Rotor system elastic support device and aeroengine

Abstract

The application discloses a kind of elastic supporting device for rotor system and aero-engine, including bearing seat, elastic ring and bearing, elastic ring is arranged in bearing seat and supports bearing, bearing is arranged in elastic ring and is used to support rotor assembly, elastic ring includes sleeve, two annular bosses and multiple connecting ribs, sleeve is between two annular bosses, connecting rib is connected with sleeve and annular boss respectively, multiple connecting ribs are evenly arranged along the circumference of annular boss, connecting rib, sleeve and annular boss form a waist-shaped hole, the outer ring surface of annular boss and the outer ring surface of sleeve are misaligned in radial direction, the inner ring surface of annular boss and the inner ring surface of sleeve are misaligned in radial direction, the radial outer end of elastic ring and bearing seat form outer extrusion oil film chamber, the radial inner end of elastic ring and bearing form inner extrusion oil film chamber, waist-shaped hole is communicated with outer extrusion oil film chamber and inner extrusion oil film chamber respectively.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a resilient support device for a rotor system. Furthermore, this invention also relates to an aero-engine including the aforementioned resilient support device for a rotor system. Background Technology

[0002] For small and medium-sized aero 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 distance between the pivot points, the method of increasing the bending stiffness of the rotor is usually adopted.

[0003] Currently, the most effective and feasible way to increase the bending stiffness of rotor assemblies is usually to install elastic ring-type elastic supports in the rotor system, which have the characteristics of simple structure, light weight and small space occupation.

[0004] However, as Figure 1 and Figure 2 As shown, existing elastic ring bearings are mainly divided into two categories: toothed elastic rings and elastic rings with internal and external bosses. However, within the limited space of the rotor system, toothed elastic rings and elastic rings with internal and external bosses often exhibit characteristics of incompatibility between stiffness and strength, resulting in poor vibration reduction. Generally speaking, the contact surface of toothed elastic rings is not a complete ring, which easily leads to tooth breakage. When the stiffness value is qualified, the fatigue strength reserve coefficient is low. On the other hand, elastic rings with internal and external bosses have a high stiffness value when the fatigue strength reserve coefficient is qualified. Furthermore, since toothed elastic rings have a notch and elastic rings with internal and external bosses have two bosses, neither of them has a central symmetry feature in terms of structure. This leads to uneven stress on the oil film in the oil film chamber formed within the rotor system, uneven oil film stiffness, and poor vibration reduction effect. Summary of the Invention

[0005] This invention provides an elastic support device for a rotor system and an aero-engine to solve the technical problems of incompatibility between the elastic support stiffness and fatigue strength reserve coefficient in existing rotor systems, and poor vibration reduction effect.

[0006] According to one aspect of the present invention, an elastic support device for a rotor system is provided, comprising a bearing housing, an elastic ring, and a bearing. The elastic ring is disposed within the bearing housing and supports the bearing. The bearing is disposed within the elastic ring and supports a rotor assembly. The elastic ring includes 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 bosses. The plurality of connecting ribs are evenly spaced along the circumference of the annular bosses. The connecting ribs, the sleeve, and the annular bosses enclose a waist-shaped hole. The outer annular surface of the annular bosses and the outer annular surface of the sleeve are offset in the radial direction. The inner annular surface of the annular bosses and the inner annular surface of the sleeve are offset in the radial direction. The radially outer end of the elastic ring and the bearing housing enclose an outer extrusion oil film chamber. The radially inner end of the elastic ring and the bearing enclose an inner extrusion oil film chamber. The waist-shaped hole communicates with the outer extrusion oil film chamber and the inner extrusion oil film chamber, respectively.

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

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

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

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

[0011] Furthermore, the elastic support device also includes a bushing retainer ring disposed within the bearing housing and abutting against the annular boss, which is used to cooperate with the bearing housing to axially position the elastic ring.

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

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

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

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

[0016] According to another aspect of the invention, an aircraft engine is also provided, which includes the above-described resilient support device for a rotor system.

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

[0018] The rotor system elastic support device of the present invention uses an elastic ring mounted on a bearing housing to provide elastic support for the bearing. This increases the bending stiffness of the rotor assembly by providing elastic support when the bearing supports the rotor assembly. In the elastic ring, the outer annular surface of the annular boss and the outer annular surface of the sleeve are radially misaligned, as are the inner annular surface of the annular boss and the inner annular surface of the sleeve. Therefore, the elastic ring fits against the bearing housing and the bearing respectively through the complete annular surfaces of the annular boss and the sleeve, thereby improving the fatigue strength reserve coefficient of the elastic ring. A waist-shaped hole is formed by the connecting ribs, the sleeve, and the annular boss. Since multiple connecting ribs are evenly spaced along the circumference of the annular boss, multiple waist-shaped holes are correspondingly formed on the elastic ring, thereby improving the... The elastic ring improves its support stiffness. The elastic ring forms an outer extrusion oil film chamber by its radially outer end and the bearing housing, while its radially inner end forms an inner extrusion oil film chamber by the bearing. A waist-shaped hole connects to both the outer and inner extrusion oil film chambers. Because the sleeve is located between two annular bosses, and the connecting ribs connect to both the sleeve and the annular bosses, the elastic ring has a centrally symmetrical structure. This ensures uniform stress and stiffness of the oil film within both the outer and inner extrusion oil film chambers, resulting in better vibration reduction. Compared to existing technologies, this solution optimizes the structure of the elastic ring and, in conjunction with the bearing and bearing housing, enhances the vibration reduction effect while maintaining both stiffness and fatigue strength reserve coefficients. It is highly practical and suitable for widespread promotion and application.

