Elastic supporting device for rotor system and aero-engine

Abstract

The invention discloses an elastic supporting device for a rotor system and an aero-engine, the elastic supporting device comprises a bearing seat, an elastic ring and a bearing, the elastic ring is arranged in the bearing seat and supports the bearing, the bearing is arranged in the elastic ring and is used for supporting a rotor assembly, the elastic ring comprises a sleeve, two annular bosses and a plurality of connecting ribs, and the two annular bosses are arranged in the sleeve. The sleeve is located between the two annular bosses, the connecting ribs are connected with the sleeve and the annular bosses respectively, the multiple connecting ribs are evenly distributed in the circumferential direction of the annular bosses at intervals, kidney-shaped holes are defined by the connecting ribs, the sleeve and the annular bosses, and the outer ring faces of the annular bosses and the outer ring face of the sleeve are arranged in a staggered mode in the radial direction. The inner ring face of the annular boss and the inner ring face of the sleeve are arranged in a staggered mode in the radial direction, the radial outer end of the elastic ring and the bearing seat define an outer extrusion oil film cavity, the radial inner end of the elastic ring and the bearing define an inner extrusion oil film cavity, and the kidney-shaped hole is communicated with the outer extrusion oil film cavity and the inner extrusion oil film cavity.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engines, and in particular, to an elastic support device for a rotor system. In addition, the present invention also relates to an aircraft engine comprising the elastic support device for a rotor system. Background Art

[0002] For small and medium-sized aircraft engines, due to their small size, high speed and wide operating speed range, the critical speed of the rotor system often falls within the operating speed range of the engine. In order to adjust the critical speed of the rotor system, when the overall parameters of the engine are strictly limited and it is difficult to adjust the diameter of the shaft and the fulcrum distance, the method of increasing the bending stiffness of the rotor is usually adopted.

[0003] At present, the most effective and feasible method to increase the bending stiffness of the rotor assembly is usually to set up an elastic ring elastic support in the rotor system, which has the characteristics of simple structure, light weight and small space occupation.

[0004] However, if Figure 1 and Figure 2 As shown, the existing elastic ring type elastic supports are mainly divided into two categories: toothed elastic rings and inner and outer boss elastic rings. However, within the limited space of the rotor system, the toothed elastic rings and the inner and outer boss elastic rings often show that the stiffness and strength are incompatible and the vibration reduction effect is poor. Generally speaking, the fitting surface of the toothed elastic ring is not a complete ring, and it is easy to have broken teeth. When the stiffness value is qualified, the fatigue strength reserve coefficient is low; while the inner and outer boss elastic rings, when the fatigue strength reserve coefficient is qualified, the stiffness value is high; and because the toothed elastic ring has a notch and the inner and outer boss elastic rings have two bosses, they do not have the central symmetry feature in structure, resulting in uneven force on the oil film in the oil film chamber formed in the rotor system, uneven stiffness of the oil film, and poor vibration reduction effect. Summary of the invention

[0005] The invention provides an elastic support device for a rotor system and an aero-engine, so as to solve the technical problems that the elastic support stiffness and the fatigue strength reserve coefficient in the existing rotor system are incompatible and the vibration reduction effect is poor.

[0006] According to one aspect of the present invention, an elastic support device for a rotor system is provided, comprising a bearing seat, an elastic ring and a bearing, wherein the elastic ring is arranged in the bearing seat and supports the bearing, the bearing is arranged in the elastic ring and is used to support the rotor assembly, the elastic ring comprises a sleeve, two annular bosses and a plurality of connecting ribs, the sleeve is located between the two annular bosses, the connecting ribs are respectively connected to the sleeve and the annular boss, the plurality of connecting ribs are evenly arranged along the circumferential direction of the annular boss, the connecting ribs, the sleeve and the annular boss are enclosed to form a waist-shaped hole, the outer annular surface of the annular boss and the outer annular surface of the sleeve are staggered in the radial direction, the inner annular surface of the annular boss and the inner annular surface of the sleeve are staggered in the radial direction, the radial outer end of the elastic ring and the bearing seat are enclosed to form an outer extrusion oil film chamber, the radial inner end of the elastic ring and the bearing are enclosed to form an inner extrusion oil film chamber, and the waist-shaped hole is respectively connected to the outer extrusion oil film chamber and the inner extrusion oil film chamber.

