A seal ring assembly

Abstract

The application provides a seal ring assembly, and relates to the technical field of seal connection of an aero-engine. The seal ring assembly comprises a seal ring, the seal ring is fixed relative to a stator, the seal ring has a first section and a second section; the first section extends radially along a rotor, the second section extends axially along the rotor, a third section extends axially along the rotor at the first section, and a clamping groove is defined between the second section and the third section; a damping piece is arranged in the clamping groove, and a radial gap is formed between the damping piece and the second section or the third section. By arranging the damping piece in the seal ring, collision between the damping piece and the seal ring consumes the vibration energy of the seal ring assembly during vibration of the seal ring assembly caused by rotation of the rotor, so that the damping effect is achieved.

Description

Technical Field

[0001] This invention relates to the field of sealing connection technology for aero-engines, and more particularly to a sealing ring assembly. Background Technology

[0002] The combustion chamber is one of the core components of an aero-engine, used to mix high-temperature, high-pressure gases and fuel, and to burn them to achieve the purpose of heating and pressurization. The sealing ring assembly is one of the components of the combustion chamber. Located between the high-pressure rotor and the combustion chamber casing assembly, that is, between the rotor and the stator, its main function is to achieve a seal between the rotor and the stator. Its sealing effect can affect the engine's cavity temperature, cavity pressure, and axial force.

[0003] Because the sealing ring assembly is located between the rotor and the stator, it directly rubs against the rotor when the rotor rotates, causing vibration. Furthermore, the rotor's rotation stirs up the surrounding air, which also contributes to the vibration of the sealing ring assembly. If the sealing ring assembly vibrates severely, the rubbing between it and the rotor intensifies, leading to a decrease or even failure of the seal between the rotor and the stator. This results in abnormal engine chamber temperature, pressure, and axial force, affecting engine performance and potentially causing safety issues. Summary of the Invention

[0004] The purpose of this invention is at least to provide a sealing ring assembly that can reduce its own vibration when affected by rotor rotation, and ensure the sealing effect of its own structure between the rotor and the stator.

[0005] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0006] One embodiment of the present invention provides a sealing ring assembly, the sealing ring assembly includes a sealing ring, the sealing ring is fixed relative to the stator, the sealing ring has a first segment and a second segment; the first segment extends radially along the rotor, the second segment extends axially along the rotor, a third segment extends axially from the first segment, and a groove is defined between the second segment and the third segment; a vibration damping element is provided in the groove, and there is a radial gap between the vibration damping element and the second segment or the third segment.

[0007] In some embodiments, there is an axial gap between the damper and the first segment.

[0008] In some embodiments, the damper is made of a flexible sheet material.

[0009] In some embodiments, the first and third segments are fixedly mounted to the stator housing, and the second segment is a free segment; the damper has a free end and a fixed end, the fixed end is connected and fixed to the second segment, the free end is located in the third segment, and there is a continuous bending structure between the fixed end and the free end that extends close to the inner wall of the slot.

[0010] In some embodiments, the first and third segments are engaged with the protruding structure inside the stator casing.

[0011] In some embodiments, the second segment is fixedly mounted to the stator casing, and the first and third segments are free segments; the damper has a free end and a fixed end, the fixed end is fixedly connected to the third segment, the free end is located in the second segment, and there is a continuous bending structure between the fixed end and the free end that extends close to the inner wall of the slot.

[0012] In some embodiments, the continuous bending structure includes a wave segment having a fulcrum structure that protrudes radially toward a second or third segment of the rotor and abuts against the second or third segment.

[0013] In some embodiments, the sealing ring is an annular structure, the sealing ring is arranged axially around the rotor, and an annular groove is defined between the second and third segments of the sealing ring; the vibration damper is an annular structure, the vibration damper is arranged axially around the rotor, and is disposed in the annular groove.

[0014] In some embodiments, the sealing ring is an annular structure, the sealing ring is arranged around the rotor axial direction, and an annular groove is defined between the second and third segments of the sealing ring; the vibration damping element includes a plurality of vibration damping elements, the plurality of vibration damping elements are disposed in the annular groove, and the plurality of vibration damping elements are spaced apart in the circumferential direction around the rotor axial direction.

[0015] In some embodiments, the sealing ring assembly includes a honeycomb ring, which is an annular structure. The sealing ring and the honeycomb ring are arranged axially around the rotor. The honeycomb ring is disposed on the outer side of the second section away from the slot, and the honeycomb ring cooperates with the sealing grates provided on the rotor to achieve sealing.

