Sealing structure and aeroengine

Abstract

The present application relates to the technical field of aero-engine, and discloses a sealing structure and an aero-engine, the sealing structure comprising: a turbine shaft, a first conveying hole being formed in the outer wall of the turbine shaft; a turbine disc comprising a disc shaft and a last stage disc, the disc shaft being fixedly sleeved on the outer side of the turbine shaft, the disc shaft being provided with a second conveying hole, the first conveying channel being communicated with the cooling space and the second conveying channel through the first conveying hole; a sealing cover, the sealing cover being sleeved on the outer side of the disc shaft; and a first sealing assembly, the first sealing assembly being provided with a third conveying hole, the second conveying channel, the second conveying hole, the third conveying hole and a sealing cavity being sequentially communicated, the present application directly forms a conveying path through the first conveying hole, the second conveying channel, the second conveying hole and the third conveying hole in the form of an opening, the airflow inside the turbine shaft can be directly introduced into the sealing cavity, the airflow flow rate flowing into the sealing cavity can be adjusted by adjusting the flow area of the first conveying hole, the second conveying hole and the third conveying hole, and the airflow flow rate of the sealing cavity can be adjusted in multiple stages.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to sealing structures and aero-engines. Background Technology

[0002] Aero-engines are highly complex and precise thermodynamic machines. When designing the turbine bearing cavity of an aero-engine, to prevent lubricating oil leakage, a high-pressure gas stream is typically drawn from the high-pressure compressor to seal the bearing cavity. During the sealing process, a certain pressure difference exists between the sealing point and the bearing cavity. If the pressure difference is too small, the seal may be unreliable, leading to partial lubricating oil leakage. If the pressure difference is too large, excessive sealing gas may flow into the bearing cavity. Therefore, to ensure the sealing effect of the turbine bearing cavity, the pressure difference between the sealing point and the bearing cavity needs to be controlled within a reasonable range.

[0003] Currently, the existing power turbine bearing cavity is usually located between the power turbine's final stage disk and the outer sealing cover. The sealing method involves setting a first sealing assembly between the sealing cover and the power turbine's final stage disk, forming a sealing cavity between the sealing cover and the first sealing assembly. High-pressure gas is introduced into the sealing cavity by opening vents in the sealing cover and connecting a separate vent pipe to the vents. In this sealing method, the pressure difference between the sealing cavity and the bearing cavity is usually difficult to adjust effectively, resulting in a problem of not being able to meet the sealing requirements. Summary of the Invention

[0004] In view of this, the present invention provides a sealing structure and an aero-engine to solve the problem that the sealing form of the existing power turbine bearing cavity is difficult to meet the sealing requirements.

[0005] In a first aspect, the present invention provides a sealing structure, comprising: a turbine shaft with a first conveying hole on its outer wall and a first conveying channel for conveying sealing gas inside; a turbine disk, including a disk shaft and a final stage disk, the disk shaft being fixedly sleeved on the outside of the turbine shaft, one end of the disk shaft forming an end point along the axial direction, the disk shaft being fixedly sleeved on the outside of the end point, and a cooling space being formed in the space away from the disk shaft along the axial direction, the space between the inner wall of the end point and the outer wall of the turbine shaft forming a second conveying channel, the disk shaft having a second conveying hole, and the first conveying channel communicating with both the cooling space and the second conveying channel through the first conveying hole; a sealing cover, sleeved on the outside of the disk shaft, and the space between the sealing cover and the disk shaft forming a bearing cavity; a first sealing assembly, the inner wall of the sealing cover being sealed and fitted with the outer wall of the disk shaft through the first sealing assembly, the first sealing assembly having a third conveying hole, the first sealing assembly and the sealing cover fitting together to form a sealing cavity, and the second conveying channel, the second conveying hole, the third conveying hole and the sealing cavity being sequentially connected.