[0007] As a further improvement of the above technical solution:

[0008] Furthermore, a first oil mist inlet is radially opened on the bearing seat, and the outer ring surfaces of the two annular bosses are both in contact with the bearing seat, so that the outer ring surface of the sleeve and the bearing seat are combined to form an external extrusion oil film chamber, and the first oil mist inlet is symmetrically distributed along the axial center plane of the external extrusion oil film chamber.

[0009] Furthermore, the inner ring surface of the sleeve fits with the bearing, so that the inner ring surfaces of the two annular bosses and the bearing seat enclose two inner extrusion oil film chambers, and the two extrusion oil film chambers are symmetrically distributed along the axial center plane of the outer extrusion oil film chamber.

[0010] Furthermore, the bearing seat is provided with a second oil mist inlet and an oil mist outlet along the axial direction, and the inner cavity of the bearing is respectively connected with the inner extrusion oil film chamber, the second oil mist inlet and the oil mist outlet.

[0011] Furthermore, the elastic support device also includes a bushing retaining ring arranged in the bearing seat and abutting against the annular boss for cooperating with the bearing seat to axially position the elastic ring.

[0012] Furthermore, the number of connecting ribs is 8-16.

[0013] Furthermore, the circumferential length of the connecting rib is 5mm-10mm, the radial height of the connecting rib is 0.3mm-2mm, and the axial width of the connecting rib is 2mm-5mm.

[0014] Furthermore, the radial height of the annular boss is 0.5 mm-4 mm, and the axial width of the annular boss is 1 mm-3 mm.

[0015] Furthermore, the radial height of the sleeve is 0.5 mm-2 mm, the inner diameter of the sleeve is 20 mm-50 mm, and the axial width of the sleeve is 3 mm-10 mm.

[0016] According to another aspect of the present invention, there is also provided an aircraft engine, which comprises the elastic support device for the rotor system mentioned above.

[0017] The present invention has the following beneficial effects:

[0018] The elastic support device for the rotor system of the present invention installs an elastic ring through a bearing seat, and elastically supports the bearing through the elastic ring, so that when the bearing supports the rotor assembly, the elastic support of the rotor assembly is realized through the elastic ring, thereby increasing the bending stiffness of the rotor assembly; in the elastic ring, since the outer ring surface of the annular boss and the outer ring surface of the sleeve are staggered in the radial direction, and the inner ring surface of the annular boss and the inner ring surface of the sleeve are staggered in the radial direction, the elastic ring is respectively fitted with the bearing seat and the bearing through the complete ring surfaces on the annular boss and the sleeve, so as to improve the fatigue strength reserve coefficient of the elastic ring; a waist-shaped hole is formed by enclosing the connecting ribs, the sleeve and the annular boss, and since a plurality of connecting ribs are evenly arranged at intervals along the circumference of the annular boss, that is, a plurality of waist-shaped holes are correspondingly formed on the elastic ring, thereby improving Improve the supporting stiffness of the elastic ring; the elastic ring is surrounded by the radial outer end and the bearing seat to form an outer extrusion oil film chamber, the radial inner end of the elastic ring and the bearing are surrounded to form an inner extrusion oil film chamber, the waist-shaped holes are respectively connected to the outer extrusion oil film chamber and the inner extrusion oil film chamber, because the sleeve is located between the two annular bosses, the connecting ribs are respectively connected to the sleeve and the annular boss, so that the elastic ring is a centrally symmetrical structure, thereby ensuring that the oil film in the outer extrusion oil film chamber and the inner extrusion oil film chamber is uniformly stressed and the oil film stiffness is uniform, so as to have a better vibration reduction effect; compared with the prior art, this scheme optimizes and improves the structure of the elastic ring, and cooperates with the bearing and the bearing seat, so that the elastic support is compatible with the stiffness and fatigue strength reserve coefficient, while enhancing the vibration reduction effect, has strong practicality, and is suitable for wide promotion and application.