[0016] The sealing ring assembly of this invention includes a vibration damping element within the sealing ring. During the vibration of the sealing ring assembly due to rotor rotation, the vibration damping element collides with the sealing ring, dissipating the vibration energy of the sealing ring assembly and achieving a vibration reduction effect. A radial gap is provided between the vibration damping element and the second or third section of the sealing ring to ensure radial vibration space for the vibration damping element and prevent vibrations caused by the vibration damping element dissipating the vibration energy of the sealing ring assembly from causing vibrations in the sealing ring in the opposite direction. Attached Figure Description

[0017] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related properties or features may have the same or similar reference numerals. Wherein:

[0018] Figure 1 This is a structural schematic diagram of an aero engine based on some embodiments;

[0019] Figure 2 This is an installation diagram of the sealing ring assembly according to some embodiments;

[0020] Figure 3 This is a structural schematic diagram of a sealing ring assembly according to some embodiments. Detailed Implementation

[0021] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0022] It should be understood that the terms “system,” “device,” “unit,” and / or “module” used herein are a method of distinguishing different components, elements, segments, sub-units, or assemblies at different levels. However, if other terms can achieve the same purpose, they may be replaced by other expressions.

[0023] It is understood that the technical terms that may be used in the description of this specification, such as “center,” “longitudinal,” “lateral,” “front,” “rear,” “left,” “right,” “vertical,” “horizontal,” “top,” “bottom,” “inner,” and “outer,” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the implementation method and do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of the invention.

[0024] It should be noted that the use of terms such as "first" and "second" to define features in this article is merely for the purpose of distinguishing the corresponding features. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0025] This specification provides an embodiment of a sealing ring assembly, which is disposed between the stator and the rotor to achieve a seal between the stator and the rotor. In an aero-engine, the stator can refer to the compressor, combustion chamber, etc., and the rotor can refer to the high-pressure rotor, etc.

[0026] Figure 1This is a structural schematic diagram of an aircraft engine based on some embodiments. For example... Figure 1 As shown, the aero-engine includes an inlet 1, a fan 2, a planetary gearbox 3, a low-pressure compressor 4, a high-pressure compressor 5, a combustion chamber 6, a high-pressure turbine 7, a low-pressure turbine 8, a low-speed shaft 9, and a high-pressure rotor 10. During engine operation, the atmospheric airflow 11 entering through the inlet 1 is split into an outer bypass airflow 12 and an inner bypass airflow 13 after the fan 2. The inner bypass airflow 13 flows in the inner bypass channel formed between the high-pressure rotor 10 and the stators, including the high-pressure compressor 5, combustion chamber 6, high-pressure turbine 7, and low-pressure turbine 8. A sealing ring assembly is installed between the rotor and the stators. For example, a sealing ring assembly is installed between the high-pressure rotor 10 and the combustion chamber 6. When the high-pressure rotor 10 rotates relative to the combustion chamber 6 around the engine axis 14, the sealing ring assembly achieves interstage sealing between the high-pressure rotor 10 and the combustion chamber 6. It should be noted that... Figure 1 The structure of the aircraft engine shown is only one example of an aircraft engine structure.

[0027] Figure 2 This is an installation diagram of the sealing ring assembly according to some embodiments. It should be noted that... Figure 2 The diagram shows the installation of the sealing ring assembly between the combustion chamber 6 and the high-pressure rotor 10. This is only an example of the installation of the sealing ring assembly between the stator and the rotor and is not intended to limit the application of the sealing ring assembly.

[0028] like Figure 2 As shown, the sealing ring assembly 100 is disposed on the stator casing 61 (e.g., combustion chamber casing), and the sealing ring assembly 100 is fixed relative to the stator. The sealing ring assembly 100 cooperates with the rotor 10 (e.g., high-pressure rotor) to form a sealing effect, which hinders the airflow between the first air chamber 102 and the second air chamber 103, thereby preventing the temperature and pressure in the first air chamber 102 and the second air chamber 103 from affecting each other, and even affecting the axial force of the engine.

[0029] See Figure 2 The sealing ring assembly 100 includes a sealing ring 110 and a honeycomb ring 120.

[0030] The sealing ring 110 has a ring-shaped structure and is arranged axially around the rotor. In some embodiments, the sealing ring 110 is fixedly mounted on the stator housing 61. In some embodiments, the sealing ring 110 is bolted to the stator housing 61. The rotor axial direction referred to in this specification means the direction along the axis of rotor rotation, and also the direction along the engine axis (e.g., engine axis 14). The sealing ring 110 provides a mounting bracket for the honeycomb ring 120.

