Spring ring vibration reduction structure of small and medium-sized gas turbine
By using a spring ring vibration reduction structure for small and medium-sized gas turbines and employing a nonlinear stiffness system of double spring rings and adjusting rings, the problems of high stiffness and large deformation compensation for bearings in small and medium-sized gas turbines and aero-engines are solved, achieving efficient vibration suppression and structural compactness, and improving the operational reliability and safety of the rotor system.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-02
- Publication Date
- 2026-03-20
AI Technical Summary
Existing vibration reduction structures for small and medium-sized gas turbine and aero-engine bearings are complex in structure, limited in space, and difficult to simultaneously achieve high stiffness and large axial deformation compensation, resulting in poor vibration control and affecting the operational reliability and safety of the rotor system.
A spring ring vibration reduction structure for small and medium-sized gas turbines is adopted. A nonlinear stiffness system is constructed by combining double spring rings and adjusting rings. A continuous support is formed by the staggered arrangement of trapezoidal bosses. Combined with high-temperature alloy materials and nitriding treatment, high stiffness and large deformation compensation are achieved. Vibration energy is absorbed through elastic deformation to reduce vibration amplitude.
It achieves high-rigidity support and large deformation compensation, effectively suppresses vibration and improves damping characteristics, increases bearing service life, reduces manufacturing and maintenance costs, is suitable for high-performance vibration reduction in confined spaces, and enhances anti-loosening and anti-wear performance.
Smart Images
Figure CN121701337A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of rotor support structure technology for gas turbines and aero engines, specifically to a spring ring vibration reduction structure for small and medium-sized gas turbines. Background Technology
[0002] Small and medium-sized gas turbines and aero engines, as high-energy-density power plants, generally operate at high speeds and high loads. Their rotor systems typically rotate at speeds exceeding 7000 rpm, and can even reach tens of thousands of rpm. Under these extreme conditions, bearings, as the core components supporting the rotor, bear complex dynamic loads, especially axial thrust and vibration. If the bearing system fails due to excessive vibration or accumulated axial deformation, it will lead to rotor instability, collisions, or even complete collapse, resulting in catastrophic consequences.
[0003] Currently, conventional bearing vibration reduction structures mostly employ hydraulic damping, extrusion oil film, or complex multi-layer elastic supports. While these methods offer some vibration reduction, they suffer from problems such as complex structures, high precision requirements, high manufacturing costs, and difficult maintenance. Especially in space-constrained small and medium-sized gas turbines and aero-engines, traditional vibration reduction solutions often struggle to achieve efficient vibration control and axial deformation compensation within limited space.
[0004] Therefore, there is an urgent need to develop a bearing vibration reduction structure that is simple in structure, easy to process and assemble, and has excellent axial deformation compensation and vibration suppression capabilities, so as to improve the operational reliability and safety of small and medium-sized gas turbines and aero-engine rotor systems. Summary of the Invention
[0005] The purpose of this invention is to solve the problems of existing vibration reduction structures for small and medium-sized gas turbine and aero-engine bearings, which are complex in structure, limited in space, and difficult to simultaneously achieve high stiffness and large axial deformation compensation capabilities. Therefore, this invention provides a spring ring vibration reduction structure for small and medium-sized gas turbines.
[0006] The technical solution of this invention is:
[0007] A spring ring vibration damping structure for small and medium-sized gas turbines includes a bearing housing 6, a bearing 2 disposed within the bearing housing 6, and a clamping assembly fixed to the end of the bearing housing 6 by a cover plate 5.
[0008] The clamping assembly is disposed between the outer ring end face of the bearing 2 and the cover plate 5;
[0009] The clamping assembly includes a pair of spring rings 3 and an adjusting ring 4 disposed between the pair of spring rings 3;
[0010] The spring ring 3 is an annular thin sheet component, and each spring ring body has multiple outwardly protruding trapezoidal bosses 3-1 evenly distributed along the circumferential direction on the end face near the adjusting ring side;
[0011] The trapezoidal bosses 3-1 of the two spring rings 3 are staggered in the axial direction, so that the bosses and roots of the two spring rings 3 form a continuous and uniform support in the circumferential direction, thus forming a nonlinear stiffness elastic system together.
[0012] The thickness of the adjusting ring 4 is configured to adjust the axial preload of the entire clamping assembly;
[0013] The cover plate 5 axially presses the pair of spring rings 3 and the adjusting ring 4 together, so that the pair of spring rings 3 and the adjusting ring 4 produce a predetermined interference fit at the designated mating surface after assembly, so as to maintain a stable bearing preload.