[0019] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

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

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

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

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

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

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

[0027] Legend:

[0028] 100, Bearing housing; 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, External extrusion oil film chamber; 600, Internal extrusion oil film chamber; 700, Bushing retaining ring. Detailed Implementation

[0029] The embodiments of the present invention will be 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 Figures 3-6 As shown, the rotor system elastic support device of this embodiment includes a bearing housing 100, an elastic ring 200, and a bearing 300. The elastic ring 200 is disposed within the bearing housing 100 and supports the bearing 300. The bearing 300 is disposed within the elastic ring 200 and supports the rotor assembly 400. The elastic ring 200 includes a sleeve 210, two annular bosses 220, and multiple 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 bosses 220. The multiple connecting ribs 230 are spaced apart circumferentially along the annular bosses 220. The connecting ribs 230, sleeve 210, and annular boss 220 are evenly arranged 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 form an outer extrusion oil film chamber 500. The radial inner end of the elastic ring 200 and the bearing 300 form an inner extrusion oil film chamber 600. The waist-shaped hole is connected to the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600, respectively.

[0031] like Figures 3-6As shown, specifically, the rotor system elastic support device of the present invention uses an elastic ring 200 mounted on a bearing housing 100 to provide elastic support for the bearing 300. This elastic ring 200 provides elastic support for the rotor assembly 400 when the bearing 300 supports the rotor assembly 400, thereby increasing the bending stiffness of the rotor assembly 400. In the elastic ring 200, because the outer annular surface of the annular boss 220 and the outer annular surface of the sleeve 210 are misaligned in the radial direction, the annular... The inner annular surfaces of the boss 220 and the sleeve 210 are offset in the radial direction. Therefore, the elastic ring 200 fits against the bearing housing 100 and the bearing 300 respectively through the complete annular surfaces on the annular boss 220 and the sleeve 210, thereby improving the fatigue strength reserve coefficient of the elastic ring 200. A waist-shaped hole is formed by the connecting ribs 230, the sleeve 210, and the annular boss 220. Since multiple connecting ribs 230 are evenly spaced along the circumference of the annular boss 220, the corresponding... Multiple oblong holes are formed to improve the support stiffness of the elastic ring 200. The elastic ring 200 forms an outer extrusion oil film chamber 500 by enclosing the outer radial end and the bearing housing 100, and forms an inner extrusion oil film chamber 600 by enclosing the inner radial end of the elastic ring 200 and the bearing 300. The oblong holes communicate with the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600, respectively. 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 bosses 220. The zero-connection design makes the elastic ring 200 a centrally symmetrical structure, thus ensuring uniform force and stiffness of the oil film in the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600, resulting in better vibration reduction. Compared with the existing technology, this solution optimizes and improves the structure of the elastic ring 200, and, in conjunction with the bearing 300 and bearing seat 100, enhances the vibration reduction effect while maintaining the elastic support's stiffness and fatigue strength reserve coefficient. It is highly practical and suitable for widespread promotion and application.

[0032] like Figures 3-6As shown, in this embodiment, a first oil mist inlet 110 is radially provided on the bearing housing 100, and the outer ring surfaces of the two annular bosses 220 are in contact with the bearing housing 100 so that the outer ring surface of the sleeve 210 and the bearing housing 100 enclose to form an external extrusion oil film chamber 500. The first oil mist inlet 110 is symmetrically distributed along the axial center surface 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 surfaces of the bearing housing 100, and the outer ring surfaces of the annular bosses 220 and the outer ring surfaces of the sleeve 210 are offset in the radial direction, the outer diameter of the annular bosses 220 is larger than the outer diameter of the sleeve 210. A radial gap is left between the outer ring surface of the sleeve 210 and the bearing housing 100 to form an external extrusion oil film chamber 500. The first oil mist inlet 110 is symmetrically distributed along the axial center surface of the external extrusion oil film chamber 500. The cooling oil mist flows evenly into the external extrusion oil film chamber 500 radially through the first oil mist inlet 110 to form a uniformly stressed oil film in the external extrusion oil film chamber 500, thereby improving the vibration damping effect.

