End face sealing device for aero-engine

Abstract

The utility model discloses an end face sealing device for an aero-engine, which comprises a movable ring, a sealing ring and a sealing ring, the static ring seat is arranged on the end cover in an axial moving manner; the static ring is arranged on the static ring seat in an axial moving manner; the self-balancing spring assembly is used for pushing the static ring to abut against the movable ring; the self-balancing spring assembly is provided with a first spring arranged between the static ring seat and the static ring and a second spring arranged between the static ring seat and the end cover. The self-balancing spring assembly is arranged, the second spring and the first spring are arranged on the left side and the right side of the static ring base correspondingly, and dynamic balance of the two springs can be achieved. When the rotating shaft has axial movement, the movable ring moves along with the rotating shaft, and the static ring abuts against the movable ring under the action of the self-balancing spring assembly. The compression amount of the first spring and the compression amount of the second spring are both changed, so that the compression change amount of the first spring is smaller than the axial movement amount of the rotating shaft, the pressure change between the static ring and the movable ring is reduced, the sealing state of the movable ring and the static ring is kept, and the problem that the sealing end face is excessively pressed and separated due to axial movement can be effectively solved.

Description

Technical Field

[0001] The invention belongs to the technical field of end face sealing, and in particular relates to an end face sealing device for an aero-engine. Background Art

[0002] In the aviation field, the shaft end dynamic sealing devices of aircraft engine accessory systems, transmission systems, fuel pumps and other mechanisms are key basic components for maintaining the pressure of lubricating oil or fuel media in the cavity, avoiding media leakage, and ensuring good lubrication of bearings and other components. Mechanical end face seals are an important type of them.

[0003] With the widespread application and development of high-performance aircraft engines, the requirements for their reliability and durability are increasing. This puts higher technical standards on mechanical seals that frequently have problems. At present, aircraft engines generally use traditional contact mechanical seals, which face many challenges: high speeds cause excessive wear of the sealing friction pair, generate a large amount of friction heat, and then aggravate thermal deformation; strong vibrations cause the sealing friction pair to be non-parallel or produce angle deviations, increasing local contact pressure; axial movement causes uneven contact pressure on the sealing surface, causing local overload or underload. These factors have significantly reduced the operating stability and reliability of aircraft engine mechanical seals.

[0004] Therefore, the research on mechanical end face seals for aircraft engines is very necessary. Patent CN202545820U proposes a non-contact mechanical seal with a groove end face with a reflux function. Its main purpose is to open a groove on the seal end face to improve friction performance and reduce wear. However, for aircraft engines with complex operating conditions, changes in operating posture can easily lead to lack of oil lubrication on the seal end face. At this time, the end face groove increases the surface roughness and aggravates the wear of the seal end face.

[0005] At present, there is no research on mechanical end face seals for aircraft engines with high speed, strong vibration and axial movement that has not been fully considered. Therefore, in order to improve the reliability of aircraft engines, it is necessary to design a mechanical end face seal device for aircraft engines.

[0006] The above information disclosed in the background technology is only used to increase the understanding of the background technology of the present application, and therefore, it may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0007] In view of the above problems in the prior art, the utility model proposes an end face sealing device for an aircraft engine, which can effectively solve the problem of excessive compression and separation of the end faces of the dynamic and static rings caused by axial movement by arranging a self-balancing spring assembly.

[0008] In order to achieve the above-mentioned purpose, the present invention adopts the following technical solutions:

[0009] An end face sealing device for an aircraft engine, comprising:

[0010] A moving ring, which is fixed on the shaft sleeve;

[0011] A stationary ring seat, which is axially movable and arranged on the end cover;

[0012] A stationary ring, which is axially movable and arranged on the stationary ring seat;

[0013] A self-balancing spring assembly, which is used to push the stationary ring against the dynamic ring;

[0014] The self-balancing spring assembly comprises a first spring arranged between the stationary ring seat and the stationary ring, and a second spring arranged between the stationary ring seat and the end cover.

[0015] In some embodiments of the present application, the first spring and the second spring are both in a compressed state; when the rotating shaft of the aircraft engine has axial movement, under the action of the self-balancing spring assembly, the stationary ring follows the movement to keep the stationary ring against the dynamic ring.