[0006] Beneficial effects: By directly forming a delivery path through the first delivery hole, second delivery channel, and third delivery hole, the airflow inside the turbine shaft can be directly guided into the sealing cavity without the need for separate piping outside the sealing cover. Since the airflow from the first delivery hole simultaneously flows into the cooling space and the second delivery channel, the airflow rate at the second delivery channel can be adjusted by changing the number, position, and size of the first delivery hole. Furthermore, since the airflow in the second delivery channel also flows sequentially through the second and third delivery holes, the flow rate at the second and third delivery holes can also be adjusted by changing their flow patterns. The area can also regulate the airflow into the sealing cavity. In addition, the airflow discharged from the sealing cavity can be adjusted by adjusting the size of the first sealing component, thereby further regulating the pressure of the sealing cavity. Through a simple and effective structure, the function of introducing airflow from the turbine axial sealing cavity is realized. At the same time, multiple adjustment methods can be used to achieve multi-level adjustment of the airflow in the sealing cavity, so that the air pressure in the sealing cavity can be adjusted within a wider range. Therefore, it can also improve the flexibility of pressure difference adjustment between the sealing cavity and the bearing cavity, effectively solving the problem that the sealing form of the existing power turbine bearing cavity is difficult to meet the sealing requirements.

[0007] In one alternative embodiment, the space between the sealing cover and the final stage disk forms an exhaust space, the sealing cavity is located between the bearing cavity and the exhaust space, and the first sealing assembly also has a fourth conveying hole, and the second conveying hole communicates with the exhaust space through the fourth conveying hole.

[0008] Beneficial effects: This type of first sealing assembly can adjust the flow rate of the airflow from the second to the third conveying hole by adjusting the size of the fourth conveying hole. Based on the flow diversion adjustment at the first conveying hole, a second flow diversion adjustment process is added, which further enhances the ability to adjust the airflow entering the sealing cavity and greatly improves the flexibility of pressure adjustment at the sealing cavity.

[0009] In one optional embodiment, the first sealing assembly includes a support portion and two sealing portions. The support portion is sleeved on the outer wall of the disc shaft, and the two sealing portions are located between the outer wall of the support portion and the inner wall of the sealing cover and are spaced apart along the axial direction. The outer wall of the support portion, the side walls of the two sealing portions, and the inner wall of the sealing cover together form a sealing cavity, and the two sealing portions are located between the exhaust space and the bearing cavity.

[0010] Beneficial effects: This type of sealing cavity allows for further adjustment of the air pressure within the sealing cavity by adjusting the size of the sealing part on the side furthest from the bearing cavity. This enables a third-stage flow regulation process, greatly improving the adjustability of the air pressure within the sealing cavity.

[0011] In one optional embodiment, the support portion has a flow-diverting cavity inside, a third conveying hole is opened on the outer peripheral surface of the support portion, a fourth conveying hole is opened on the end face of the support portion away from the bearing cavity, and the second conveying hole is connected to both the third and fourth conveying holes through the flow-diverting cavity.

[0012] Beneficial effects: This type of support is easier to process and manufacture, and has stronger bending resistance. In addition, the diversion cavity can buffer the airflow entering through the second conveying hole, and then discharge it through the third and fourth conveying holes, which can improve the uniformity of the airflow discharged from the third and fourth conveying holes.

[0013] In one alternative embodiment, the support has an annular groove with an opening facing the disc shaft, and the support forms a flow-dividing cavity by the annular groove and the outer peripheral surface of the disc shaft.

[0014] Beneficial effects: This type of flow divider structure is simpler and more reliable, and the annular groove is easy to process and manufacture.

[0015] In one optional embodiment, the sealing structure further includes a second sealing assembly, which is disposed between the sealing cover and the final stage disk and located in the exhaust space. The space between the second sealing assembly and the first sealing assembly in the exhaust space forms a first exhaust chamber, and the space on the other side of the second sealing assembly in the exhaust space forms a second exhaust chamber.

[0016] Beneficial effects: The second sealing component blocks the airflow from the first exhaust chamber to the second exhaust chamber, increases the pressure in the first exhaust chamber, and prevents excessive airflow from the diversion chamber from flowing into the exhaust space.