[0031] The honeycomb ring 120 has a ring-shaped structure and is arranged axially around the rotor. In some embodiments, the honeycomb ring 120 is sleeved on the outside of the sealing ring 110, so that the honeycomb ring 120 is fixed relative to the stator. In some embodiments, the honeycomb ring 120 is sleeved on the outside of the sealing ring 110, directly opposite the sealing grating 101, and the honeycomb ring 120 cooperates with the sealing grating 101 provided on the rotor 10 to achieve interstage sealing.

[0032] When the rotor 10 rotates, the honeycomb ring 120 and the sealing grates 101 on the rotor 10 generate sliding friction. The force transmitted by the sealing grates 101 causes the honeycomb ring 120 and even the sealing ring assembly 100 to vibrate. The rotation of the rotor 10 will drive the surrounding air to stir, and the stirred air will further aggravate the vibration of the sealing ring assembly 100. When the vibration amplitude of the sealing ring assembly 100 is too large, the honeycomb ring 120 will correspondingly generate a large amplitude vibration, resulting in severe rubbing between the honeycomb ring 120 and the sealing grates 101. This will lead to a reduction or even failure of the seal between the rotor 10 and the sealing ring assembly 100, resulting in abnormal engine cavity temperature, cavity pressure and axial force, affecting engine performance, and may even cause safety problems.

[0033] In some embodiments, to mitigate vibration of the sealing ring assembly 100, the sealing ring assembly 100 further includes a vibration damper 130. The vibration damper 130 is disposed between the honeycomb ring 120 and the stator housing 61 to mitigate vibration of the sealing ring assembly 100 caused by the rotation of the rotor 10.

[0034] Figure 3 This is a structural schematic diagram of a sealing ring assembly according to some embodiments.

[0035] In some embodiments, such as Figure 3As shown, the sealing ring 110 includes a first segment 111 and a second segment 112. The first segment 111 and the second segment 112 are interconnected, forming a stable triangular support with the stator housing 61, ensuring stable support between the sealing ring 110 and the stator housing 61. Since the stator housing 61 also generates slight vibrations during engine operation, to prevent the sealing ring 110 from being affected by the vibrations of the stator housing 61, either the first segment 111 or the second segment 112 of the sealing ring 110 is connected to the stator housing 61. In some embodiments, the first segment 111 extends approximately radially along the rotor, and the second segment 112 extends approximately axially along the rotor. The rotor radial direction referred to in this specification means the direction along the radius of the rotor 10. The sealing ring 110 configured in this way can provide a flat radial plane for the installation of the honeycomb ring 120 on the irregular inner surface of the stator housing 61, which is beneficial to ensuring the sealing effect between the honeycomb ring 120 and the sealing teeth 101. In some embodiments, since the vibration between the honeycomb ring 120 and the sealing teeth 101 is mainly radial vibration, in order to reduce the radial vibration between the honeycomb ring 120 and the sealing teeth 101, the vibration damping member 130 is disposed in the radial direction of the sealing ring 110.

[0036] In some embodiments, a third segment 113 extends axially from the first segment 111 along the rotor axis, and an annular groove 114 is defined between the second segment 112 and the third segment 113, the groove 114 being arranged axially around the rotor axis. A vibration damper 130 is disposed in the groove 114. A honeycomb ring 120 is sleeved on the outer side of the second segment 112 opposite to the groove 114.

[0037] In some embodiments, the first segment 111 or the third segment 113 is fixedly installed on the stator housing 61, and the second segment 112 can be considered a free segment. In this case, the vibration damper 130 is fixedly installed on the free segment, i.e., the second segment 112, which helps to optimize the vibration damping effect of the vibration damper 130. In some embodiments, the first segment 111 and the third segment 113 are simultaneously installed and fixed on the stator housing 61. The first segment 111 and the third segment 113 can together form a stable triangular support with the inner side of the stator housing 61, which helps to ensure the stability and sealing of the connection structure between the sealing ring 110 and the stator housing 61. In some embodiments, the first segment 111 and the third segment 113 are adapted to the inner structure of the stator housing 61, which helps to ensure the sealing of the connection structure between the sealing ring 110 and the stator housing 61. In some embodiments, such as Figure 2 As shown, the first segment 111 and the third segment 113 are connected and engaged with the protruding structure inside the stator housing 61. In some embodiments, the second segment 112 is fixedly installed to the stator housing 61, and the first segment 111 and the third segment 113 can be regarded as free segments. In this case, fixing the vibration damper 130 to the free segment, i.e., the third segment 113, is beneficial to optimizing the vibration damping effect of the vibration damper 130.