[0019] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0021] Figure 1 It is a structural schematic diagram of a toothed elastic ring in the prior art;

[0022] Figure 2 It is a schematic diagram of the structure of the elastic ring of the inner and outer bosses in the prior art;

[0023] Figure 3is a schematic structural diagram of an elastic support device for a rotor system according to a preferred embodiment of the present invention;

[0024] Figure 4 is a schematic structural diagram of an elastic ring in an elastic support device for a rotor system in a preferred embodiment of the present invention;

[0025] Figure 5 is a side view of an elastic ring in an elastic support device for a rotor system according to a preferred embodiment of the present invention;

[0026] Figure 6 It is a cross-sectional schematic diagram of an elastic ring in an elastic supporting device for a rotor system according to a preferred embodiment of the present invention.

[0027] Legend:

[0028] 100, bearing seat; 110, first oil mist inlet; 120, second oil mist inlet; 130, oil mist outlet; 200, elastic ring; 210, sleeve; 220, annular boss; 230, connecting rib; 300, bearing; 400, rotor assembly; 500, outer extrusion oil film chamber; 600, inner extrusion oil film chamber; 700, bushing retaining ring. DETAILED DESCRIPTION

[0029] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0030] like Figure 3-Figure 6 As shown, the elastic support device for the rotor system of this embodiment includes a bearing seat 100, an elastic ring 200 and a bearing 300. The elastic ring 200 is arranged in the bearing seat 100 and supports the bearing 300. The bearing 300 is arranged in the elastic ring 200 and is used to support the rotor assembly 400. The elastic ring 200 includes a sleeve 210, two annular bosses 220 and a plurality of connecting ribs 230. The sleeve 210 is located between the two annular bosses 220. The connecting ribs 230 are connected to the sleeve 210 and the annular boss 220 respectively. The plurality of connecting ribs 230 are spaced circumferentially along the annular boss 220. The connecting rib 230, the sleeve 210 and the annular boss 220 are evenly arranged, and a waist-shaped hole is enclosed. The outer ring surface of the annular boss 220 and the outer ring surface of the sleeve 210 are staggered in the radial direction. The inner ring surface of the annular boss 220 and the inner ring surface of the sleeve 210 are staggered in the radial direction. The radial outer end of the elastic ring 200 and the bearing seat 100 are enclosed to form an outer extrusion oil film chamber 500. The radial inner end of the elastic ring 200 and the bearing 300 are enclosed to form an inner extrusion oil film chamber 600. The waist-shaped hole is respectively connected to the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600.

[0031] like Figure 3-Figure 6As shown, specifically, the elastic support device for the rotor system of the present invention installs an elastic ring 200 through a bearing seat 100, and elastically supports the bearing 300 through the elastic ring 200, so that when the bearing 300 supports the rotor assembly 400, the elastic ring 200 realizes elastic support of the rotor assembly 400, thereby increasing the bending stiffness of the rotor assembly 400; in the elastic ring 200, since the outer annular surface of the annular boss 220 and the outer annular surface of the sleeve 210 are staggered in the radial direction, the annular boss 220 is staggered in the radial direction, and the annular boss 220 is staggered in the radial direction. The inner annular surface of the boss 220 and the inner annular surface of the sleeve 210 are arranged in a radially staggered manner. Therefore, the elastic ring 200 is respectively fitted with the bearing seat 100 and the bearing 300 through the complete annular surfaces on the annular boss 220 and the sleeve 210 to improve the fatigue strength reserve coefficient of the elastic ring 200; the waist-shaped hole is formed by enclosing the connecting ribs 230, the sleeve 210 and the annular boss 220. Since the multiple connecting ribs 230 are evenly arranged at intervals along the circumference of the annular boss 220, that is, the corresponding A plurality of waist-shaped holes are formed to improve the supporting stiffness of the elastic ring 200; the elastic ring 200 is enclosed by the radial outer end and the bearing seat 100 to form an outer extrusion oil film chamber 500, and the radial inner end of the elastic ring 200 is enclosed by the bearing 300 to form an inner extrusion oil film chamber 600, and the waist-shaped holes are respectively connected to the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600. Since the sleeve 210 is located between the two annular bosses 220, the connecting ribs 230 are respectively connected to the sleeve 210 and the annular boss 220. 0 connection, so that the elastic ring 200 is a centrally symmetrical structure, thereby ensuring that the oil film in the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600 is evenly stressed and has uniform oil film stiffness, thereby having a better vibration reduction effect; compared with the prior art, this solution optimizes and improves the structure of the elastic ring 200, and cooperates with the bearing 300 and the bearing seat 100, so that the elastic support is compatible with the stiffness and fatigue strength reserve coefficient, while enhancing the vibration reduction effect, has strong practicality, and is suitable for wide promotion and application.