[0016] In some embodiments of the present application, the elastic coefficient of the first spring is greater than the elastic coefficient of the second spring.

[0017] In some embodiments of the present application, an axial dimension of the first spring is smaller than an axial dimension of the second spring.

[0018] In some embodiments of the present application, a radial dimension of the first spring is smaller than a radial dimension of the second spring.

[0019] In some embodiments of the present application, a first limiting ring extending axially toward the stationary ring is provided on the stationary ring seat, the stationary ring is radially movable on the outside of the first limiting ring, and a stationary ring sealing ring is provided between the stationary ring and the first limiting ring.

[0020] In some embodiments of the present application, a second limiting ring extending axially toward the end cover is provided on the stationary ring seat, the end cover is provided on the outside of the second limiting ring, and an end cover sealing ring is provided between the end cover and the second limiting ring.

[0021] In some embodiments of the present application, a limiting column for limiting the movement range of the stationary ring seat is further included, the second spring is sleeved on the outside of the limiting column, and the limiting column is fixed on the end cover.

[0022] In some embodiments of the present application, a limiting hole for the limiting column to pass through is provided on the stationary ring seat, one end of the limiting column is fixed on the end cover, and the other end is provided with a limiting edge, and the limiting edge is located at the end of the limiting hole away from the end cover.

[0023] In some embodiments of the present application, a first limit pin for limiting radial movement of the stationary ring is provided between the stationary ring and the stationary ring seat, and a second limit pin for limiting axial movement of the stationary ring seat is provided between the stationary ring seat and the end cover.

[0024] Compared with the prior art, the advantages and positive effects of the utility model are: by setting a self-balancing spring assembly, the second spring and the first spring are respectively set on the left and right sides of the static ring seat, so that the dynamic balance of the two springs can be achieved. When the rotating shaft has axial movement, the dynamic ring moves with the rotating shaft, and the static ring abuts against the dynamic ring under the action of the self-balancing spring assembly; the compression amount of the first spring and the second spring both change, so that the compression change of the first spring is less than the axial movement of the rotating shaft, so that the pressure change between the static ring and the dynamic ring is reduced, which is conducive to maintaining the sealing state of the dynamic ring and the static ring, and can effectively solve the problem of excessive compression and separation of the sealing end face caused by axial movement.

[0025] After reading the specific embodiments of the present invention in conjunction with the accompanying drawings, other features and advantages of the present invention will become more clear. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, a brief introduction will be given below to the drawings required for use in the embodiments. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 This is a schematic structural diagram of an embodiment of an end face sealing device for an aircraft engine proposed by the utility model;

[0028] Figure 2 for Figure 1 A magnified schematic diagram of the structure in the middle;

[0029] Among them, the mechanical end face sealing device 100;

[0030] Dynamic ring 10;

[0031] Stationary ring 20; Stationary ring sealing ring 23;

[0032] Bushing 30;

[0033] A first spring 40;

[0034] Stationary ring seat 50; seat body 51; first limiting ring 52; second limiting ring 53; mounting groove 54; first limiting pin 55; second limiting pin 56; limiting hole 57;

[0035] A defining column 60; a defining edge 61;

[0036] A second spring 70;

[0037] Rotating shaft 200;

[0038] End cover 300; end cover sealing ring 310. DETAILED DESCRIPTION

[0039] In order to make the purpose, technical solution and advantages of the embodiments of the present utility model clearer, the technical solution in the embodiments of the present utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the present utility model.

[0040] In the description of the present utility model, it should be noted that the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", etc. are based on the positional relationships shown in the accompanying drawings, with the direction close to the axis of the rotating shaft being "inside" and the opposite being "outside". The terms are only for the convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance; features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0041] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0042] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0043] The disclosure below provides many different embodiments or examples for realizing different structures of the present invention. In order to simplify the disclosure of the present invention, the components and settings of specific examples are described below. Of course, they are merely examples, and the purpose is not to limit the present invention. In addition, the present invention may repeat reference numbers and / or reference letters in different examples, and such repetition is for the purpose of simplification and clarity, and does not itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present invention provides various specific examples of processes and materials, but those of ordinary skill in the art may be aware of the application of other processes and / or the use of other materials.

