Oil supply structure for inter-propeller bearing of contra-rotating propeller fan

Abstract

The invention belongs to the technical field of oil supply structures, and provides an oil supply structure for a bearing between paddles of a contra-rotating paddle fan, which comprises a front paddle component and a rear paddle component, and the rear paddle component is rotatably mounted on the outer side of the front paddle component through a bearing; the rear propeller component comprises a second propeller shaft, a second propeller hub and a second propeller oil cylinder which are connected in sequence; the second propeller oil cylinder and the second propeller hub are both mounted on an outer ring of the bearing; communicated lubricating oil channels are arranged in the second propeller shaft, the second propeller hub and the second propeller oil cylinder, and oil spraying openings of the lubricating oil channels directly face the bearing; lubricating oil is adopted for lubricating and cooling the bearings, lubricating of the lubricating oil between the bearings can be achieved by arranging the lubricating oil channel (namely the oil supply oil way) and the oil return cavity (namely the oil return oil way), and the lubricating oil cooling device can be applied to paddle fan engines with different thrust levels.

Description

Technical Field

[0001] This invention belongs to the field of oil supply structure technology, and specifically relates to an oil supply structure for a bearing between a counter-rotating propeller and a fan propeller. Background Technology

[0002] In a counter-rotating propfan engine, the front and rear propellers rotate coaxially in opposite directions. Bearings are designed between the front and rear propellers. Because the front and rear propellers rotate coaxially in opposite directions, the bearings need to be constantly lubricated to ensure the engine's lifespan, reliability, and operating conditions.

[0003] Existing technologies typically employ grease lubrication. Structurally, the inter-propeller bearing is located within a designed cavity, which is filled with grease during assembly. When the engine is running, the grease is used to lubricate and cool the bearing. However, although grease lubrication is relatively easy to implement structurally, it is slow to cool and cannot be replenished in a timely manner. Therefore, grease lubrication is generally used in propfan engines with relatively low thrust.

[0004] For propfan engines with high thrust, the bearings are under heavy load during operation, resulting in high heat generation. Therefore, an oil supply structure that can be lubricated by lubricating oil is required. Summary of the Invention

[0005] To address the above problems, this invention proposes an oil supply structure for a counter-rotating fan bearing, comprising a front propeller assembly and a rear propeller assembly, wherein the rear propeller assembly is rotatably mounted on the outside of the front propeller assembly via a bearing. The rear propeller assembly includes a second propeller shaft, a second propeller hub, and a second propeller cylinder connected in sequence. The second propeller cylinder and the second propeller hub are both connected to the outer ring of the bearing. The second propeller shaft, the second propeller hub, and the second propeller cylinder are all provided with communicating lubricating oil channels, and the oil injection port of the lubricating oil channel is directly opposite the bearing. The front propeller component includes a first propeller shaft and a sealing oil shaft. The inner ring of the bearing is fitted onto the outer surface of the first propeller shaft. The sealing oil shaft is installed inside the first propeller shaft, and the end of the sealing oil shaft away from the second propeller shaft is fixedly connected to the inner surface of the first propeller shaft. An oil return chamber is formed between the first propeller shaft and the sealing oil shaft. The oil return chamber is connected to the fuel injection port.

[0006] Furthermore, the bearing includes a first bearing and a second bearing, the inner rings of the first bearing and the second bearing are both fixedly installed on the outer surface of the first propeller shaft, the outer ring of the first bearing is fixedly connected to the inner wall of the second propeller cylinder, and the outer ring of the second bearing is fixedly connected to the inner wall of the second propeller hub.

[0007] Furthermore, the end of the inner ring of the first bearing away from the second bearing abuts against the protrusion of the first propeller shaft, and the end of the inner ring of the first bearing near the second bearing abuts against the oil catch nut, which is threadedly installed on the outer surface of the first propeller shaft.

[0008] Furthermore, the outer side of the oil-collecting nut is provided with an oil-collecting port, and the inner side of the oil-collecting nut is provided with an annular groove, and the oil-collecting port communicates with the annular groove; the outer surface of the first propeller shaft is provided with an oil passage hole, and the annular groove and the oil return chamber are connected through the oil passage hole.

[0009] Furthermore, the outer surface of the oil-collecting nut is provided with an oil-collecting port along the rotational tangential direction.