[0033] like Figures 3-6 As shown, in this embodiment, the inner annular surface of the sleeve 210 is in contact with the bearing 300 so that the inner annular surfaces of the two annular bosses 220 and the bearing seat 100 enclose to form two inner extrusion oil film chambers 600. The two extrusion oil film chambers are symmetrically distributed along the axial center surface of the outer extrusion oil film chamber 500. Specifically, since the inner ring surface of the sleeve 210 is in contact 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 offset in the radial direction, the inner diameter of the annular boss 220 is larger than the inner diameter of the sleeve 210, resulting in two annular bosses 220. 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 symmetrically distributed between the two annular bosses 220, i.e., the two extrusion oil film chambers are symmetrically distributed along the axial center surface 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 hole, so as to form a uniformly stressed oil film in the inner extrusion oil film chambers 600 to improve 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 transmits the load to the annular bosses 220 on both sides through the evenly distributed connecting ribs 230. The annular bosses 220 then transmit the load to the bearing housing 100. Compared with the prior art, the elastic ring 200 has a more uniform force distribution, a shorter force transmission path, and a more stable structure.

[0035] like Figures 3-6As shown, in this embodiment, the bearing housing 100 has a second oil mist inlet 120 and an oil mist outlet 130 along the axial direction. The inner cavity of the bearing 300 is connected to the inner extrusion oil film chamber 600, the second oil mist inlet 120, and the oil mist outlet 130, respectively. Specifically, 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 achieving cooling of the bearing 300. Optionally, the bearing housing 100 has an exhaust hole along the radial direction that communicates with the oil mist outlet 130. The oil mist flowing out from the oil mist outlet 130 is discharged to the outside of the bearing housing 100 through the exhaust hole.

[0036] like Figure 3 As shown, in this embodiment, the elastic support device further includes a bushing retainer ring 700 disposed within the bearing housing 100 and abutting against the annular boss 220, for axially positioning the elastic ring 200 in cooperation with the bearing housing 100. Specifically, the axial positioning of the elastic ring 200 is achieved through the cooperation between the bushing retainer ring 700 and the bearing housing 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 directly proportional to the number of oblong holes, and the support stiffness of the elastic ring 200 can be adjusted by adjusting the number of oblong 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 its reliability is low. Furthermore, changing the number of connecting ribs 230 between 8 and 16 also changes the structure of the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600 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 is 0.3mm-2mm, and the axial width is 2mm-5mm. Specifically, by changing the circumferential length of the connecting rib 230 between 5mm-10mm, the radial height between 0.3mm-2mm, and the axial width between 2mm-5mm, the length and width of the oblong hole are changed by altering the parameters of the connecting rib 230, thereby adjusting the support stiffness of the elastic ring 200. Simultaneously, the structures of the outer extrusion oil film chamber 500 and the inner extrusion oil film chamber 600 are changed to achieve the purpose of adjusting the oil film stiffness.

[0039] In this embodiment, the radial height of the annular boss 220 is 0.5mm-4mm, and the axial width of the annular boss 220 is 1mm-3mm. Specifically, by changing the radial height of the annular boss 220 between 0.5mm-4mm and the axial width of the annular boss 220 between 1mm-3mm, 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 simultaneously changing the structure of the inner extrusion oil film chamber 600 to achieve the purpose of adjusting the oil film stiffness.

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

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

[0042] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An elastic support device for a rotor system, characterized in that, The assembly includes a bearing housing (100), an elastic ring (200), and a bearing (300). The elastic ring (200) is disposed within the bearing housing (100) and supports the bearing (300). The bearing (300) is disposed within the elastic ring (200) and supports the rotor assembly (400). The elastic ring (200) includes a sleeve (210), two annular bosses (220), and multiple 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 bosses (220) respectively. The multiple connecting ribs (230) are evenly spaced along the circumference of the annular bosses (220). The connecting rib (230), sleeve (210) and annular boss (220) surround 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 offset in the radial direction. The inner ring surface of the annular boss (220) and the inner ring surface of the sleeve (210) are offset in the radial direction. The radial outer end of the elastic ring (200) and the bearing seat (100) surround to form an outer extrusion oil film chamber (500). The radial inner end of the elastic ring (200) and the bearing (300) surround to form an inner extrusion oil film chamber (600). The waist-shaped hole is connected to the outer extrusion oil film chamber (500) and the inner extrusion oil film chamber (600) respectively.

2. The elastic support device for a rotor system according to claim 1, characterized in that, The bearing housing (100) has a first oil mist inlet (110) radially provided. The outer ring surfaces of the two annular bosses (220) are in contact with the bearing housing (100) so that the outer ring surface of the sleeve (210) and the bearing housing (100) enclose to form an external extrusion oil film chamber (500). The first oil mist inlet (110) is symmetrically distributed along the axial center surface 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 against the bearing (300) so that the inner ring surfaces of the two annular bosses (220) and the bearing housing (100) enclose to form two inner extrusion oil film chambers (600), and the two extrusion oil film chambers are symmetrically distributed along the axial center surface of the outer extrusion oil film chamber (500).

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

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

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

7. The elastic support device for a rotor system according to any one of claims 1-3, characterized in that, 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.

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

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

10. An aircraft engine, characterized in that, Includes the elastic support device for rotor systems as described in any one of claims 1-9.

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