[0044] See also Figure 1-Figure 2 , is an embodiment of an end face sealing device for an aircraft engine proposed by the utility model, an end face sealing device 100 for an aircraft engine comprises: a dynamic ring 10, a static ring 20, a sleeve 30 and a static ring seat 50, the dynamic ring 10 is fixed on the sleeve 30, and the sleeve 30 is sleeved on the rotating shaft 200. The static ring seat 50 is axially movable on the end cover 300, and the static ring 20 is axially movable on the static ring seat 50; both the static ring seat 50 and the static ring 20 are axially movable, so that the axial adjustable range of the mechanical end face sealing device 100 is increased, which is conducive to coping with the axial movement of the rotating shaft 200.

[0045] In this embodiment, the end face sealing device 100 further includes a self-balancing spring assembly for maintaining the stationary ring 20 against the moving ring 10, and the self-balancing spring assembly includes a first spring 40 axially arranged between the stationary ring seat 50 and the stationary ring 20, and a second spring 70 axially arranged between the stationary ring seat 50 and the end cover 300. By setting the self-balancing spring assembly, the first spring 40 and the second spring 70 are arranged in series in the axial direction, and the second spring 70 and the first spring 40 are respectively arranged on the left and right sides of the stationary ring seat 50, so that the dynamic balance of the two springs can be achieved. When the rotating shaft 200 has axial movement, the moving ring 10 moves with the rotating shaft, and the stationary ring 20 is pressed against the moving ring 10 under the action of the self-balancing spring assembly; the compression amount of the first spring 40 and the second spring 70 both change, so that the compression change amount of the first spring 40 is less than the axial movement amount of the rotating shaft 200. The sum of the compression variation of the first spring 40 and the compression variation of the second spring 70 is equal to the axial movement of the rotating shaft. The pressure variation between the static ring and the dynamic ring is the change of elastic force caused by the compression variation of the first spring 40. Therefore, compared with setting one spring, it is beneficial to reduce the compression variation of the first spring 40, thereby reducing the change of elastic force of the first spring 40, reducing the pressure variation between the static ring 20 and the dynamic ring 10, which is beneficial to maintain the sealing state of the dynamic ring 10 and the static ring 20, and can effectively solve the problem of excessive compression and separation of the sealing end faces caused by axial movement. The first spring 40 and the second spring 70 are set to increase the range of the compression variation, avoiding the situation that the first spring 40 is compressed and stuck when the axial movement of the rotating shaft 200 toward the end cover 300 is large; it also avoids the situation that the compression variation of the spring is insufficient when the axial movement of the rotating shaft 200 away from the end cover 300 is large, resulting in the separation of the dynamic ring 10 and the static ring 20.

[0046] In some embodiments of the present application, the first spring 40 and the second spring 70 are both in a compressed state. When the rotating shaft 200 of the aircraft engine has axial movement, under the action of the self-balancing spring assembly, the stationary ring 20 follows the movement and keeps the stationary ring 20 against the dynamic ring 10. When the rotating shaft 200 moves toward the end cover 300, the dynamic ring 10 pushes the stationary ring 20 to move toward the end cover 300, so that the compression of the first spring 40 increases, and then the pressure is transmitted to the stationary ring seat 50, so that the compression of the second spring 70 increases. When the rotating shaft 200 moves toward the end cover 300, the dynamic ring 10 pushes the stationary ring 20 to move toward the end cover 300, so that the compression of the first spring 40 increases, and then the pressure is transmitted to the stationary ring seat 50, so that the compression of the second spring 70 increases. When the rotating shaft 200 moves away from the end cover 300, the static ring 20 moves with the dynamic ring 10 under the push of the first spring 40 and the second spring 70, and the compression of the first spring 40 and the second spring 70 is reduced. That is, the axial movement of the rotating shaft 200 realizes the change of the compression variation of the first spring 40 and the compression variation of the second spring 70, or the compression variation is distributed to the first spring 40 and the second spring 70.

