels correspond one-to-one with a plurality of blades.

[0016] Preferably, the disk body is a two-half type along the axial direction of the disk body, and the disk rim, the main disk body, the annular cavity and the partition block are all two-half type;

[0017] The two halves of the disc are welded together, and the welding surface on each half of the disc includes the inner side of the edge of each half of the disc and the inner side of the partition block of each half.

[0018] Preferably, the upper base of the trapezoidal cross-section of the annular cavity closest to the outer diameter side of the main disc body is not less than 4 mm.

[0019] The present invention also provides an aircraft engine, including a turbine disk, wherein the turbine disk is any of the turbine disks described above.

[0020] As can be seen from the above technical solution, this embodiment not only sets a hollow structure in the disk body to achieve the weight reduction of the disk body, but also sets multiple annular cavities with progressively smaller axial dimensions according to the structural characteristics of the disk body to ensure that the disk body as a whole has high rigidity and stability, and at the same time ensures that all parts of the disk body can be fully cooled, thereby improving the cooling effect. Attached Figure Description

[0021] To more clearly illustrate the solutions in the embodiments of the present invention, the accompanying drawings used in the embodiments 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.

[0022] Figure 1 A cross-sectional view of the disk body taken by a plane passing through the axis of the disk body according to a specific embodiment of the present invention;

[0023] Figure 2 This is a cross-sectional view of the disk body obtained by a plane perpendicular to the axis of the disk body, according to a specific embodiment of the present invention.

[0024] Among them, 1 is the disc body, 11 is the main disc body, 12 is the disc edge, 2 is the annular cavity, 3 is the ventilation ring groove, 4 is the exhaust channel, 5 is the disc center, and 6 is the partition block. Detailed Implementation

[0025] This invention discloses a turbine disk that achieves both lightweight design and improved rigidity and stability, while also enhancing the cooling efficiency of the cooling air. This invention also discloses an aero-engine.

[0026] 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 a part of the embodiments of the present invention, and not all of the 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.

[0027] Please refer to the attached document. Figure 1 - Appendix Figure 2 .

[0028] This invention discloses a turbine disk, which includes a disk body 1, comprising a main disk body 11 and a disk rim 12. The center 5 of the main disk body 11 is used for intake of cooling air. The disk rim 12 is arranged around the outer diameter side of the main disk body 11. Along the radial direction of the disk body 1, from the inner diameter side to the outer diameter side of the main disk body 11, the axial dimension of the main disk body 11 gradually decreases. In other words, along the radial direction of the disk body 1, from the inner diameter side to the outer diameter side of the main disk body 11, the thickness of the main disk body 11 gradually decreases. Compared to a main disk body with a uniform axial dimension in the radial direction, the main disk body 11 that gradually thins along the radial direction in this invention is lighter, thereby facilitating the weight reduction of the main disk body 11.

[0029] In a specific embodiment of the present invention, an annular cavity 2 is provided inside the main disk body 11, and the annular cavity 2 is arranged around the disk center 5 of the main disk body 11. There are multiple annular cavities 2, and the multiple annular cavities 2 are arranged radially along the main disk body 11.

[0030] An exhaust channel 4 is provided inside the rim 12, and the annular cavity 2 closest to the rim 12 communicates with the exhaust channel 4 inside the rim 12. The annular cavity 2 closest to the inner diameter side of the main disc body 11 communicates with the center 5 of the main disc body 11, which is used for air intake. Multiple annular cavities 2 are connected radially in sequence. Cooling air first enters the center 5 of the main disc body 11, and then, under the action of centrifugal force, enters the annular cavity 2 near the center 5 of the main disc body 11. Afterward, it passes through each annular cavity 2 radially in sequence, and finally exits from the exhaust channel 4 inside the rim 12.

[0031] In this embodiment, the annular cavity 2 is characterized as follows: the cross-section of the annular cavity 2 obtained by the plane passing through the axis of the main disk 11 is a trapezoidal cross-section. The upper and lower bases of the trapezoidal cross-section are arranged radially along the main disk 11. The upper base is farther away from the disk center 5 of the main disk 11 than the lower base, and the size of the upper base is smaller than the size of the lower base. In two adjacent annular cavities 2, the axial dimension of the lower base of the trapezoidal cross-section of the annular cavity 2 farther from the disk center 5 of the main disk 11 is smaller than the size of the upper base of the trapezoidal cross-section of the annular cavity 2 closer to the disk center 5 of the main disk 11. That is, the thickness of each annular cavity 2 gradually decreases along the radial direction of the main disk 11 from the inner diameter side to the outer diameter side. For the same annular cavity 2, the thickness gradually decreases along the radial direction of the main disk 11 from the inner diameter side to the outer diameter side.