[0017] In one alternative embodiment, the axial extension of the second conveying hole intersects the radial extension of the disc shaft, the axial extension of the fourth conveying hole intersects the axis of the support, and the third conveying hole extends radially along the support; and / or, the number of first conveying holes is multiple and they are circumferentially spaced along the outer wall of the turbine shaft, and the first conveying hole is a strip-shaped hole extending axially.

[0018] Beneficial effects: The obliquely arranged second and fourth conveying holes can increase the heat exchange area between the airflow and the hole walls of the second and fourth conveying holes, thereby improving the cooling effect of the airflow. In addition, this type of first conveying hole has a smaller impact on the pressure of the airflow discharged in the first conveying channel and also has a smaller impact on the structural strength of the turbine shaft.

[0019] In one optional embodiment, the pressure difference between the sealing cavity and the bearing cavity is greater than 3.5 kPa, the ratio of the cross-sectional area of ​​the second conveying hole to the cross-sectional area of ​​the third conveying hole is in the range of 0.87 to 0.88, the ratio of the cross-sectional area of ​​the fourth conveying hole to the cross-sectional area of ​​the third conveying hole is in the range of 0.093 to 0.095, and the ratio of the flow rate of the second conveying hole to the flow rate of the third conveying hole is in the range of 0.3 to 0.8.

[0020] Beneficial effect: The conveying hole under this ratio can achieve efficient sealing.

[0021] In one optional embodiment, the inner wall of the disc shaft is provided with an annular groove with an opening facing the turbine shaft, and the second delivery hole is provided on the inner wall of the annular groove away from the turbine shaft. The space inside the annular groove forms a connecting cavity, and the second delivery channel communicates with the second delivery hole through the connecting cavity. The ratio of the pressure at the connecting cavity to the pressure at the second exhaust cavity ranges from 2.8 to 3.2, and the ratio of the pressure at the connecting cavity to the pressure at the bearing cavity ranges from 1.8 to 2.2.

[0022] Beneficial effects: The structure is simple and reliable, and the connecting cavity can buffer the airflow flowing out of the second conveying channel.

[0023] Secondly, the present invention also provides an aircraft engine comprising the aforementioned sealing structure. Attached Figure Description

[0024] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the arrangement of a sealing structure in a cut-off state according to an embodiment of the present invention;

[0026] Figure 2 for Figure 1 A schematic diagram of the airflow path of the sealing structure is shown.

[0027] Explanation of reference numerals in the attached figures:

[0028] 1. Turbine shaft; 101. Conveying hole; 102. First conveying channel;

[0029] 2. Turbine disk; 201. Disk shaft; 202. Final stage disk; 203. Cooling space; 204. Second conveying channel; 205. Second conveying hole; 206. Connecting cavity;

[0030] 3. Sealing cover; 301. Bearing cavity;

[0031] 4. First sealing assembly; 401. Third conveying hole; 402. Sealing cavity; 403. Exhaust space; 4031. First exhaust cavity; 4032. Second exhaust cavity; 404. Fourth conveying hole; 405. Support part; 406. Sealing part; 407. Diversion cavity;

[0032] 5. Second sealing component. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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, 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.

[0034] The following is combined Figures 1 to 2 The following describes embodiments of the present invention.

[0035] In related technologies, due to the limited space between the sealing cover and the final stage disk of the power turbine, the selectable size of the first sealing assembly is also limited. The pressure at the sealing cavity can only be adjusted by changing the size of the first sealing assembly. With the limited selectable size of the first sealing assembly, the adjustable range of the pressure difference between the sealing cavity and the bearing cavity is limited to a small range. This makes it difficult to flexibly and effectively adjust the pressure difference to the required range, and thus it is difficult to match the needs of the engine operating at different speeds. The pressure difference is often too large or too small, making it difficult to carry out the design work of the aero-engine.