[0032] like Figure 3-Figure 6As shown, in this embodiment, a first oil mist inlet 110 is radially opened on the bearing seat 100, and the outer annular surfaces of the two annular bosses 220 are both in contact with the bearing seat 100, so that the outer annular surface of the sleeve 210 and the bearing seat 100 are enclosed to form an external extrusion oil film chamber 500, and the first oil mist inlet 110 is symmetrically distributed along the axial center plane of the external extrusion oil film chamber 500. Specifically, since the outer ring surfaces of the two annular bosses 220 are both in contact with the inner ring surface of the bearing seat 100, and the outer ring surfaces of the annular bosses 220 and the outer ring surface of the sleeve 210 are staggered in the radial direction, the outer diameter of the annular boss 220 is larger than the outer diameter of the sleeve 210, and a radial gap is left between the outer ring surface of the sleeve 210 and the bearing seat 100 to form an outer extrusion oil film chamber 500. The first oil mist inlet 110 is symmetrically distributed along the axial center plane of the outer extrusion oil film chamber 500, and the cooling oil mist flows evenly into the outer extrusion oil film chamber 500 through the first oil mist inlet 110 in the radial direction to form an oil film with uniform force in the outer extrusion oil film chamber 500, thereby improving the vibration reduction effect.

[0033] like Figure 3-Figure 6 As shown, in this embodiment, the inner ring surface of the sleeve 210 is fitted with the bearing 300, so that the inner ring surfaces of the two annular bosses 220 and the bearing seat 100 are enclosed to form two inner extrusion oil film chambers 600, and the two extrusion oil film chambers are symmetrically distributed along the axial center plane of the outer extrusion oil film chamber 500. Specifically, since the inner ring surface of the sleeve 210 fits with the outer ring surface of the bearing 300, and the inner ring surface of the annular boss 220 and the inner ring surface of the sleeve 210 are staggered in the radial direction, the inner diameter of the annular boss 220 is larger than the inner diameter of the sleeve 210, and there are two annular bosses 220, and a radial gap is left between the two annular bosses 220 and the bearing 300 to form two inner extrusion oil film chambers 600. At the same time, since the sleeve 210 is between the two annular bosses 220, that is, the two extrusion oil film chambers are symmetrically distributed along the axial center plane of the outer extrusion oil film chamber 500, the cooling oil mist flowing into the outer extrusion oil film chamber 500 from the first oil mist inlet 110 flows evenly into the two inner extrusion oil film chambers 600 through the waist-shaped holes, so as to form an oil film with uniform force in the inner extrusion oil film chamber 600, thereby improving the vibration reduction effect.

[0034] It should be understood that, in this embodiment, after bearing the radial load of the rotor assembly 400, the sleeve 210 transfers the load to the annular bosses 220 on both sides through evenly distributed and equal-length connecting ribs 230, and the annular bosses 220 transfer the load to the bearing seat 100. Compared with the prior art, the elastic ring 200 has a uniform force distribution, a short force transmission route, and a more stable structure.