[0032] In this embodiment, the main disk 11 gradually thins along its radial direction from the inner diameter to the outer diameter. Multiple annular cavities, also gradually thinning along the radial direction from the inner diameter to the outer diameter, are adapted to the gradually thinning main disk 11. The thicker sections of the main disk 11 have correspondingly thicker annular cavities 2, which can hold more cooling air, thus effectively cooling the thicker sections of the main disk 11 while ensuring high rigidity in these areas. The thinner sections of the main disk 11 require less cooling air; therefore, the corresponding annular cavities 2 are designed to be thinner, ensuring high rigidity in the thinner sections of the main disk 11.

[0033] This embodiment not only features a hollow structure within the disk body 1, thus achieving a lightweight design, but also incorporates multiple annular cavities 2 with progressively decreasing axial dimensions, based on the structural characteristics of the disk body 1. This ensures that the disk body 1 as a whole possesses high rigidity and stability, while also ensuring that all parts of the disk body 1 can be adequately cooled, thereby improving the cooling effect.

[0034] It should be noted that the axial dimensions of the multiple annular cavities 2 decrease sequentially along the radial direction of the main disk 11 from the inner diameter side to the outer diameter side. Therefore, to avoid sharp angles in the annular cavities 2 along the axial direction, which would cause stress concentration, this invention limits the upper base dimension of the trapezoidal cross-section of the annular cavity 2 closest to the disk edge 12 to be no less than 4 mm. Since the upper base dimension of the trapezoidal cross-section of the annular cavity 2 closest to the disk edge 12 is the smallest among all the trapezoidal cross-sections of the annular cavity 2, if the upper base dimension of the trapezoidal cross-section of the annular cavity 2 closest to the disk edge 12 is no less than 4 mm, then the lower base dimension of the trapezoidal cross-section of this annular cavity 2, as well as the upper and lower base dimensions of the trapezoidal cross-sections of the other annular cavities 2, are all greater than 4 mm.

[0035] In a specific embodiment of the present invention, a venting annular groove 3 is further provided inside the main disc body 11, and the venting annular groove 3 is arranged around the center 5 of the main disc body 11. Two adjacent annular cavities 2 are connected by the venting annular groove 3. The venting annular groove 3 in this embodiment is characterized in that: the cross-section of the venting annular groove 3 obtained by the plane passing through the axis of the main disc body 11 is rectangular, the axial dimension of the venting annular groove 3 is smaller than the axial dimension of the lower base of the trapezoidal cross-section of the annular cavity 2 connected to it, and the annular cavity 2 connected to it is farther away from the center 5 of the main disc body 11 relative to the venting annular groove 3. In other words, the annular cavity 2 connected to the venting annular groove 3 is the one annular cavity 2 that is farther away from the center 5 of the main disc body 11.

[0036] The two annular cavities 2 connected to the ventilation ring groove 3 have relatively large axial dimensions, so the cooling air in the two annular cavities 2 is sufficient to cool the area where the two annular cavities 2 are located to the preset temperature. If two adjacent annular cavities 2 are directly connected, the cooling effect will be weakened, and the hollow volume of the main disk 11 will be increased, thereby weakening the rigidity and stability of the main disk 11.

[0037] In this embodiment, two adjacent annular cavities 2 are connected by a venting annular groove 3. The venting annular groove 3 contracts axially relative to the two annular cavities 2 it connects to, thereby reducing the hollow volume of the area where the venting annular groove 3 is located, thus improving the rigidity and stability of the main disc 11. The venting annular groove 3 between two adjacent annular cavities 2 mainly serves to connect the two annular cavities 2.

[0038] The alternating arrangement of ventilation ring grooves 3 and annular cavities 2 constitutes a bamboo joint structure. Bamboo has excellent pressure resistance and stability, so the disc body 1 in this invention also has good pressure resistance and stability.

[0039] For two adjacent annular cavities 2, if the volume of the annular cavity 2 farther from the main disk body 11 center 5 is smaller than the volume of the annular cavity 2 closer to the main disk body 11 center 5, it is not conducive to the flow of cooling gas from the center 5 to the edge 12. Therefore, this embodiment limits the volume of the annular cavity 2 farther from the main disk body 11 center 5 to be greater than the volume of the annular cavity 2 closer to the main disk body 11 center 5 in two adjacent annular cavities 2. Since the area of ​​the trapezoidal cross section of the annular cavity 2 farther from the main disk body 11 center 5 in two adjacent annular cavities 2 is smaller than the area of ​​the trapezoidal cross section of the annular cavity 2 closer to the main disk body 11 center 5, it is necessary to ensure that the annular cavity 2 farther from the main disk body 11 center 5 has a larger radial dimension to ensure that the volume of this annular cavity 2 is greater than the volume of the annular cavity 2 closer to the main disk body 11 center 5.