[0036] According to an embodiment of the present invention, a sealing structure is provided, comprising: a turbine shaft 1, a turbine disk 2, a sealing cover 3, and a first sealing assembly 4. The turbine shaft 1 has a first conveying hole 101 on its outer wall and a first conveying channel 102 for conveying sealing gas inside. The turbine disk 2 includes a disk shaft 201 and a final stage disk 202. The disk shaft 201 is fixedly sleeved on the outside of the turbine shaft 1, with one axial end of the disk shaft 201 forming an end point. The disk shaft 201 is fixedly sleeved on the outside of the end point, and a cooling space 203 is formed in the space axially away from the side of the disk shaft 201. The space between the inner wall of the end point and the outer wall of the turbine shaft 1 forms a second conveying channel. 204. A second conveying hole 205 is provided on the disc shaft 201. The first conveying channel 102 is connected to the cooling space 203 and the second conveying channel 204 through the first conveying hole 101. The sealing cover 3 is sleeved on the outside of the disc shaft 201, and the space between the sealing cover 3 and the disc shaft 201 forms a bearing cavity 301. The inner wall of the sealing cover 3 is sealed to the outer wall of the disc shaft 201 through the first sealing assembly 4. The first sealing assembly 4 has a third conveying hole 401. The first sealing assembly 4 and the sealing cover 3 cooperate to form a sealing cavity 402. The second conveying channel 204, the second conveying hole 205, the third conveying hole 401 and the sealing cavity 402 are connected in sequence.

[0037] Using the sealing structure of this embodiment, a conveying path is directly formed through the first conveying hole 101, the second conveying channel 204, the second conveying hole 205, and the third conveying hole 401. This allows for direct airflow from inside the turbine shaft 1 to the sealing cavity 402 without the need for a separate pipeline outside the sealing cover 3. Since the airflow from the first conveying hole 101 simultaneously flows into the cooling space 203 and the second conveying channel 204, the airflow rate at the second conveying channel 204 can be adjusted by changing the number, position, and size of the first conveying holes 101. Furthermore, since the airflow in the second conveying channel 204 also flows sequentially through the second conveying hole 205 and the third conveying hole 401, the airflow rate can also be adjusted by changing the number, position, and size of the first conveying holes 101. The flow area of ​​205 and the third conveying hole 401 can also adjust the airflow rate into the sealing cavity 402. In addition, the flow rate of the airflow discharged from the sealing cavity 402 can be adjusted by adjusting the size of the first sealing component 4, so as to further adjust the pressure of the sealing cavity 402. Through a simple and effective structure, the function of introducing airflow from the turbine shaft 1 into the sealing cavity 402 is realized. At the same time, multiple adjustment methods can be used to realize multi-level adjustment of the airflow rate in the sealing cavity 402, so that the air pressure in the sealing cavity 402 can be adjusted within a wider range. Therefore, the flexibility of the pressure difference adjustment between the sealing cavity 402 and the sealing cavity can be improved, effectively solving the problem that the sealing form of the existing power turbine bearing cavity is difficult to meet the sealing requirements.

[0038] It should be noted that the bearing cavity 301 formed between the sealing cover 3 and the disc shaft 201 is the bearing cavity, and the first sealing component 4 is the sealing component used to seal the opening of the bearing cavity 301; the final stage disc 202 is the disc body located at the axial end of the turbine disc 2, and the final stage disc 202 and the disc shaft 201 are an integral component; the cooling space 203 is not a completely open or completely closed space, the power turbine also has a first stage disc, the cooling space 203 is the space between the final stage disc 202 and the first stage disc, and there is another sealing structure at the end of the cooling space 203. The airflow entering the cooling space 203 will move along the gap between the final stage disc 202 and the first stage disc, and a reliable seal will be formed at the sealing structure here. Excess airflow will enter the mainstream combustion gas through the sealing structure flowing into this location.