[0010] Furthermore, a spiral sealing ring is provided at the end of the second propeller cylinder away from the second bearing, and the spiral sealing ring rotates and seals with the outer surface of the first propeller shaft.

[0011] Furthermore, a leather cup is provided in the groove at the end of the spiral sealing ring away from the second propeller cylinder, and the leather cup rotates and seals with the outer surface of the first propeller shaft.

[0012] Furthermore, a first bearing cavity is formed between the spiral sealing ring, the second propeller cylinder, and the first propeller shaft, and the first bearing is located in the first bearing cavity. The oil injection port and the oil return cavity are both connected to the first bearing cavity.

[0013] Furthermore, a fourth lubricating oil channel is provided on the inner surface of the end of the first propeller shaft near the oil collection tank, and the fourth lubricating oil channel connects the oil return chamber and the second bearing chamber.

[0014] Furthermore, the second propeller cylinder is provided with a third lubricating oil channel, and the inner surface of the second propeller cylinder is provided with a second oil injection port, which is connected to the third lubricating oil channel; the second oil injection port is connected to the first bearing cavity, and the second oil injection port is directly opposite the first bearing.

[0015] Furthermore, the inner cavity of the first propeller shaft is tapered, and the wall thickness of the first propeller shaft on the side closer to the first bearing is greater than the wall thickness of the first propeller shaft on the side farther from the first bearing.

[0016] Furthermore, the oil supply structure also includes a reducer, wherein the output shaft of the reducer is connected to the oil sealing shaft, and the reducer is provided with a second propeller shaft; the second propeller shaft is installed on the outside of the output shaft inside the reducer.

[0017] Furthermore, a second bearing cavity is formed between the output shaft, the second propeller shaft, the first propeller shaft, and the reducer, and the oil injection port and the oil return cavity are both connected to the second bearing cavity; an oil collection tank is provided in the reducer, and the inlet of the oil collection tank is connected to the second bearing cavity.

[0018] Furthermore, the second propeller shaft has a first lubricating oil channel inside, and a first oil injection port is provided on the inner surface of the second propeller shaft. The first oil injection port is connected to the first lubricating oil channel; the first oil injection port is connected to the second bearing cavity, and the first oil injection port is directly opposite the second bearing.

[0019] Furthermore, the inner wall of the reducer is provided with a reducer stator, the reducer stator is installed on the outside of the second propeller shaft, and an oil distribution bushing is installed between the reducer stator and the second propeller shaft.

[0020] Furthermore, the interior of the second propeller hub is provided with a second lubricating oil passage, and the first lubricating oil passage, the second lubricating oil passage, and the third lubricating oil passage are connected in sequence.

[0021] The beneficial effects of this application are: 1. The oil supply structure for the propeller bearing of the present invention includes a front propeller assembly and a rear propeller assembly. The rear propeller assembly includes a second propeller shaft, a second propeller hub, and a second propeller cylinder connected in sequence. Each of the second propeller shaft, the second propeller hub, and the second propeller cylinder has a communicating oil passage, with the oil injection port of the oil passage facing the bearing. The front propeller assembly includes a first propeller shaft and a sealing shaft, with a return oil chamber formed between the first propeller shaft and the sealing shaft. The return oil chamber is connected to the oil injection port. This invention uses lubricating oil to lubricate and cool the bearing. By setting up oil passages (i.e., oil supply lines) and return oil chambers (i.e., oil return lines), lubrication between the bearings can be achieved, and it can be applied to propfan engines of different thrust levels.

[0022] 2. In the oil supply structure of the counter-rotating propeller fan bearing of the present invention, the inner ring of the first bearing, away from the second bearing, abuts against the protrusion of the first propeller shaft, and the inner ring of the first bearing, close to the second bearing, abuts against the oil catch nut. The oil catch nut is threadedly installed on the outer surface of the first propeller shaft. By limiting the inner ring of the first bearing with the oil catch nut, the first bearing is fixed and prevented from shaking during use.

[0023] 3. The oil receiving nut of the oil supply structure of the counter-rotating propeller fan bearing of the present invention has an oil receiving port on its outer surface along the rotational tangential direction; by setting the oil receiving port on the outer surface of the oil receiving nut along the rotational tangential direction, it is convenient to recover lubricating oil when the front propeller component and the rear propeller component rotate relative to each other.