[0047] In some embodiments of the present application, the stationary ring seat 50 has a seat body 51, a first stop ring 52 extending axially along the seat body 51 toward the stationary ring 20, and the stationary ring 20 is radially movable and arranged outside the first stop ring 52; by setting the first stop ring 52, the installation and sealing of the stationary ring 20 and the axial movement of the stationary ring 20 along the first stop ring 52 are realized. The first stop ring 52 extending radially toward the moving ring 10 is arranged along the inner side of the seat body 51, and a first spring 40 is arranged between the seat body 51 and the stationary ring 20, and the axis of the first spring 40 is arranged parallel to the axis of the rotating shaft 200. A stationary ring sealing ring 23 is arranged between the stationary ring 20 and the first stop ring 52 to maintain the sealing between the stationary ring 20 and the stationary ring seat 50. An installation groove 54 is provided on the stationary ring seat 50 for installing the stationary ring 20, and the installation groove 54 is provided on the seat body 51.

[0048] In some embodiments of the present application, a first limiting pin 55 for limiting the radial movement of the stationary ring 20 is provided between the stationary ring 20 and the stationary ring seat 50. The first limiting pin 55 is arranged parallel to the axis of the rotating shaft 200, and a receiving groove matching the first limiting pin 55 is provided on the stationary ring 20 and the stationary ring seat 50. The first limiting pin 55 is provided to limit the axial movement of the stationary ring 20.

[0049] In some embodiments of the present application, a second limiting ring 53 is provided inside the seat body 51 of the stationary ring seat 50, and the second limiting ring 53 extends axially along the inside of the seat body 51 toward the end cover 300; the end cover 300 is provided outside the second limiting ring 53 to limit the axial movement of the stationary ring seat 50, and is conducive to achieving the seal between the stationary ring seat 50 and the end cover 300. An end cover sealing ring 310 is provided between the end cover 300 and the second limiting ring 53.

[0050] In some embodiments of the present application, a second limiting pin 56 for limiting the axial movement of the stationary ring seat 50 is provided between the stationary ring seat 50 and the end cover 300. The second limiting pin 56 is arranged parallel to the axis of the rotating shaft 200, and a receiving groove matching the second limiting pin 56 is respectively provided on the end cover 300 and the stationary ring seat 50. The second limiting pin 56 is provided to limit the axial movement of the stationary ring seat 50.

[0051] In some embodiments of the present application, the mechanical end face sealing device 100 further includes a limiting column 60 for limiting the moving range of the stationary ring seat 50, and the second spring 70 is sleeved on the outer side of the limiting column 60, and the limiting column 60 is fixed on the end cover 300. By providing the limiting column 60, the movable range of the stationary ring seat 50 in the axial direction is limited, and the separation of the stationary ring seat 50 and the end cover 300 is avoided, which causes the outflow of the sealing medium.

[0052] In some embodiments of the present application, a limiting hole 57 for the limiting column 60 to pass through is provided on the stationary ring seat 50, one end of the limiting column 60 is fixed on the end cover 300, and the other end is provided with a limiting edge 61, and the limiting edge 61 is located at the end of the limiting hole 57 away from the end cover 300. The limiting column 60 passes through the limiting hole 57 from the left side, and then the second spring 70 is sleeved on the limiting column 60, and then the limiting column 60 is fixed on the end cover 300. One end of the second spring 70 is pressed against the end cover 300, and the other end is pressed against the stationary ring seat 50. The length of the second spring 70 after compression is the distance between the seat body 51 and the end cover 300.

[0053] In some embodiments of the present application, if the force applied to the stationary ring seat 50 is analyzed, when the stationary ring seat 50 is in a stationary state, the static friction force applied to the stationary ring seat 50 is ignored, the first spring 40 applies an axial force to the right to the stationary ring seat 50, and the second spring 70 applies an axial force to the left to the stationary ring seat 50. At this time, the elastic force of the first spring 40 is equal to the elastic force of the second spring 70, and the elastic force of the first spring 40 also acts on the stationary ring 20 to the left, and the stationary ring 20 transmits the leftward thrust to the dynamic ring 10. At this time, the pressure between the end faces of the dynamic and static rings is the elastic force of the first spring 40.

[0054] In some embodiments of the present application, it is preferably configured that the elastic coefficient of the first spring 40 is greater than the elastic coefficient of the second spring 70, so that when the rotating shaft 200 has axial movement, most of the axial movement distance is distributed to the second spring 70, the compression change amount of the second spring 70 is large, and the compression change amount of the first spring 40 is small. It is preferably configured that the radial dimension of the first spring 40 is smaller than the radial dimension of the second spring 70; the axial dimension of the first spring 40 is smaller than the axial dimension of the second spring 70.