[0039] Specifically, such as Figure 2 As shown, when the airflow inside the turbine shaft 1 flows out through the first conveying hole 101, part of it enters the second conveying channel 204, while the other part moves radially along the surface of the final stage disk 202, thereby regulating the gas flow rate entering the second conveying channel 204. At the same time, the airflow that does not enter the second conveying channel 204 can also exchange heat with the final stage disk 202 to cool the final stage disk 202, thus playing a cooling role.

[0040] In one possible implementation, the space between the sealing cover 3 and the final stage disk 202 forms an exhaust space 403. The sealing cavity 402 is located between the bearing cavity 301 and the exhaust space 403. The first sealing assembly 4 also has a fourth conveying hole 404. The second conveying hole 205 communicates with the exhaust space 403 through the fourth conveying hole 404. In this form of the first sealing assembly 4, the second conveying hole 205 is simultaneously connected to the third conveying hole 401 and the fourth conveying hole 404. A portion of the airflow flowing through the second conveying hole 205 can enter the exhaust space 403 through the fourth conveying hole 404. By adjusting the size of the fourth conveying hole 404, the flow rate of the airflow delivered from the second conveying hole 205 to the third conveying hole 401 can be adjusted. Based on the flow diversion adjustment at the first conveying hole 101, a second flow diversion adjustment process is added, further improving the ability to adjust the airflow entering the sealing cavity 402 and greatly improving the flexibility of pressure adjustment at the sealing cavity 402.

[0041] The specific diameter and number of the second conveying hole 205, the third conveying hole 401 and the fourth conveying hole 404 are not limited. The second conveying hole 205, the third conveying hole 401 and the fourth conveying hole 404 are all multiple and are arranged at intervals along the circumference. The specific diameter and number can be determined according to the air system flow calculation results during the design. It will not be elaborated on here.

[0042] In one possible implementation, such as Figure 1As shown, the first sealing assembly 4 includes a support portion 405 and two sealing portions 406. The support portion 405 is sleeved on the outer wall of the disc shaft 201. The two sealing portions 406 are located between the outer wall of the support portion 405 and the inner wall of the sealing cover 3 and are spaced apart along the axial direction. The outer wall of the support portion 405, the side walls of the two sealing portions 406, and the sealing cover 3 form a sealing cavity 402. The two sealing portions 406 are located between the exhaust space 403 and the bearing cavity 301. This type of sealing cavity 402... The airflow in section 2 cooperates with the sealing part 406 on the side near the bearing cavity 301 to form an air curtain, so as to effectively seal the bearing cavity 301. The airflow in the sealing cavity 402 can enter the exhaust space 403 through the sealing part 406 on the side away from the bearing cavity 301. By adjusting the size of the sealing part 406 on the side away from the bearing cavity 301, the air pressure in the sealing cavity 402 can be further adjusted. Here, a third flow diversion adjustment process can be performed, which greatly improves the adjustability of the air pressure in the sealing cavity 402.

[0043] Specifically, there is no limitation on the specific type of the two sealing parts 406. They can be graphite sealing structures or toothed sealing structures, and can be flexibly selected according to the requirements.

[0044] Furthermore, the first delivery hole 101, the second delivery hole 205, the third delivery hole 401, and the fourth delivery hole 404 are all throttling holes. The sealing structure of this application does not rely entirely on graphite sealing and toothed sealing to control the sealing flow. Instead, it cleverly controls the flow of each branch through multiple throttling holes, achieving efficient sealing while allowing for more flexible adjustment of the air pressure in the sealing cavity 402. In particular, the fourth delivery hole 404 can introduce more airflow into the exhaust space 403 to cool the other side of the final stage disk 202, achieving simultaneous cooling of both sides of the final stage disk 202. This avoids excessive airflow flowing into the bearing cavity 301, which could cause excessive sealing flow in the bearing cavity of the power turbine and lead to lubricating oil overheating.

[0045] If, during the test run, a fault such as oil leakage or overheating is found in the sealing of the power turbine bearing cavity, it is only necessary to rework the structure of each throttling orifice, increase the number of holes or seal some of the throttling orifices, and adjust the flow distribution of each branch to achieve rapid test verification of the relevant improvement measures.