[0014] Furthermore, the number of trapezoidal bosses 3-1 is 4, 6, or 8.
[0015] Furthermore, the predetermined interference is 0.30 mm to 0.35 mm.
[0016] Furthermore, the thickness H of the spring ring 3 is 4.5 mm.
[0017] Furthermore, the trapezoidal boss 3-1 has a thickness h of 3.8 mm, a top width W1 of 6 mm, and an angle B of 60 degrees.
[0018] Furthermore, the spring ring 3 is made of a high-temperature alloy.
[0019] Furthermore, the high-temperature alloy is a nickel-based high-temperature alloy or a cobalt-based high-temperature alloy.
[0020] Furthermore, the spring ring 3 is made of high-temperature heat-resistant and corrosion-resistant stainless steel alloy and has undergone solution treatment and aging treatment.
[0021] Furthermore, the surface of the trapezoidal boss 3-1 is subjected to nitriding treatment.
[0022] Furthermore, the adjustment ring 4 is a flat annular sheet with a thickness tolerance of ±0.01mm or a non-flat structure with a tapered or wavy cross-section.
[0023] Compared with the prior art, the present invention has the following advantages:
[0024] 1. This invention discloses a spring ring vibration damping structure for small and medium-sized gas turbines, which can simultaneously achieve axial deformation compensation and high stiffness maintenance. A nonlinear stiffness system is constructed through the combination of a double spring ring and an adjusting ring. This specific structure provides a stiffness of up to 2700 kg / mm while effectively absorbing axial thermal deformation of over 0.3 mm, thus resolving the contradiction between high stiffness and large allowable deformation.
[0025] 2. This invention provides a spring ring vibration damping structure for small and medium-sized gas turbines, which can effectively suppress vibration and improve damping characteristics. While bearing axial loads, the spring ring absorbs and dissipates vibration energy through its elastic deformation, reducing the vibration amplitude transmitted to the support structure, effectively suppressing high-cycle fatigue and resonance risks, and improving bearing service life.
[0026] 3. This invention provides a spring ring vibration damping structure for small and medium-sized gas turbines, exhibiting excellent resistance to loosening and uneven wear. The preset interference fit of 0.30-0.35mm ensures that the system maintains sufficient initial preload during long-term operation, effectively resisting relaxation caused by high-cycle alternating loads. The nitriding treatment and optimized geometry of the boss surface greatly improve wear resistance, avoiding premature failure of traditional wave springs due to localized wear.
[0027] 4. This invention provides a spring ring vibration damping structure for small and medium-sized gas turbines, which features extremely high structural compactness and engineering adaptability. The entire vibration damping module has a very small axial dimension, consisting of only three thin rings. It has strong component versatility and is particularly suitable for achieving high-performance vibration damping in the confined space of the bearing cavity. It can directly replace the original flat ring or single spring washer without modifying the main structure.
[0028] 5. This invention provides a spring ring vibration damping structure for small and medium-sized gas turbines, achieving low manufacturing and maintenance costs. The standardized and parametric design of the spring ring and adjusting ring allows for precise fine-tuning of their stiffness and preload through the adjusting ring thickness. The structure is simple and easy to assemble and disassemble, greatly reducing the difficulty and cost of manufacturing, assembly, and subsequent maintenance. Attached Figure Description
[0029] Figure 1 This is a cross-sectional view of the overall structure of the present invention.
[0030] Figure 2 This is a front view of the spring ring in this invention.
[0031] Figure 3 yes Figure 2 Side view of the middle spring ring.
[0032] Figure 4 This is a schematic diagram showing the assembly explosion relationship between the spring ring and the adjusting ring.
[0033] In the diagram: 1-rotor structure, 2-bearing, 3-spring ring, 3-1-trapezoidal boss, 4-adjusting ring, 5-cover plate, 6-bearing housing. Detailed Implementation
[0034] Specific implementation method one: Combining Figures 1 to 4This embodiment describes a spring ring vibration damping structure for small and medium-sized gas turbines, comprising a bearing housing 6, a bearing 2 disposed within the bearing housing 6, and a clamping assembly fixed to the end of the bearing housing 6 by a cover plate 5.