[0055] When the rotating shaft 200 has axial movement, the dynamic following effect of the stationary ring 20 on the dynamic ring 10 is specifically analyzed as follows:

[0056] The stiffness coefficient of the first spring 40 is set to K A , set the stiffness coefficient of the second spring 70 to K B ; In the stable working state of the end face sealing device 100, the compression amount of the first spring 40 is h A , the compression amount of the second spring 70 is h B , ignoring friction:

[0057] F=K A ·h A =K B ·h B (1)

[0058] ① When the rotating shaft 200 moves to the left, the sleeve 30 and the dynamic ring 10 installed on the rotating shaft 200 also move to the left; at this time, the static ring 20 will move to the left under the push of the first spring 40 and the second spring 70, and the static ring seat 50 will also move to the left under the action of the second spring 70.

[0059] Assuming that the displacement of the dynamic ring 10 to the left is h, and the displacement of the static ring seat 50 to the left is δ (δ<h), the displacement of the static ring 20 to the left is h-δ; that is, the compression change of the second spring 70 is δ, and the compression change of the first spring 40 is h-δ. By axially arranging the first spring 40 and the second spring 70 in series, the axial movement of the rotating shaft 200 is borne by the compression change of the first spring 40 and the compression change of the second spring 70. Compared with the arrangement of one spring, it is beneficial to reduce the compression change of the first spring 40, thereby reducing the change of the elastic force of the first spring 40, reducing the pressure change between the end faces of the dynamic and static rings, and improving the sealing performance of the mechanical end face sealing device 100.

[0060] After the first spring 40 and the second spring 70 finish moving, a new balance is reached; at this time, the elastic force of the first spring 40 is:

[0061] F A =K A ·(hA -h+δ) (2)

[0062] The elastic force of the second spring 70 is:

[0063] F B =K B ·(h B -δ) (3)

[0064] In the new equilibrium state, the elastic force of the first spring 40 and the elastic force of the second spring 70 are still equal, then:

[0065] K A ·(h A -h+δ)=K B ·(h B -δ) (4)

[0066] K A ·h A -K A ·h+K A δ=K B ·h B -K B δ (5)

[0067] Substituting formula (1) into formula (5), we get:

[0068] -K A ·h+K A ·δ=-K B ·δ (6)

[0069]

[0070] It can be seen from formula (7) that the larger the elastic coefficient of the first spring 40 is relative to the elastic coefficient of the second spring 70, the larger the displacement δ of the stationary ring seat 50 to the left, making the displacement h-δ of the stationary ring 20 to the left smaller. When the elastic coefficient of the first spring 40 is infinitely large relative to the elastic coefficient of the second spring 70, δ approaches h, that is, the compression of the first spring 40 approaches no change, so that the elastic force of the first spring 40 acting on the stationary ring 20 to the left approaches no change, and the pressure between the end faces of the dynamic and static rings approaches no change.

[0071] Therefore, it is preferred to set the elastic coefficient of the first spring 40 to be greater than the elastic coefficient of the second spring 70, so that the compression change of the first spring 40 is smaller, and the pressure change between the dynamic ring 10 and the static ring 20 is small, which is beneficial to the end face sealing and reduces the influence of the axial movement of the rotating shaft 200 on the end face sealing.

[0072] ② When the rotating shaft 200 moves to the right, the sleeve 30 and the moving ring 10 installed on the rotating shaft 200 also move to the right, thereby pushing the stationary ring 20 to move to the right, the first spring 40 is further compressed, the first spring 40 pushes the stationary ring seat 50 to move to the right, and the second spring 70 is further compressed.

[0073] Assuming that the rightward movement of the dynamic ring 10 is h, and the rightward displacement of the static ring seat 50 is δ (δ<h), the rightward displacement of the static ring 20 is h-δ; that is, the compression change of the second spring 70 is δ, and the compression change of the first spring 40 is h-δ. By axially arranging the first spring 40 and the second spring 70 in series, the axial movement of the rotating shaft 200 is borne by the compression change of the first spring 40 and the compression change of the second spring 70. Compared with the arrangement of one spring, it is beneficial to reduce the compression change of the first spring 40, thereby reducing the change of the elastic force of the first spring 40, reducing the pressure change between the end faces of the dynamic and static rings, and improving the sealing performance of the mechanical end face sealing device 100.