[0046] In one possible implementation, the support portion 405 has a flow-diverting cavity 407 inside, a third conveying hole 401 is opened on the outer peripheral surface of the support portion 405, and a fourth conveying hole 404 is opened on the end face of the support portion 405 away from the bearing cavity 301. The second conveying hole 205 is connected to both the third conveying hole 401 and the fourth conveying hole 404 through the flow-diverting cavity 407. This type of support portion 405 is easier to process and manufacture, and also has stronger bending resistance. In addition, the flow-diverting cavity 407 can buffer the airflow entering through the second conveying hole 205, and then discharge it through the third conveying hole 401 and the fourth conveying hole 404, which can improve the uniformity of the airflow discharged from the third conveying hole 401 and the fourth conveying hole 404.

[0047] Specifically, the form of the diversion cavity 407 is not limited. It can be a cavity formed by the inner wall of the support part 405, or it can be a cavity formed by the support part 405 and the adjacent component.

[0048] In one possible implementation, the support portion 405 has an annular groove with an opening facing the disc shaft 201. The support portion 405 forms a flow divider cavity 407 by the annular groove and the outer peripheral surface of the disc shaft 201. This type of flow divider cavity 407 has a simpler and more reliable structure, and the annular groove is easy to process and manufacture.

[0049] Specifically, there are no restrictions on the shape of the inner wall of the annular groove. It can be a continuous curved surface or a wall formed by a combination of planes and curved surfaces. The choice can be made flexibly according to the usage requirements.

[0050] In one possible implementation, the sealing structure further includes a second sealing component 5, which is disposed between the sealing cover 3 and the final stage disk 202 and located in the exhaust space 403. The space in the exhaust space 403 between the second sealing component 5 and the first sealing component 4 forms a first exhaust chamber 4031, and the space in the exhaust space 403 on the other side of the second sealing component 5 forms a second exhaust chamber 4032. The second sealing component 5 blocks the airflow from the first exhaust chamber 4031 to the second exhaust chamber 4032, increases the pressure in the first exhaust chamber 4031, and prevents excessive airflow from the diversion chamber 407 from flowing into the exhaust space 403.

[0051] The airflow entering the second exhaust chamber 4032 will flow into the main combustion passage of the engine and be used to seal the rear stage space of the final stage plate 202.

[0052] Specifically, the sealing part 406 and the second sealing component 5 are either graphite seals or toothed seals.

[0053] Preferably, the second sealing component 5 is a toothed sealing structure, and the sealing part 406 is a graphite sealing structure.

[0054] In one possible implementation, the axial extension of the second conveying hole 205 intersects the radial extension of the disc shaft 201, the axial extension of the fourth conveying hole 404 intersects the axis of the support portion 405, and the third conveying hole 401 extends radially along the support portion 405. This oblique arrangement of the second conveying hole 205 and the fourth conveying hole 404 can increase the heat exchange area between the airflow and the hole walls of the second conveying hole 205 and the fourth conveying hole 404, thereby improving the cooling effect of the airflow.

[0055] It is understood that, as an alternative implementation, the axial extension line of the second conveying hole 205 is parallel to the radial extension line of the disc shaft 201, and the axial extension line of the fourth conveying hole 404 is parallel to the axis of the support portion 405.

[0056] In one possible implementation, there are multiple first delivery holes 101 and they are spaced apart circumferentially along the outer wall of the turbine shaft 1. The first delivery hole 101 is a strip-shaped hole extending axially. This type of first delivery hole 101 has a smaller impact on the pressure of the airflow discharged in the first delivery channel 102 and also has a smaller impact on the structural strength of the turbine shaft 1.

[0057] It is understood that, as an alternative implementation, the first conveying hole 101 can also be a circular hole or a hole of other shapes, which can be flexibly selected according to the needs.