[0035] The clamping assembly is disposed between the outer ring end face of the bearing 2 and the cover plate 5;
[0036] The clamping assembly includes a pair of spring rings 3 and an adjusting ring 4 disposed between the pair of spring rings 3;
[0037] The spring ring 3 is an annular thin sheet component, and each spring ring body has multiple outwardly protruding trapezoidal bosses 3-1 evenly distributed along the circumferential direction on the end face near the adjusting ring side;
[0038] The trapezoidal bosses 3-1 of the two spring rings 3 are staggered in the axial direction, so that the bosses and roots of the two spring rings 3 form a continuous and uniform support in the circumferential direction, thus forming a nonlinear stiffness elastic system together.
[0039] The thickness of the adjusting ring 4 is configured to adjust the axial preload of the entire clamping assembly;
[0040] The cover plate 5 axially presses the pair of spring rings 3 and the adjusting ring 4 together, so that the pair of spring rings 3 and the adjusting ring 4 produce a predetermined interference fit at the designated mating surface after assembly, so as to maintain a stable bearing preload.
[0041] Specific Implementation Method Two: Combining Figures 1 to 4 In this embodiment, the trapezoidal bosses 3-1 are 4, 6, or 8 in number. This arrangement provides different options for the number of bosses, allowing the vibration damping structure to adapt to bearings of different sizes and load requirements, thus enhancing design flexibility and applicability. Other components and connections are the same as in Specific Embodiment One.
[0042] Specific implementation method three: Combining Figures 1 to 4 In this embodiment, the predetermined interference fit is between 0.30 mm and 0.35 mm. This interference fit range ensures that the system generates sufficient initial preload after assembly, which is crucial for ensuring the long-term reliability of the vibration damping structure. Other components and connections are the same as in specific embodiments one or two.
[0043] Specific implementation method four: Combination Figures 1 to 4 In this embodiment, the thickness H of the spring ring 3 is 4.5 mm. This thickness parameter is a designed dimension for the spring ring structure, providing a basis for achieving the desired stiffness and elastic deformation capacity. Other components and connections are the same as in specific embodiments one, two, or three.
[0044] Specific Implementation Method Five: Combining Figures 1 to 4 In this embodiment, the trapezoidal boss 3-1 has a thickness h of 3.8 mm, a top width W1 of 6 mm, and an angle B of 60 degrees. This configuration defines the optimized geometry of the trapezoidal boss, contributing to uniform load distribution and a favorable stress state. Other components and connections are the same as in specific embodiments one, two, three, or four.
[0045] Specific Implementation Method Six: Combination Figures 1 to 4 This embodiment describes a spring ring 3 made of a high-temperature alloy. This design ensures that the spring ring maintains excellent mechanical properties and anti-relaxation capabilities even under high-temperature operating conditions. Other components and connections are the same as in specific embodiments one, two, three, four, or five.
[0046] Specific implementation method seven: Combination Figures 1 to 4 This embodiment describes a high-temperature alloy that is either a nickel-based or a cobalt-based high-temperature alloy. This configuration makes nickel-based or cobalt-based high-temperature alloys preferred materials for extreme high-temperature conditions, further extending the service life of the spring ring in harsh environments. Other components and connections are the same as in specific embodiments one, two, three, four, five, or six.
[0047] Specific implementation method eight: Combination Figures 1 to 4 This embodiment describes a spring ring 3 made of high-temperature, heat-resistant, and corrosion-resistant stainless steel alloy, which has undergone solution treatment and aging treatment. This configuration, combining the high-temperature stainless steel alloy with solution and aging treatment, gives the spring ring excellent corrosion resistance, high-temperature strength, and toughness. Other components and connections are the same as in specific embodiments one, two, three, four, five, six, or seven.
[0048] Specific Implementation Method Nine: Combining Figures 1 to 4 In this embodiment, the surface of the trapezoidal boss 3-1 is nitrided. This nitriding treatment significantly improves the hardness and wear resistance of the trapezoidal boss surface, effectively resisting wear under high-frequency fretting conditions. Other components and connections are the same as in specific embodiments one, two, three, four, five, six, seven, or eight.
[0049] Specific Implementation Method Ten: Combining Figures 1 to 4In this embodiment, the adjusting ring 4 is a flat annular sheet with a thickness tolerance of ±0.01mm or a non-flat structure with a tapered or wavy cross-section. This design allows for precise control of the preload force with a flat annular sheet, while the tapered or wavy non-flat structure provides another feasible solution for fine-tuning the system's stiffness characteristics. Other components and connections are the same as in specific embodiments one, two, three, four, five, six, seven, eight, or nine.