[0040] In a specific embodiment of the present invention, the annular cavity 2 closest to the inner diameter side of the main disk body 11 is connected to the disk center 5 of the main disk body 11 via a venting annular groove 3. One end of the venting annular groove 3 is directly connected to the disk center 5, and the other end of the venting annular groove 3 is connected to the annular cavity 2 closest to the disk center 5 of the main disk body 11. Since the axial dimension of the venting annular groove 3 is smaller than the axial dimension of the annular cavity 2 connected to it, the main disk body 11 has high rigidity and stability at the venting annular groove 3, so as to effectively resist the disk center stress at the disk center 5.

[0041] In a specific embodiment of the present invention, a partition block 6 is provided in the venting ring groove 3. Two opposing wall surfaces of the partition block 6 along the axial direction of the main disc 11 respectively contact two opposing wall surfaces of the venting ring groove 3 along the axial direction of the main disc 11. In other words, the partition block 6 divides the venting ring groove 3 into non-communicating arc segments along its circumference. If multiple partition blocks 6 are provided in the venting ring groove 3 arranged circumferentially, then the multiple partition blocks 6 divide the venting ring groove 3 into multiple arc segments. The provision of the partition block 6 effectively improves the structural stiffness and stability of the area in which it is located.

[0042] To facilitate the flow of cooling air from the inner diameter side to the outer diameter side of the main disc 11, this embodiment defines that the spacing between two adjacent partitions 6 in each venting annular groove 3 increases sequentially from the inner diameter side to the outer diameter side of the main disc 11. In other words, the further away from the center 5 of the main disc 11 the venting annular groove 3 is, the larger the spacing between adjacent partitions 6 inside it. The larger the spacing between adjacent partitions 6, the smaller the resistance to cooling air, and the more conducive it is to the flow of cooling air.

[0043] For the venting annular groove 3 used to connect the annular cavity 2 of the disk center 5 and the disk center 5 closest to the main disk body 11, the number and circumferential dimensions of the partition blocks 6 in the venting annular groove 3 are designed according to the air intake at the disk center 5. If the air intake at the disk center 5 is large, the number of partition blocks 6 and the circumferential dimensions of the partition blocks 6 are reduced, thereby reducing the resistance of the cooling air. If the air intake at the disk center 5 is small, the number of partition blocks 6 and the circumferential dimensions of the partition blocks 6 are increased. Based on rigidity and stability considerations, the sum of the circumferential dimensions of the multiple partition blocks 6 in the circumferential direction is not less than 40% of the circumferential dimension of the disk center 5.

[0044] In one specific embodiment of the present invention, four annular cavities 2 and four ventilation annular grooves 3 are arranged radially along the main disk body 11. Eight spacers 6 are evenly distributed in each ventilation annular groove 3.

[0045] As described above, the rim 12 is provided with exhaust channels 4. In a specific embodiment of the present invention, multiple exhaust channels 4 are designed, arranged around the center 5 of the main rim 11. Each exhaust channel 4 corresponds to one blade. The cooling air discharged from the exhaust channel 4 enters the interior of the blade. In a specific embodiment of the present invention, the number of exhaust channels 4 is not less than 53, and the cross-sectional area of ​​the exhaust channels 4 is not less than 10 mm². 2 The number of exhaust channels 4 can vary depending on the number of blades, and the cross-sectional area of ​​the exhaust channels 4 can vary depending on the amount of cooling air.

[0046] In a specific embodiment of the present invention, the disc body 1 has a two-half structure, and the two halves of the disc body 1 are assembled along the axial direction to form a complete disc body 1. If the disc body 1 is two-half, then the disc rim 12, the main disc body 11, the annular cavity 2, and the spacer 6 are also correspondingly two-half. One half of the disc body 1 is formed by forging and machining in sequence, and then the two halves of the disc body 1 are welded together to form a complete disc body 1. The two-half disc body 1 facilitates the forming of the annular cavity 2, thereby reducing the processing difficulty of the disc body 1.

[0047] Specifically, diffusion welding is used to weld the two halves of the disc 1. Diffusion welding has advantages such as high welding quality, no need for post-weld processing, and high degree of automation. The welding surface of each half of the disc 1 includes the inner surface of the rim 12 of each half and the inner surface of the spacer 6 of each half. The spacer 6 is disposed in each venting ring groove 3, and multiple spacers 6 are evenly distributed in each venting ring groove 3. Therefore, multiple welding surfaces corresponding to the spacers 6 are distributed along the radial and circumferential directions of the disc 1, which improves the uniformity and firmness of the connection between the two halves of the disc 1.