[0058] In one possible implementation, the pressure difference between the sealing cavity 402 and the bearing cavity 301 is greater than 3.5 kPa, the ratio of the cross-sectional area of ​​the second conveying hole 205 to the cross-sectional area of ​​the third conveying hole 401 is in the range of 0.87 to 0.88, the ratio of the cross-sectional area of ​​the fourth conveying hole 404 to the cross-sectional area of ​​the third conveying hole 401 is in the range of 0.093 to 0.095, and the ratio of the flow rate of the second conveying hole 205 to the flow rate of the third conveying hole 401 is in the range of 0.3 to 0.8. The conveying holes under this ratio can achieve efficient sealing.

[0059] It should be noted that the cross-sectional area is the flow area of ​​the hole.

[0060] Preferably, the ratio of the cross-sectional areas of the second conveying hole 205, the third conveying hole 401, and the fourth conveying hole 404 is 56:64:6; the flow rate of the second conveying hole 205 is equal to the sum of the flow rates of the third conveying hole 401 and the fourth conveying hole 404, the flow rate of the second conveying hole 205 is less than the flow rate of the third conveying hole 401, and the ratio of the flow rate of the second conveying hole 205 to the flow rate of the third conveying hole 401 is 6:9.

[0061] Furthermore, the above ratio is the ratio when the number of the second conveying hole 205, the third conveying hole 401, and the fourth conveying hole 404 is the same, or the above ratio is the ratio of the total number of the second conveying hole 205, the third conveying hole 401, and the fourth conveying hole 404.

[0062] In one possible implementation, the inner wall of the disc shaft 201 has an annular groove with an opening facing the turbine shaft 1. The second conveying hole 205 is opened on the inner wall of the annular groove away from the turbine shaft 1. The space inside the annular groove forms a connecting cavity 206. The second conveying channel 204 communicates with the second conveying hole 205 through the connecting cavity 206. The ratio of the pressure at the connecting cavity 206 to the pressure at the second exhaust cavity 4032 is in the range of 2.8 to 3.2. The ratio of the pressure at the connecting cavity 206 to the pressure at the bearing cavity 301 is in the range of 1.8 to 2.2. The structure is simple and reliable. The connecting cavity 206 can buffer the airflow flowing out of the second conveying channel 204.

[0063] Preferably, the pressure ratio at the connecting cavity 206 to the pressure at the second exhaust cavity 4032 is 3, and the pressure ratio at the connecting cavity 206 to the pressure at the bearing cavity 301 is 2.

[0064] In particular, when the engine is in an emergency, the pressure at the connecting cavity 206 is greater than twice the pressure at the bearing cavity 301.

[0065] According to an embodiment of the present invention, in another aspect, an aircraft engine is provided, which includes the sealing structure described above.

[0066] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A sealing structure, characterized in that, include: The turbine shaft (1) has a first conveying hole (101) on its outer wall and a first conveying channel (102) for conveying sealing gas inside. The turbine disk (2) includes a disk shaft (201) and a final stage disk (202). The disk shaft (201) is fixedly sleeved on the outside of the turbine shaft (1). One end of the disk shaft (201) along the axial direction forms an end. The disk shaft (201) is fixedly sleeved on the outside of the end. A cooling space (203) is formed in the space away from the disk shaft (201) along the axial direction. The space between the inner wall of the end and the outer wall of the turbine shaft (1) forms a second conveying channel (204). A second conveying hole (205) is provided on the disk shaft (201). The first conveying channel (102) communicates with the cooling space (203) and the second conveying channel (204) through the first conveying hole (101). A sealing cover (3) is fitted on the outside of the disc shaft (201), and the space between the cover and the disc shaft (201) forms a bearing cavity (301); The first sealing assembly (4) is used to seal the inner wall of the sealing cover (3) with the outer wall of the disc shaft (201). The first sealing assembly (4) has a third conveying hole (401). The first sealing assembly (4) and the sealing cover (3) cooperate to form a sealing cavity (402). The second conveying channel (204), the second conveying hole (205), the third conveying hole (401) and the sealing cavity (402) are connected in sequence.