[0024] 4. In the oil supply structure of the counter-rotating propeller fan bearing of the present invention, a spiral sealing ring is provided at the end of the second propeller cylinder away from the locking nut, and a leather cup is provided in the groove at the end of the spiral sealing ring away from the second propeller cylinder. The spiral sealing ring and the leather cup are rotated to seal the outer surface of the first propeller shaft; thus achieving double sealing and preventing the first bearing cavity from leaking lubricating oil.

[0025] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 A cross-sectional schematic diagram of the oil supply structure for the propeller-fan bearing in an embodiment of the present invention is shown.

[0028] Figure 2 A schematic diagram of the oil receiving nut of the oil supply structure for the propeller-fan inter-bearing in an embodiment of the present invention is shown.

[0029] Figure 3 A cross-sectional schematic diagram of the second propeller cylinder, the oil recovery nut, and the first propeller shaft of the oil supply structure for the propeller-fan inter-propeller bearing in an embodiment of the present invention is shown.

[0030] Figure 4 A schematic diagram of the spline of the first propeller shaft and the fourth lubricating oil passage of the oil supply structure for the propeller-fan inter-bearing bearing in an embodiment of the present invention is shown.

[0031] In the diagram, 1. First propeller hub; 2. First propeller shaft; 21. Oil passage hole; 3. Leather cup; 4. Spiral sealing ring; 5. Second propeller cylinder; 6. Second propeller hub; 7. First bearing; 8. Oil catch nut; 81. Oil catch port; 82. Ring groove; 9. Oil seal shaft lock nut; 10. Oil seal shaft; 11. Second propeller shaft; 12. Output shaft inside the reducer; 13. Oil distributor bushing; 14. Second bearing; 15. Reducer stator; 16. Reducer; 17. Lock nut; 31. First lubricating oil passage; 32. Second lubricating oil passage; 33. Third lubricating oil passage; 41. First fuel injector; 42. Second fuel injector; 201, Spline; 202, Fourth lubricating oil passage. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] Example 1 This invention provides an oil supply structure for a counter-rotating propeller fan bearing, comprising a first propeller hub 1, a first propeller shaft 2, a piston cup 3, a spiral sealing ring 4, a second propeller cylinder 5, a second propeller hub 6, a first bearing 7, an oil catch nut 8, an oil sealing shaft locking nut 9, an oil sealing shaft 10, a second propeller shaft 11, a reducer inner output shaft 12, an oil distribution bushing 13, a second bearing 14, a reducer stator 15, a reducer 16, and a locking nut 17. The flange edge of the first propeller hub 1 is fixedly connected to the flange edge of the first propeller shaft 2 at the end away from the reducer 16. A front propeller assembly is mounted on the outside of the first propeller hub 1. The end of the first propeller shaft 2 away from the first propeller hub 1 is fitted onto the outside of the reducer inner output shaft 12. The front propeller assembly is cantilevered on the rear propeller assembly by two bearings (first bearing 7 and second bearing 14) on the first propeller shaft 2.

[0035] Furthermore, the reducer 16 is equipped with a second propeller shaft 11, which is fixedly connected to the end of the second propeller hub 6 away from the first propeller hub 1. The outer surface of the second propeller hub 6 is fitted with a rear propeller component. The protrusion on the inner wall of the second propeller hub 6 is connected to the outer ring of the second bearing 14. The reducer 16 drives the second propeller hub 6 through the second propeller shaft 11, thereby driving the rear propeller component to rotate. The reducer 16 drives the first propeller shaft 2 through the output shaft 12 inside the reducer, thereby driving the first propeller hub 1 and the front propeller component on the first propeller hub 1 to rotate. This achieves coaxial counter-rotation between the front propeller component and the rear propeller component. The tension / thrust generated by the front propeller component is transmitted to the rear propeller component through the first bearing 7, the second propeller cylinder 5, and the second propeller hub 6.