[0074] After the first spring 40 and the second spring 70 finish moving, a new balance is reached; at this time, the elastic force of the first spring 40 is:

[0075] F A =K A ·(h A +h-δ) (8)

[0076] The elastic force of the second spring 70 is:

[0077] F B =K B ·(h B +δ) (9)

[0078] In the new equilibrium state, the elastic force of the first spring 40 and the elastic force of the second spring 70 are still equal, then:

[0079] K A ·(h A + h-δ) = K B ·(h B +δ) (10)

[0080] K A ·h A +K A ·hK A δ=K B ·h B +K B ·δ (11)

[0081] Substituting formula (1) into formula (11), we get:

[0082] KA ·hK A δ=K B ·δ (12)

[0083]

[0084] It can be seen from formula (13) that, similar to formula (7), the larger the elastic coefficient of the first spring 40 relative to the elastic coefficient of the second spring 70, the larger the displacement δ of the stationary ring seat 50 to the right, making the displacement h-δ of the stationary ring 20 to the right smaller. When the elastic coefficient of the first spring 40 is infinitely large relative to the elastic coefficient of the second spring 70, δ approaches h, that is, the compression of the first spring 40 approaches no change, so that the elastic force of the first spring 40 acting on the stationary ring 20 to the left approaches no change, and the pressure between the end faces of the dynamic and static rings approaches no change.

[0085] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the above embodiments, it is still possible for a person skilled in the art to modify the technical solutions described in the above embodiments, or to replace some of the technical features therein with equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions claimed to be protected by the present invention.

Claims

1. An end face sealing device for an aircraft engine, characterized in that: include: A moving ring, which is fixed on the shaft sleeve; A stationary ring seat, which is axially movable and arranged on the end cover; A stationary ring, which is axially movable and arranged on the stationary ring seat; A self-balancing spring assembly, which is used to push the stationary ring against the dynamic ring; The self-balancing spring assembly comprises a first spring arranged between the stationary ring seat and the stationary ring, and a second spring arranged between the stationary ring seat and the end cover.

2. The end face sealing device according to claim 1, characterized in that: The first spring and the second spring are both in a compressed state; when the rotating shaft of the aircraft engine has axial movement, under the action of the self-balancing spring assembly, the static ring follows the movement to keep the static ring against the dynamic ring.

3. The end face sealing device according to claim 1, characterized in that: The elastic coefficient of the first spring is greater than the elastic coefficient of the second spring.

4. The end face sealing device according to claim 1, characterized in that: An axial dimension of the first spring is smaller than an axial dimension of the second spring, and a radial dimension of the first spring is smaller than a radial dimension of the second spring.

5. The end face sealing device according to any one of claims 1 to 4, characterized in that: A first limiting ring extending axially toward the stationary ring is provided on the stationary ring seat, the stationary ring is radially movably provided outside the first limiting ring, and a stationary ring sealing ring is provided between the stationary ring and the first limiting ring.

6. The end face sealing device according to any one of claims 1 to 4, characterized in that: A second limiting ring extending axially toward the end cover is provided on the stationary ring seat, the end cover is arranged on the outer side of the second limiting ring, and an end cover sealing ring is provided between the end cover and the second limiting ring.

7. The end face sealing device according to any one of claims 1 to 4, characterized in that: It also includes a limiting column for limiting the moving range of the stationary ring seat, the second spring is sleeved on the outside of the limiting column, and the limiting column is fixed on the end cover.

8. The end face sealing device according to claim 7, characterized in that: A limiting hole for the limiting column to pass through is provided on the stationary ring seat. One end of the limiting column is fixed on the end cover, and the other end is provided with a limiting edge. The limiting edge is located at the end of the limiting hole away from the end cover.

9. The end face sealing device according to any one of claims 1 to 4, characterized in that: A first limiting pin for limiting the radial movement of the stationary ring is provided between the stationary ring and the stationary ring seat.

10. The end face sealing device according to any one of claims 1 to 4, characterized in that: A second limiting pin for limiting the axial movement of the stationary ring seat is provided between the stationary ring seat and the end cover.

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