[0038] In some embodiments, the damper 130 has a fixed end 131 and a free end 132. When the second segment 112 is a free segment, the fixed end 131 is fixedly connected to the second segment 112, and the free end 132 extends along the first segment 111 and is located in the third segment 113. In some embodiments, when either the first segment 111 or the third segment 113 is a free segment, the fixed end 131 is fixedly connected to the third segment 113, and the free end 132 extends along the first segment 111 and is located in the second segment 112. The connection and fixing method between the damper 130 and the sealing ring 110 is not limited; for example, bolt connection, welding, bonding, etc., can be used. It should be noted that... Figure 3 The diagram shows the first segment 111 or the third segment 113 fixed to the stator housing 61, with the second segment 112 being a free segment, and the fixed end 131 connected and fixed to the second segment 112. Since the damper 130 primarily reduces the radial vibration of the sealing ring 110, when the first segment 111 or the third segment 113 is fixed to the stator housing 61 and the second segment 112 is a free segment, the damper 130 is fixed to the second segment 112, achieving a better damping effect. This manual will now use the example of the first segment 111 or the third segment 113 being fixed to the stator housing 61 and the second segment 112 being a free segment, with the damper 130 fixed to the second segment 112, for further explanation.

[0039] In some embodiments of this specification, a damping element 130 is provided in the slot 114 defined within the sealing ring 110. When the sealing ring assembly 100 vibrates in contact with the sealing teeth 101, the damping element 130 and the slot 114 collide and rub against each other. This can reduce or consume the energy of the vibration load generated by the sealing ring assembly 100, thereby achieving a vibration reduction effect. This helps to maintain normal and not excessive friction between the honeycomb ring 120 and the sealing teeth 101, ensuring the sealing effect. It also maintains the normal cavity temperature, cavity pressure and axial force of the cavities connected to the sealing ring assembly 100 (e.g., the first air cavity 102 and the second air cavity 103), thus maintaining the normal and safe operation of the engine.

[0040] In some embodiments, the fixed end 131 and the free end 132 of the damper 130 have a continuous bending structure extending close to the inner wall of the slot 114. The continuous bending structure extends along the inner wall of the slot 114 and connects the fixed end 131 and the free end 132. Within limited axial and radial space, the size and mass of the damper 130 can be increased to increase the mass of the free end 132 of the damper 130, thereby increasing the energy consumed by the collision between the damper 130 and the sealing ring 110, effectively enhancing the vibration damping effect.

[0041] In some embodiments, to further increase the mass of the free end 132 of the damper 130, the continuous bending structure between the fixed end 131 and the free end 132 includes regular or irregular structures such as wave segments, toothed segments, broken line segments, and arc segments. In some embodiments, a fulcrum structure 133 is provided on the continuous bending structure. The damper 130 contacts the sealing ring 110 through the fulcrum structure 133. The contact between the fulcrum structure 133 and the sealing ring 110 forms a vibration fulcrum. The vibration fulcrum is the main location where the damper 130 collides with the sealing ring 110, and it is also the main location for consuming the vibration kinetic energy of the sealing ring 110. The fulcrum structure 133 can be set at any position on the continuous bending structure. In some embodiments, to reduce the amplitude of the damper 130 and ensure the damping effect of the damper 130, the fulcrum structure 133 is set close to the fixed end 131 of the damper 130. In some embodiments, when the fixed end 131 of the damper 130 is connected and fixed to the second segment 112, the fulcrum structure 133 protrudes toward the second segment 112 and abuts against the second segment 112. In some embodiments, when the fixed end 131 of the damper 130 is connected and fixed to the third segment 113, the fulcrum structure 133 protrudes toward the third segment 113 and abuts against the third segment 113.

[0042] In some embodiments, the continuous bending structure includes one or more support structures 133, which can dissipate more of the vibrational kinetic energy of the sealing ring 110. In some embodiments, the damping sections on both sides of the support structure 133 are relatively far away from the sealing ring 110 to avoid vibration caused by the support structure 133 dissipating the vibrational kinetic energy of the sealing ring 110, and to prevent the sealing ring 110 from vibrating in the opposite direction. In some embodiments, the support structure 133 is a sharp-corner structure, an arc structure, or a boss structure, etc., and the support structure 133 can be provided on the wave segment, toothed segment, broken line segment, or arc segment of the continuous bending structure.

[0043] In some embodiments, to ensure the elasticity of the damper 130, the damper 130 is made of a flexible sheet material. The flexible sheet material is in the shape of a thin sheet, which is beneficial for utilizing the flexibility of the material. In some embodiments, the flexible sheet material includes an elastic metallic material, such as an elastic alloy, including highly elastic alloys and constant-elastic alloys.