[0036] Furthermore, the end of the first bearing 7 near the reducer 16 abuts against the oil catch nut 8, which is threaded onto the thread on the outside of the first propeller shaft 2; the oil catch nut 8 has a rotational oil catch function; the inner ring of the first bearing 7 is fixed to the front end of the first propeller shaft 2, and the outer ring of the first bearing 7 is fixedly connected to the inner wall of the second propeller cylinder 5; the second bearing 14 has its inner ring fixed to the rear end of the first propeller shaft 2 by a locking nut 17. An oil sealing shaft 10 is mounted on the inner side of the first propeller shaft 2. The oil sealing shaft 10 is fixedly connected to the first propeller shaft 2 by an oil sealing shaft locking nut 9. Specifically, the oil sealing shaft 10 is installed on the inner side of the first propeller shaft 2. The protrusion at the end of the oil sealing shaft 10 is connected to the groove on the inner side of the first propeller shaft 2. The oil sealing shaft locking nut 9 is threadedly connected to the inner side of the first propeller shaft 2, thereby limiting the oil sealing shaft 10 and fixing the first propeller shaft 2, the oil sealing shaft locking nut 9, and the oil sealing shaft 10 together. The end of the oil sealing shaft 10 away from the first bearing 7 is designed with a sealing structure with the output shaft 12 inside the reducer.

[0037] Furthermore, a second propeller cylinder 5 is mounted on the outer ring of the first bearing 7. A spiral sealing ring 4 is mounted on the end of the second propeller cylinder 5 near the first propeller hub 1. The second propeller cylinder 5, the spiral sealing ring 4, and the first propeller shaft 2 together form the first bearing cavity. The second oil injection port 42 on the second propeller cylinder 5 faces the first bearing 7, and the first bearing 7 is installed in the first bearing cavity. The first propeller shaft 2, the sealing shaft 10, and the output shaft 12 inside the reducer together form the oil return cavity, through which lubricating oil is recovered. A lip cup 3 is provided at the end of the spiral sealing ring 4 away from the first bearing 7. The lip cup 3 and the first propeller shaft 2 rotate to form a double seal, preventing lubricating oil leakage.

[0038] refer to Figure 1 The oil distributor bushing 13 is fitted onto the end of the second propeller shaft 11 near the reducer 16. The oil distributor bushing 13 is also fitted onto the inner side of the reducer stator 15. The reducer stator 15 is fixedly connected to the reducer 16, and the oil distributor bushing 13 is sealed to the reducer stator 15 and the second propeller shaft 11. The oil distributor bushing 13 is a rotor component. A sealing structure is designed between the oil distributor bushing 13 and the reducer stator 15. During operation, lubricating oil from the control system accessories enters the reducer stator 15 and then flows to the oil distributor bushing 13. After the lubricating oil passes through the oil distributor bushing 13 to achieve the conversion between the rotor component and the stator component, it enters... The lubricating oil enters the first lubricating oil channel 31 on the second propeller shaft 11. A portion of the lubricating oil is sprayed through the first oil spray port 41 on the second propeller shaft 11 to lubricate the second bearing 14. The lubricating oil cooling the second bearing 14 directly enters the output shaft 12 and the second propeller shaft 11 in the reducer, and finally enters the oil collection pool of the reducer 16. A portion of the lubricating oil is sequentially transferred along the second lubricating oil channel 32 of the second propeller hub 6 and the third lubricating oil channel 33 on the reinforcing rib of the second propeller cylinder 5 to the second oil spray port 42 of the second propeller cylinder 5 facing the first bearing 7. The lubricating oil is sprayed through the second oil spray port 42 of the second propeller cylinder 5 to lubricate the first bearing 7.

[0039] refer to Figure 2 The outer side of the oil-collecting nut 8 is designed with an oil-collecting port 81 along the tangential direction of rotation (the number is designed according to needs), and the inner side is designed with an annular groove 82 communicating with the oil-collecting port 81. The first propeller shaft 2 corresponding to the annular groove 82 is designed with an oil passage hole 21 (the number is designed according to needs). During operation, the oil-collecting port 81 collects oil by the counter-rotation between the front and rear propellers. The lubricating oil in the first bearing cavity flows along the oil-collecting port 81 to the annular groove 82 and then to the oil passage hole 21, and enters the return oil chamber inside the first propeller shaft 2 through the oil passage hole 21. The inner side of the first propeller shaft 2 is designed with a conical structure. Under the action of centrifugal force, the lubricating oil flows backward along the inner side of the first propeller shaft 2, reaching the spline 201 of the first propeller shaft 2 and the spline 201 of the output shaft 12 in the reducer, where the spline 201 is mated, cooling the spline 201, and then flowing out through the fourth lubricating oil channel 202 between the splines 201 (see reference). Figure 4It enters between the second propeller shaft 11 and the output shaft 12 inside the reducer, and finally enters the oil collection sump of the reducer 16.