2. The sealing structure according to claim 1, characterized in that, The space between the sealing cover (3) and the final stage disk (202) forms an exhaust space (403). The sealing cavity (402) is located between the bearing cavity (301) and the exhaust space (403). The first sealing assembly (4) also has a fourth conveying hole (404). The second conveying hole (205) communicates with the exhaust space (403) through the fourth conveying hole (404).

3. The sealing structure according to claim 2, characterized in that, The first sealing assembly (4) includes a support part (405) and two sealing parts (406). The support part (405) is sleeved on the outer wall of the disc shaft (201). The two sealing parts (406) are located between the outer wall of the support part (405) and the inner wall of the sealing cover (3) and are spaced apart along the axial direction. The outer wall of the support part (405), the side walls of the two sealing parts (406) and the inner wall of the sealing cover (3) together form the sealing cavity (402). The two sealing parts (406) are located between the exhaust space (403) and the bearing cavity (301).

4. The sealing structure according to claim 3, characterized in that, The support portion (405) has a flow divider cavity (407) inside. The third conveying hole (401) is opened on the outer peripheral surface of the support portion (405). The fourth conveying hole (404) is opened on the end face of the support portion (405) away from the bearing cavity (301). The second conveying hole (205) communicates with both the third conveying hole (401) and the fourth conveying hole (404) through the flow divider cavity (407).

5. The sealing structure according to claim 4, characterized in that, The support (405) has an annular groove with an opening facing the disc shaft (201), and the support (405) and the outer peripheral surface of the disc shaft (201) enclose the flow divider cavity (407) through the annular groove.

6. The sealing structure according to any one of claims 2 to 5, characterized in that, The sealing structure further includes a second sealing component (5), which is disposed between the sealing cover (3) and the final stage disk (202) and located in the exhaust space (403). The space between the second sealing component (5) and the first sealing component (4) in the exhaust space (403) forms a first exhaust chamber (4031), and the space on the other side of the exhaust space (403) forms a second exhaust chamber (4032).

7. The sealing structure according to any one of claims 3 to 5, characterized in that, The axial extension of the second conveying hole (205) intersects the radial extension of the disc shaft (201), the axial extension of the fourth conveying hole (404) intersects the axis of the support (405), and the third conveying hole (401) extends radially along the support (405). And / or, the number of the first delivery holes (101) is multiple and they are circumferentially spaced along the outer wall of the turbine shaft (1), and the first delivery holes (101) are strip-shaped holes extending along the axial direction.

8. The sealing structure according to any one of claims 2 to 5, characterized in that, The pressure difference between the sealing cavity (402) and the bearing cavity (301) is greater than 3.5 kPa. The ratio of the cross-sectional area of ​​the second conveying hole (205) to the cross-sectional area of ​​the third conveying hole (401) is between 0.87 and 0.

88. The ratio of the cross-sectional area of ​​the fourth conveying hole (404) to the cross-sectional area of ​​the third conveying hole (401) is between 0.093 and 0.

095. The ratio of the flow rate of the second conveying hole (205) to the flow rate of the third conveying hole (401) is between 0.3 and 0.

8.

9. The sealing structure according to claim 6, characterized in that, The inner wall of the disc shaft (201) is provided with an annular groove that opens toward the turbine shaft (1). The second conveying hole (205) is opened in the inner wall of the annular groove away from the turbine shaft (1). The space inside the annular groove forms a connecting cavity (206). The second conveying channel (204) communicates with the second conveying hole (205) through the connecting cavity (206). The ratio of the pressure at the connecting cavity (206) to the pressure at the second exhaust cavity (4032) is in the range of 2.8 to 3.

2. The ratio of the pressure at the connecting cavity (206) to the pressure at the bearing cavity (301) is in the range of 1.8 to 2.

2.

10. An aircraft engine, characterized in that, include: The sealing structure according to any one of claims 1 to 9.

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