[0050] Working principle
[0051] Combination Figures 1 to 4 The working principle of the spring ring vibration reduction structure for small and medium-sized gas turbines of the present invention is as follows: During the assembly stage, two spring rings 3 are arranged with their trapezoidal bosses 3-1 staggered, with the adjusting ring 4 sandwiched in the middle, and pressed between the outer ring of the bearing 2 and the bearing housing 6 by the cover plate 5. This assembly process generates an interference of 0.30mm to 0.35mm on the specified mating surface (T surface), which provides a stable initial preload for the system. During operation, the axial force from the rotor is transmitted to the clamping assembly through the outer ring of bearing 2. Due to the staggered arrangement of the bosses of the two spring rings, a continuous and uniform support is formed in the circumferential direction, allowing the load to be evenly distributed along the circumference. This together constitutes a nonlinear stiffness elastic system. In actual measurements within the axial load range of 500kg to 2500kg, its instantaneous stiffness is stable between 2700kg / mm and 3000kg / mm, achieving high-stiffness support. When the rotor system undergoes axial dimensional changes due to thermal expansion, this structure can effectively absorb axial thermal deformation of more than 0.3mm through the elastic deformation of the spring ring bosses, achieving deformation compensation. At the same time, the broadband vibration energy generated during engine operation is transmitted here and absorbed and dissipated by the elastic deformation of the spring rings, thereby significantly reducing the vibration amplitude transmitted to the support structure and suppressing the risk of high-cycle fatigue and resonance. In summary, this structure, through its unique staggered double spring ring design, simultaneously achieves high-stiffness support, large deformation compensation, and efficient vibration suppression.
[0052] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims
1. A spring ring vibration damping structure for small and medium-sized gas turbines, comprising a bearing housing (6), a bearing (2) disposed within the bearing housing (6), and a clamping assembly fixed to the end of the bearing housing (6) by a cover plate (5), characterized in that: The clamping assembly is disposed between the outer ring end face of the bearing (2) and the cover plate (5); The clamping assembly includes a pair of spring rings (3) and an adjusting ring (4) disposed between the pair of spring rings (3); The spring ring (3) is an annular thin sheet component. On the end face of each spring ring body near the adjusting ring, there are multiple outwardly protruding trapezoidal bosses (3-1) evenly distributed in the circumferential direction. The trapezoidal bosses (3-1) of the two spring rings (3) are staggered in the axial direction, so that the bosses and roots of the two spring rings (3) form a continuous and uniform support in the circumferential direction, thus forming a nonlinear stiffness elastic system together. The thickness of the adjusting ring (4) is configured to adjust the axial preload of the entire clamping assembly; The cover plate (5) axially presses the pair of spring rings (3) and the adjusting ring (4) together, so that the pair of spring rings (3) and the adjusting ring (4) produce a predetermined interference fit at the specified mating surface after assembly, so as to maintain a stable bearing preload.
2. The spring ring vibration damping structure for small and medium-sized gas turbines according to claim 1, characterized in that, The number of trapezoidal bosses (3-1) is 4, 6, or 8.
3. A spring ring vibration damping structure for small and medium-sized gas turbines according to claim 1 or 2, characterized in that, The predetermined interference is 0.30 mm to 0.35 mm.
4. A spring ring vibration damping structure for small and medium-sized gas turbines according to claim 1 or 2, characterized in that, The thickness (H) of the spring ring (3) is 4.5 mm.
5. A spring ring vibration damping structure for small and medium-sized gas turbines according to claim 1 or 2, characterized in that, The trapezoidal boss (3-1) has a thickness (h) of 3.8 mm, a top width (W1) of 6 mm, and an angle (B) of 60 degrees.
6. A spring ring vibration damping structure for small and medium-sized gas turbines according to claim 1 or 2, characterized in that, The spring ring (3) is made of high-temperature alloy.
7. The spring ring vibration damping structure for small and medium-sized gas turbines according to claim 6, characterized in that, The high-temperature alloy is a nickel-based high-temperature alloy or a cobalt-based high-temperature alloy.
8. A spring ring vibration damping structure for small and medium-sized gas turbines according to claim 1 or 2, characterized in that, The spring ring (3) is made of high-temperature heat-resistant and corrosion-resistant stainless steel alloy and has undergone solution treatment and aging treatment.
9. A spring ring vibration damping structure for small and medium-sized gas turbines according to claim 6, 7, or 8, characterized in that, The surface of the trapezoidal boss (3-1) is nitrided.
10. A spring ring vibration damping structure for small and medium-sized gas turbines according to claim 1 or 2, characterized in that, The adjustment ring (4) is a flat annular sheet with a thickness tolerance of ±0.01mm or a non-flat structure with a tapered or wavy cross-section.