[0040] Example 2 refer to Figure 1 An oil supply structure for a counter-rotating fan bearing includes a front propeller assembly and a rear propeller assembly. The rear propeller assembly is rotatably mounted on the outside of the front propeller assembly via a bearing. The front and rear propeller assemblies are coaxially mounted. The rear propeller assembly includes a second propeller shaft 11, a second propeller hub 6, and a second propeller cylinder 5 connected in sequence. Both the second propeller cylinder 5 and the second propeller hub 6 are connected to the outer ring of the bearing. The second propeller shaft 11, the second propeller hub 6, and the second propeller cylinder 5 are all provided with communicating oil channels, and the oil nozzles of the oil channels are directly facing the bearing. Oil is supplied through the oil channels to cool and lubricate the bearing.

[0041] Furthermore, the front propeller assembly includes a first propeller shaft 2 and an oil sealing shaft 10. A bearing inner ring is fitted onto the outer surface of the first propeller shaft 2, and the oil sealing shaft 10 is installed inside the first propeller shaft 2. The end of the oil sealing shaft 10 furthest from the second propeller shaft 11 is fixedly connected to the inner surface of the first propeller shaft 2, forming an oil return chamber between the first propeller shaft 2 and the oil sealing shaft 10. The oil return chamber communicates with the fuel injection port. Oil return through the oil return chamber ensures the integrity of the oil circuit, thereby achieving circulating oil supply and cooling.

[0042] This application uses lubricating oil to lubricate and cool the bearings. By setting up lubricating oil channels (i.e., oil supply lines) and oil return chambers (i.e., oil return lines), lubricating oil can be achieved between the bearings, and it can be applied to propfan engines with different thrust levels.

[0043] In this application, the bearings include a first bearing 7 and a second bearing 14. The inner rings of the first bearing 7 and the second bearing 14 are both fixedly installed on the outer surface of the first propeller shaft 2. The outer ring of the first bearing 7 is fixedly connected to the inner wall of the second propeller cylinder 5, and the outer ring of the second bearing 14 is fixedly connected to the inner wall of the second propeller hub 6.

[0044] The counter-rotating propeller's front blade is cantilevered at both ends of the rear blade via two bearings (first bearing 7 and second bearing 14) to achieve coaxial counter-rotation between the front and rear blades during operation, and to transmit the thrust / pull generated by the front blade. During operation, the bearings (first bearing 7 and second bearing 14) bear motor loads, aerodynamic loads, unbalanced loads, etc. The thrust / pull generated by the front blade is also transmitted to the rear blade through the ball bearings within them. Therefore, the bearings are under heavy load during operation, requiring the design of a lubricating oil cooling structure. Since the bearings are arranged between the front and rear blades, both of which are rotating components without a stator casing on the outside, the lubricating oil from the reducer stator component 15 needs to be switched between the rotating and stator components and then passed through the rotating rear blade to be delivered to the bearings for oil supply. The lubricating oil in the bearing cavity needs to pass through the coaxially rotating front and rear blades before entering the reducer 16, and finally reaching the oil collection sump of the reducer 16.

[0045] refer to Figure 1 The inner ring of the first bearing 7, at the end furthest from the second bearing 14, abuts against the protrusion of the first propeller shaft 2, while the inner ring of the first bearing 7, at the end closest to the second bearing 14, abuts against the oil catch nut 8. The oil catch nut 8 is threaded onto the outer surface of the first propeller shaft 2. By limiting the inner ring of the first bearing 7 with the oil catch nut 8, the first bearing 7 is fixed, preventing it from shaking during use.

[0046] refer to Figure 2 The oil catch nut 8 has an oil catch port 81 on its outer side and an annular groove 82 on its inner side, with the oil catch port 81 communicating with the annular groove 82. The outer surface of the first propeller shaft 2 has an oil passage hole 21, which connects the annular groove 82 and the oil return chamber. By providing an oil catch port 81 on the outer side of the oil catch nut 8, and by connecting the oil catch port 81 with the oil return chamber through the annular groove 82 and the oil passage hole 21, lubricating oil recovery is achieved.