[0035] like Figure 3-Figure 6As shown, in this embodiment, the bearing seat 100 is provided with a second oil mist inlet 120 and an oil mist outlet 130 in the axial direction, and the inner cavity of the bearing 300 is respectively connected with the inner extrusion oil film chamber 600, the second oil mist inlet 120 and the oil mist outlet 130. Specifically, the cooling oil mist flows into the inner cavity of the bearing 300 through the second oil mist inlet 120, flows through the bearing 300, and then flows out through the oil mist outlet 130, thereby cooling the bearing 300. Optionally, the bearing seat 100 is provided with an exhaust hole in the radial direction that is connected with the oil mist outlet 130, and the oil mist flowing out of the oil mist outlet 130 is discharged to the outside of the bearing seat 100 through the exhaust hole.

[0036] like Figure 3 As shown, in this embodiment, the elastic support device also includes a bushing retaining ring 700 arranged in the bearing seat 100 and abutting against the annular boss 220 for cooperating with the bearing seat 100 to axially position the elastic ring 200. Specifically, the axial positioning of the elastic ring 200 is achieved by cooperating with the bushing retaining ring 700 and the bearing seat 100.

[0037] like Figure 4 As shown, in this embodiment, the number of connecting ribs 230 is 8-16. It should be understood that the number of connecting ribs 230 is proportional to the number of waist-shaped holes, and the support stiffness of the elastic ring 200 can be adjusted by adjusting the number of waist-shaped holes. Specifically, when the number of connecting ribs 230 is between 8 and 16, the support stiffness of the elastic ring 200 is appropriate, when the number of connecting ribs 230 is less than 8, the support stiffness of the elastic ring 200 is low; when the number of connecting ribs 230 is greater than 16, the structure of the elastic ring 200 is complex and the reliability is low; in addition, when the number of connecting ribs 230 is changed between 8 and 16, the structure of the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600 is also changed to achieve the purpose of adjusting the oil film stiffness.

[0038] In this embodiment, the circumferential length of the connecting rib 230 is 5mm-10mm, the radial height of the connecting rib 230 is 0.3mm-2mm, and the axial width of the connecting rib 230 is 2mm-5mm. Specifically, by changing the circumferential length of the connecting rib 230 between 5mm-10mm, changing the radial height of the connecting rib 230 between 0.3mm-2mm, and changing the axial width of the connecting rib 230 between 2mm-5mm, the length and width of the waist-shaped hole are changed by changing the parameters of the connecting rib 230, thereby adjusting the support stiffness of the elastic ring 200, and synchronously changing the structures of the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600, so as to achieve the purpose of adjusting the oil film stiffness.

[0039] In this embodiment, the radial height of the annular boss 220 is 0.5 mm-4 mm, and the axial width of the annular boss 220 is 1 mm-3 mm. Specifically, by changing the radial height of the annular boss 220 between 0.5 mm-4 mm and the axial width of the annular boss 220 between 1 mm-3 mm, the length and width of the waist-shaped hole are changed by changing the parameters of the annular boss 220, thereby adjusting the support stiffness of the elastic ring 200, and synchronously changing the structure of the inner extrusion oil film chamber 600, so as to achieve the purpose of adjusting the stiffness of the oil film.

[0040] In this embodiment, the radial height of the sleeve 210 is 0.5 mm-2 mm, the inner diameter of the sleeve 210 is 20 mm-50 mm, and the axial width of the sleeve 210 is 3 mm-10 mm. Specifically, by changing the radial height of the sleeve 210 between 0.5 mm-2 mm, changing the inner diameter of the sleeve 210 between 20 mm-50 mm, and changing the axial width of the sleeve 210 between 3 mm-10 mm, the length and width of the waist-shaped hole are changed by changing the parameters of the sleeve 210, thereby adjusting the support stiffness of the elastic ring 200, and synchronously changing the structure of the external extrusion oil film chamber 500, so as to achieve the purpose of adjusting the stiffness of the oil film.

[0041] The aircraft engine of this embodiment includes the above-mentioned elastic support device for the rotor system. Specifically, by using the above-mentioned elastic support device for the rotor system in the aircraft engine, the elastic support in the rotor system is compatible with the fatigue strength reserve coefficient and stiffness, and the stiffness adjustment range is wide and the vibration reduction effect is strong, thereby effectively realizing the adjustment of the critical speed of the rotor system.