[0048] The present invention also discloses an aero-engine, including a turbine disk, specifically any of the turbine disks described above. The turbine disks described above have the aforementioned effects, and the aero-engines having the aforementioned turbine disks also have the aforementioned effects; therefore, further details are omitted here.

[0049] Finally, it should be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0050] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0051] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A turbine disk, characterized in that, Includes a disk body (1), the disk body (1) includes a main disk body (11) and a disk edge (12), the disk edge (12) is arranged around the outer diameter side of the main disk body (11), and along the radial direction of the main disk body (11) from the inner diameter side of the main disk body (11) to the outer diameter side of the main disk body (11), the axial dimension of the main disk body (11) gradually decreases; The main disk body (11) is provided with an annular cavity (2), which surrounds the disk center (5) of the main disk body (11). There are multiple annular cavities (2), which are arranged radially along the main disk body (11). An exhaust channel (4) is provided inside the rim (12). The annular cavity (2) closest to the rim (12) is connected to the exhaust channel (4). The annular cavity (2) closest to the inner diameter side of the main disc body (11) is connected to the center (5) of the main disc body (11). The center (5) of the main disc body (11) is used for air intake. Multiple annular cavities (2) are connected in sequence. The cross section of the annular cavity (2) cut by the plane passing through the axis of the main disk (11) is a trapezoidal cross section. The upper and lower bases of the trapezoidal cross section are arranged radially along the main disk (11). The upper base is farther away from the center (5) of the main disk (11) relative to the lower base, and the size of the upper base is smaller than the size of the lower base. In two adjacent annular cavities (2), the size of the lower base of the trapezoidal cross section of the annular cavity (2) farther away from the center (5) of the main disk (11) is smaller than the size of the upper base of the trapezoidal cross section of the annular cavity (2) closer to the center (5) of the main disk (11). The axial dimensions of the plurality of annular cavities (2) gradually decrease from the inner diameter side to the outer diameter side along the radial direction of the main disk body (11), and correspond to the change in the axial dimensions of the main disk body (11), so that the cooling gas flows through the plurality of annular cavities (2) in sequence to perform differentiated cooling on different radial parts and maintain the rigidity of the corresponding parts of the main disk body (11). The main plate (11) is provided with a ventilation ring groove (3), which is arranged around the center (5) of the main plate (11). Two adjacent annular cavities (2) are connected through the ventilation ring groove (3). The cross section of the ventilation ring groove (3) cut by the plane passing through the axis of the main disk body (11) is a rectangular cross section. The axial dimension of the ventilation ring groove (3) is smaller than the dimension of the lower base of the trapezoidal cross section of the annular cavity (2) connected to it. The connected annular cavity (2) is far away from the center (5) of the main disk body (11) relative to the ventilation ring groove (3). The annular cavity (2) away from the disk center (5) has a larger radial dimension, such that the volume of the annular cavity (2) away from the disk center (5) of the main disk body (11) is greater than the volume of the annular cavity (2) close to the disk center (5) of the main disk body (11).

2. The turbine disk according to claim 1, characterized in that, The annular cavity (2) closest to the inner diameter side of the main disc (11) is connected to the center (5) of the main disc (11) through the ventilation annular groove (3).

3. The turbine disk according to claim 1, characterized in that, A partition (6) is provided in the ventilation ring groove (3). On the axial direction of the main disc (11), the two opposite walls of the partition (6) are in contact with the two opposite walls of the ventilation ring groove (3); the partition (6) consists of a plurality of partitions arranged circumferentially around the ventilation ring groove (3).

4. The turbine disk according to claim 3, characterized in that, The spacing between two adjacent partitions (6) in each of the ventilation ring grooves (3) increases sequentially along the direction from the inner diameter side of the main disc (11) to the outer diameter side of the main disc (11).

5. The turbine disk according to claim 1, characterized in that, The disk edge (12) is provided with a plurality of exhaust channels (4), which are arranged around the disk center (5) of the main disk body (11), and the plurality of exhaust channels (4) correspond to a plurality of blades.

6. The turbine disk according to claim 3, characterized in that, Along the axial direction of the disk body (1), the disk body (1) is a two-half type, and the disk edge (12), the main disk body (11), the annular cavity (2) and the partition block (6) are all two-half type; The two halves of the disc body (1) are welded together, and the welding surface on each half of the disc body (1) includes the inner side of the edge (12) of each half of the disc body (1) and the inner side of the partition (6) of each half of the disc body (1).

7. The turbine disk according to claim 1, characterized in that, The size of the upper base of the trapezoidal cross section of the annular cavity (2) closest to the outer diameter side of the main disk body (11) is not less than 4 mm.

8. An aircraft engine, comprising a turbine disk, characterized in that, The turbine disk is the turbine disk as described in any one of claims 1-7.

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