[0047] refer to Figure 3 The outer surface of the oil recovery nut 8 is provided with an oil recovery port 81 along the rotational tangential direction. By setting the oil recovery port 81 on the outer surface of the oil recovery nut 8 along the rotational tangential direction, it is easier to recover lubricating oil when the front propeller assembly and the rear propeller assembly rotate relative to each other.

[0048] refer to Figure 1 A spiral sealing ring 4 is provided at the end of the second propeller cylinder 5 away from the second bearing 14. The spiral sealing ring 4 is fixedly connected to the end face of the second propeller cylinder 5, and the spiral sealing ring 4 rotates and seals against the outer surface of the first propeller shaft 2. By providing the spiral sealing ring 4, the first bearing 7 is sealed, preventing lubricating oil leakage.

[0049] Furthermore, a cup 3 is provided in the groove at the end of the spiral sealing ring 4 away from the second propeller cylinder 5, and the cup 3 rotates and seals with the outer surface of the first propeller shaft 2. By providing a cup 3 on the outside of the spiral sealing ring 4, a secondary seal is achieved for the first bearing 7, thereby achieving a double seal and preventing oil leakage from the first bearing cavity.

[0050] In the above embodiments, another optional implementation is that a first bearing cavity is formed between the spiral sealing ring 4, the second propeller cylinder 5, and the first propeller shaft 2, and the first bearing 7 is located in the first bearing cavity. The oil injection port and the oil return chamber are both connected to the first bearing cavity. By providing a first bearing cavity on the outside of the first bearing 7, it is convenient for lubricating oil to lubricate the first bearing 7, thereby enabling the first bearing 7 to be quickly lubricated and its temperature reduced.

[0051] Furthermore, the second propeller cylinder 5 is provided with a third lubricating oil channel 33, and the inner surface of the second propeller cylinder 5 is provided with a second oil injection port 42, which is connected to the third lubricating oil channel 33; the second oil injection port 42 is connected to the first bearing cavity, and the second oil injection port 42 is directly facing the first bearing 7. By having the second oil injection port 42 directly facing the first bearing 7, rapid lubrication and cooling of the first bearing 7 are achieved.

[0052] In the above embodiments, another optional implementation is that the inner cavity of the first propeller shaft 2 is conical, and the wall thickness of the side of the first propeller shaft 2 closest to the first bearing 7 is greater than the wall thickness of the side of the first propeller shaft 2 furthest from the first bearing 7. Specifically, the lubricating oil channel is also conical when the inner cavity of the first propeller shaft 2 is conical, thereby enabling the lubricating oil to flow backward along the inner side of the first propeller shaft 2 under the action of centrifugal force, reaching the spline 201 of the first propeller shaft 2 and the spline 201 of the output shaft 12 in the reducer, cooling the spline 201, and entering the space between the second propeller shaft 11 and the output shaft 12 in the reducer from the gap of the spline 201 and the reserved fourth lubricating oil channel 202, and finally entering the oil collection tank of the reducer 16.

[0053] refer to Figure 1 The oil supply structure also includes a reducer 16. The internal output shaft 12 of the reducer 16 is connected to the first propeller shaft 2. The reducer 16 is provided with a second propeller shaft 11 (i.e., the external output shaft of the reducer 16). The second propeller shaft 11 is installed outside the internal output shaft 12 of the reducer. By providing the internal output shaft 12 and the external shaft, the reducer 16 enables the coaxial and counter-rotating of the front propeller component and the rear propeller component.

[0054] In the above embodiments, another optional implementation is that a second bearing cavity is formed between the output shaft 12, the second propeller shaft 11, the first propeller shaft 2, and the reducer 16, and both the oil injection port and the oil return cavity are connected to the second bearing cavity; an oil collection tank is provided in the reducer 16, and the inlet of the oil collection tank is connected to the second bearing cavity. By providing a second bearing cavity outside the second bearing 14, lubricating oil can be conveniently used to lubricate the second bearing 14, thereby enabling rapid lubrication and temperature reduction of the second bearing 14. At the same time, the second bearing cavity is connected to the oil collection tank, thereby realizing the recovery of lubricating oil.