[0042] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An elastic support device for a rotor system, characterized in that: The invention comprises a bearing seat (100), an elastic ring (200) and a bearing (300), wherein the elastic ring (200) is arranged in the bearing seat (100) and supports the bearing (300), the bearing (300) is arranged in the elastic ring (200) and is used to support a rotor assembly (400), the elastic ring (200) comprises a sleeve (210), two annular bosses (220) and a plurality of connecting ribs (230), the sleeve (210) is located between the two annular bosses (220), the connecting ribs (230) are respectively connected to the sleeve (210) and the annular boss (220), and the plurality of connecting ribs (230) are evenly arranged at intervals along the circumference of the annular boss (220). The connecting rib (230), the sleeve (210) and the annular boss (220) are enclosed to form a waist-shaped hole; the outer ring surface of the annular boss (220) and the outer ring surface of the sleeve (210) are staggered in the radial direction; the inner ring surface of the annular boss (220) and the inner ring surface of the sleeve (210) are staggered in the radial direction; the radial outer end of the elastic ring (200) and the bearing seat (100) are enclosed to form an outer extrusion oil film chamber (500); the radial inner end of the elastic ring (200) and the bearing (300) are enclosed to form an inner extrusion oil film chamber (600); and the waist-shaped hole is respectively connected to the outer extrusion oil film chamber (500) and the inner extrusion oil film chamber (600).

2. The elastic support device for a rotor system according to claim 1, characterized in that: A first oil mist inlet (110) is radially opened on the bearing seat (100), and the outer ring surfaces of the two annular bosses (220) are both in contact with the bearing seat (100) so that the outer ring surface of the sleeve (210) and the bearing seat (100) are enclosed to form an external extrusion oil film chamber (500), and the first oil mist inlet (110) is symmetrically distributed along the axial center plane of the external extrusion oil film chamber (500).

3. The elastic support device for a rotor system according to claim 2, characterized in that: The inner ring surface of the sleeve (210) fits with the bearing (300), so that the inner ring surfaces of the two annular bosses (220) and the bearing seat (100) enclose two inner extrusion oil film chambers (600), and the two extrusion oil film chambers are symmetrically distributed along the axial center plane of the outer extrusion oil film chamber (500).

4. The elastic support device for a rotor system according to any one of claims 1 to 3, characterized in that: The bearing seat (100) is provided with a second oil mist inlet (120) and an oil mist outlet (130) along the axial direction, and the inner cavity of the bearing (300) is respectively connected with the inner extrusion oil film chamber (600), the second oil mist inlet (120) and the oil mist outlet (130).

5. The elastic support device for a rotor system according to any one of claims 1 to 3, characterized in that: The elastic support device also includes a bushing retaining ring (700) disposed in the bearing seat (100) and abutting against the annular boss (220) and used for cooperating with the bearing seat (100) to axially position the elastic ring (200).

6. The elastic support device for a rotor system according to any one of claims 1 to 3, characterized in that: The number of the connecting ribs (230) is 8 to 16.

7. The elastic support device for a rotor system according to any one of claims 1 to 3, characterized in that: The circumferential length of the connecting rib (230) is 5 mm to 10 mm, the radial height of the connecting rib (230) is 0.3 mm to 2 mm, and the axial width of the connecting rib (230) is 2 mm to 5 mm.

8. The elastic support device for a rotor system according to any one of claims 1 to 3, characterized in that: The radial height of the annular boss (220) is 0.5 mm to 4 mm, and the axial width of the annular boss (220) is 1 mm to 3 mm.

9. The elastic support device for a rotor system according to any one of claims 1 to 3, characterized in that: The radial height of the sleeve (210) is 0.5 mm to 2 mm, the inner diameter of the sleeve (210) is 20 mm to 50 mm, and the axial width of the sleeve (210) is 3 mm to 10 mm.

10. An aircraft engine, characterized in that: An elastic support device for a rotor system comprising any one of claims 1-9.

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