[0044] In some embodiments, the damper 130 has a radial gap with the second segment 112 and the third segment 113, or the damper 130 has a radial gap with the second segment 112 or the third segment 113. The width of the radial gap is radial, ensuring that the damper 130 has the necessary radial vibration space during the damping process, and preventing the vibration generated by the damper 130 due to the consumption of the vibration energy of the sealing ring assembly 100 from causing the sealing ring 110 to vibrate in the opposite direction. In some embodiments, the damper 130 has an axial gap with the first segment 111. The width of the axial gap is axial, ensuring that the damper 130 has the necessary axial vibration space during the damping process, and preventing the vibration generated by the damper 130 due to the consumption of the vibration energy of the sealing ring assembly 100 from causing the sealing ring 110 to vibrate in the opposite direction.

[0045] In some embodiments, the damping element 130 has a ring-shaped structure and is disposed within the annular groove 114, arranged around the rotor axis. This allows for uniform vibration damping of the sealing ring 110 in the circumferential direction around the rotor axis. In some embodiments, the sealing ring assembly 100 includes the damping element 130, with multiple damping elements 130 disposed within the annular groove 114. The multiple damping elements 130 are evenly spaced in the circumferential direction, which can achieve a relatively uniform vibration damping effect on the sealing ring 110 in the circumferential direction around the rotor axis. This also helps to reduce the weight of the sealing ring assembly 100, achieving a lightweight design.

[0046] The basic concepts have been described above. It is clear that the detailed disclosure above is merely illustrative and does not constitute a limitation of this specification, especially for those skilled in the art. Furthermore, unless expressly stated in the claims, the order of elements and sequences, the use of numbers and letters, or other names in this specification are not intended to limit the order of the processes and methods described herein. Although various examples of currently considered useful embodiments of the invention have been discussed in the foregoing disclosure, it should be understood that such details are for illustrative purposes only, and the appended claims are not limited to the disclosed embodiments. Rather, the claims are intended to cover all modifications and equivalent combinations that conform to the substance and scope of the embodiments described herein.

Claims

1. A sealing ring assembly, characterized in that, The sealing ring assembly includes a sealing ring, which is fixed relative to the stator, and the sealing ring has a first segment and a second segment; The first segment extends radially along the rotor, the second segment extends axially along the rotor, and a third segment extends axially from the first segment, with a groove defined between the second segment and the third segment. A vibration damping component is provided in the slot, and there is a radial gap between the vibration damping component and the second section or the third section.

2. The sealing ring assembly according to claim 1, characterized in that, There is an axial gap between the vibration damper and the first section.

3. The sealing ring assembly according to claim 1, characterized in that, The vibration damper is made of a flexible sheet material.

4. The sealing ring assembly according to claim 1, characterized in that, The first segment and the third segment are fixedly installed with the stator casing, while the second segment is a free segment; The vibration damper has a free end and a fixed end. The fixed end is connected and fixed to the second segment, and the free end is located in the third segment. There is a continuous bending structure between the fixed end and the free end that extends close to the inner wall of the slot.

5. The sealing ring assembly according to claim 4, characterized in that, The first segment and the third segment are connected and fitted with the protruding structure inside the stator casing.

6. The sealing ring assembly according to claim 1, characterized in that, The second section is fixedly installed with the stator casing, while the first and third sections are free sections; The vibration damper has a free end and a fixed end. The fixed end is connected and fixed to the third segment. The free end is located in the second segment. There is a continuous bending structure between the fixed end and the free end that extends close to the inner wall of the slot.

7. The sealing ring assembly according to claim 4 or 6, characterized in that, The continuous bending structure includes a wave segment, which has a support structure that protrudes radially toward the second or third segment of the rotor and abuts against the second or third segment.

8. The sealing ring assembly according to claim 1, characterized in that, The sealing ring has a ring-shaped structure and is arranged axially around the rotor. An annular groove is defined between the second segment and the third segment of the sealing ring. The vibration damping component is a ring-shaped structure, and it is arranged axially around the rotor and disposed within the annular groove.

9. The sealing ring assembly according to claim 1, characterized in that, The sealing ring has a ring-shaped structure and is arranged axially around the rotor. An annular groove is defined between the second segment and the third segment of the sealing ring. The vibration damping component includes a plurality of vibration damping components, which are disposed in the annular groove and are spaced apart in the circumferential direction around the rotor axis.

10. The sealing ring assembly according to claim 1, characterized in that, The sealing ring assembly includes a honeycomb ring, the sealing ring having an annular structure, and the sealing ring and the honeycomb ring being arranged axially around the rotor; The honeycomb ring is disposed on the outer side of the second section opposite to the slot, and the honeycomb ring cooperates with the sealing grating provided on the rotor to achieve sealing.

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