[0055] Furthermore, a fourth lubricating oil channel 202 is provided on the inner surface of the end of the first propeller shaft 2 near the oil collection tank, and the fourth lubricating oil channel 202 connects the oil return chamber and the second bearing chamber.

[0056] Furthermore, the second propeller shaft 11 has a first lubricating oil channel 31 inside, and a first oil injection port 41 is provided on the inner surface of the second propeller shaft 11, which communicates with the first lubricating oil channel 31; the first oil injection port 41 communicates with the second bearing cavity, and the first oil injection port 41 is directly facing the second bearing 14. By having the first oil injection port 41 directly facing the second bearing 14, rapid lubrication and cooling of the second bearing 14 are achieved.

[0057] In this application, a reducer stator 15 is provided on the inner wall of the reducer 16. The reducer stator 15 is installed on the outer side of the second propeller shaft 11. An oil distribution bushing 13 is installed between the reducer stator 15 and the second propeller shaft 11. The outlet of the oil collection sump passes through holes on the reducer stator 15 and the oil distribution bushing 13 and communicates with the first lubricating oil channel 31. By providing the oil distribution bushing 13, a rotatable connection between the reducer 16 and the first lubricating oil channel 31 is achieved.

[0058] In this application, the second propeller hub 6 is provided with a second lubricating oil passage 32, and the first lubricating oil passage 31, the second lubricating oil passage 32, and the third lubricating oil passage 33 are connected in sequence. Specifically, the lubricating oil passage includes the first lubricating oil passage 31, the second lubricating oil passage 32, and the third lubricating oil passage 33 connected in sequence.

[0059] During engine operation, the lubricating oil from the stator component 15 of the reducer is transferred to the first lubricating oil passage 31 of the rotating second propeller shaft 11. The lubricating oil is then delivered to the first bearing 7 via the second lubricating oil passage 32 and the third lubricating oil passage 33. After cooling the first bearing 7, the lubricating oil is recovered into the return oil chamber via the oil recovery nut 8. The return oil chamber then enters the oil collection pool of the reducer 16 through the second bearing chamber, thus achieving lubrication and cooling of the first bearing 7 and the second bearing 14. For high-thrust propfan engines with large bearing loads and long service lives, this structure is more suitable than existing grease lubrication methods.

[0060] Although this application 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; and these 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 this application.

Claims

1. An oil supply structure for an inter-fan bearing of a contra-rotating fan, characterized by, The front paddle part and the rear paddle part are rotatably connected through a bearing; The rear paddle part comprises a second paddle shaft (11), a second paddle hub (6) and a second paddle oil cylinder (5) connected in sequence, and the second paddle oil cylinder (5) and the second paddle hub (6) are connected with the outer ring of the bearing; the second paddle shaft (11), the second paddle hub (6) and the second paddle oil cylinder (5) are provided with oil passages in communication, and the oil injection port of the oil passage is opposite to the bearing. The front paddle part comprises a first paddle shaft (2) and an oil sealing shaft (10), the inner ring of the bearing is sleeved on the outer surface of the first paddle shaft (2), the oil sealing shaft (10) is installed inside the first paddle shaft (2), and the end of the oil sealing shaft (10) away from the second paddle shaft (11) is fixedly connected with the inner surface of the first paddle shaft (2), and the oil return cavity is formed between the first paddle shaft (2) and the oil sealing shaft (10); the oil return cavity is in communication with the oil injection port.

2. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 1, characterized in that, The bearing comprises a first bearing (7) and a second bearing (14), the inner rings of the first bearing (7) and the second bearing (14) are fixedly installed on the outer surface of the first paddle shaft (2), the outer ring of the first bearing (7) is fixedly connected with the inner wall of the second paddle oil cylinder (5), and the outer ring of the second bearing (14) is fixedly connected with the inner wall of the second paddle hub (6).

3. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 2, characterized in that, The end of the inner ring of the first bearing (7) away from the second bearing (14) is in abutment with the protrusion of the first paddle shaft (2), and the end of the inner ring of the first bearing (7) close to the second bearing (14) is in abutment with the oil collecting nut (8), and the oil collecting nut (8) is threadedly installed on the outer surface of the first paddle shaft (2).

4. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 3, characterized in that, The outer side of the oil collecting nut (8) is provided with an oil collecting port (81), the inner side of the oil collecting nut (8) is provided with an annular groove (82), and the oil collecting port (81) is in communication with the annular groove (82); the outer surface of the first paddle shaft (2) is provided with an oil passage hole (21), and the annular groove (82) and the oil return cavity are in communication through the oil passage hole (21).

5. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 4, characterized in that, The outer surface of the oil collecting nut (8) is provided with an oil collecting port (81) in a rotating tangential direction.

6. An oil supply structure for a counter-rotating fan and propeller inter-shaft bearing according to any one of claims 2 to 5, characterized in that, The end of the second paddle oil cylinder (5) away from the second bearing (14) is provided with a spiral sealing ring (4), and the spiral sealing ring (4) is rotatably sealed with the outer surface of the first paddle shaft (2).

7. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 6, characterized in that, The groove of the end of the spiral sealing ring (4) away from the second paddle oil cylinder (5) is provided with a leather cup (3), and the leather cup (3) is rotatably sealed with the outer surface of the first paddle shaft (2).

8. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 6, characterized in that, The spiral sealing ring (4), the second paddle oil cylinder (5) and the first paddle shaft (2) form a first bearing cavity, the first bearing (7) is located in the first bearing cavity, and the oil injection port and the oil return cavity are in communication with the first bearing cavity.

9. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 8, characterized in that, The second paddle oil cylinder (5) is provided with a third oil passage (33), the inner surface of the second paddle oil cylinder (5) is provided with a second oil injection port (42), the second oil injection port (42) is in communication with the third oil passage (33); the second oil injection port (42) is in communication with the first bearing cavity, and the second oil injection port (42) is opposite to the first bearing (7).

10. The oil supply structure for a counter-rotating fan / propeller inter-shaft bearing according to claim 1 or 2, characterized by The inner cavity of the first paddle shaft (2) is conical, and the wall thickness of the side of the first paddle shaft (2) close to the first bearing (7) is greater than the wall thickness of the side of the first paddle shaft (2) away from the first bearing (7).

11. The oil supply structure for a counter-rotating fan / propeller inter-shaft bearing according to claim 1 or 2, characterized by The oil supply structure further comprises a reducer (16), an inner output shaft (12) of the reducer (16) is in transmission connection with the first paddle shaft (2), and the reducer (16) is provided with a second paddle shaft (11); the second paddle shaft (11) is installed on the outer side of the inner output shaft (12) of the reducer.

12. The oil supply structure for a counter-rotating fan / propeller inter-shaft bearing according to claim 11, characterized by The inner output shaft (12) of the reducer, the second paddle shaft (11), the first paddle shaft (2) and the reducer (16) form a second bearing cavity, and the oil injection port and the oil return cavity are in communication with the second bearing cavity; an oil collecting pool is arranged in the reducer (16), and an inlet of the oil collecting pool is in communication with the second bearing cavity.

13. The oil supply structure for a counter-rotating fan / propeller inter-shaft bearing according to claim 12, characterized by The inner surface of one end of the first paddle shaft (2) close to the oil collecting pool is provided with a fourth oil passage (202), and the fourth oil passage (202) is in communication with the oil return cavity and the second bearing cavity.

14. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 12, characterized in that, The second paddle shaft (11) is internally provided with a first oil passage (31); the inner surface of the second paddle shaft (11) is provided with a first oil injection port (41), the first oil injection port (41) is in communication with the first oil passage (31); the first oil injection port (41) is in communication with the second bearing cavity, and the first oil injection port (41) is opposite to the second bearing (14).

15. The oil supply structure for a counter-rotating fan / propeller inter-shaft bearing according to claim 12 or 14, characterized by The inner wall of the reducer (16) is provided with a reducer stator (15), the reducer stator (15) is installed on the outer side of the second paddle shaft (11), and a oil distribution bushing (13) is installed between the reducer stator (15) and the second paddle shaft (11).

16. The oil supply structure for the inter-shaft bearing of a contra-rotating fan / propeller according to claim 14, characterized in that, The second paddle hub (6) is internally provided with a second oil passage (32), and the first oil passage (31), the second oil passage (32) and the third oil passage (33) are in sequence.

Images