Turbine device with oil-gas separation structure and aero-engine

Abstract

The invention discloses a turbine device with an oil-gas separation structure and an aero-engine, the turbine device with the oil-gas separation structure comprises a turbine shaft, a transmission shaft, a first bearing, a first bearing seat and an oil-gas separation ring, the periphery of the turbine shaft is sleeved with the transmission shaft, and a lubricating oil cavity is formed in the space between the first bearing seat and the turbine shaft; a first exhaust cavity is defined between the oil-gas separation ring and the transmission shaft, a second exhaust cavity is defined between the transmission shaft and the turbine shaft, oil-gas separation holes are distributed in the oil-gas separation ring, and the oil-gas separation holes communicate the lubricating oil cavity with the first exhaust cavity; a first vent hole is formed in the transmission shaft, and the first exhaust cavity is communicated with the second exhaust cavity through the first vent hole; a second vent hole is formed in the second end, corresponding to the second exhaust cavity, of the turbine shaft, and the second exhaust cavity is communicated with a central shaft hole of the turbine shaft through the second vent hole. The turbine device with the oil-gas separation structure is provided with the oil-gas separation structure, and multi-stage oil-gas separation operation can be achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of oil-gas separation of aircraft engines, and in particular to a turbine device with an oil-gas separation structure, and an aircraft engine using the turbine device with the oil-gas separation structure. Background Art

[0002] At present, since the bearings of aircraft engines generate a lot of heat during high-speed rotation, effective measures need to be taken to cool them, otherwise the bearings will fail quickly after the temperature rises. In this regard, the commonly used bearing cooling method is to use a closed lubricating oil system for cooling. By arranging a bearing cavity around the bearing, injecting lubricating oil into the bearing cavity and allowing the lubricating oil to flow as required, the bearing cooling is achieved. Secondly, in order to prevent the lubricating oil in the bearing cavity from leaking to the turbine disc cavity and other parts and causing accidents such as lubricating oil combustion, it is necessary to seal the outer periphery of the bearing cavity with sealed cold air at a certain pressure. The sealed cold air will inevitably enter the bearing cavity under high pressure, and the air in the bearing cavity will mix with the lubricating oil to form oil gas. If the oil-gas mixture is directly discharged from the bearing cavity, it will lead to a large consumption of lubricating oil.

[0003] Therefore, before the oil-gas mixture in the aircraft engine lubricating oil system is discharged from the bearing system, an oil-gas separation device needs to be set up to separate the lubricating oil for recycling to reduce the lubricating oil consumption. However, conventional oil-gas separation devices require a dedicated ventilation transmission system or an independent oil-gas separation component, which requires a large installation space. As aircraft engines gradually require miniaturized designs, it is difficult to arrange an effective oil-gas separation device in the turbine bearing cavity due to space constraints. Summary of the invention

[0004] The present invention provides a turbine device with an oil-gas separation structure to solve the technical problem that it is difficult to achieve a good oil-gas separation effect while realizing a miniaturized design in the existing turbine bearing cavity.

[0005] The present invention also provides an aero-engine, which adopts the turbine device with the oil-gas separation structure.

[0006] According to one aspect of the present invention, a turbine device with an oil-gas separation structure is provided, comprising a turbine shaft, a transmission shaft, a first bearing, a first bearing seat and an oil-gas separation ring, wherein the transmission shaft is sleeved on the outer periphery of the turbine shaft and is used to mount the inner ring of the first bearing, the outer ring of the first bearing is mounted on the first bearing seat, the space between the first bearing seat and the turbine shaft forms a lubricating oil cavity, and the oil-gas separation ring is sleeved on the outer periphery of the transmission shaft;

[0007] A first exhaust chamber is enclosed between the oil-gas separation ring and the transmission shaft, and a second exhaust chamber is enclosed between the transmission shaft and the turbine shaft. An oil-gas separation hole is arranged on the oil-gas separation ring, and the oil-gas separation hole connects the lubricating oil chamber with the first exhaust chamber; a first ventilation hole is arranged at a first end of the transmission shaft corresponding to the second exhaust chamber, and the first ventilation hole connects the first exhaust chamber with the second exhaust chamber; a second ventilation hole is arranged at a second end of the turbine shaft corresponding to the second exhaust chamber, and the second ventilation hole connects the second exhaust chamber with the central shaft hole of the turbine shaft.

[0008] Preferably, the oil-gas separation ring comprises a first segment and a second segment arranged along the axial direction, the oil-gas separation hole comprises an elongated hole arranged on the first segment and a circular hole arranged on the second segment, and the first ventilation hole is arranged corresponding to the second segment.

[0009] Preferably, the elongated holes and the circular holes are both provided in multiple rows along the axial direction of the oil-gas separation ring, and the number of rows of the elongated holes is greater than the number of rows of the circular holes.

[0010] Preferably, a radial width of the first exhaust cavity corresponding to the first segment is smaller than a radial width of the first exhaust cavity corresponding to the second segment.

[0011] Preferably, the turbine device with an oil-gas separation structure also includes an oil collecting ring, which is sleeved on the outer periphery of the oil-gas separation ring and enclosed with the oil-gas separation ring to form an oil-gas separation chamber, and the oil collecting ring is provided with an exhaust hole that connects the lubricating oil chamber with the oil-gas separation chamber.

[0012] Preferably, the oil collecting ring includes a mounting ring and a retaining ring, the mounting ring is mounted on the transmission shaft, the first end of the retaining ring is connected to the mounting ring, the second end of the retaining ring extends to the side of the oil-gas separation ring away from the mounting ring and abuts against a preset limiting flange on the oil-gas separation ring, and the exhaust hole is opened on the retaining ring.

[0013] Preferably, the turbine device with an oil-gas separation structure also includes an ejector nozzle, which is inserted into the central shaft hole and is used to eject gas toward the rear end of the turbine shaft, thereby accelerating the oil-gas mixture in the central shaft hole and ejecting it toward the rear end of the turbine shaft.

[0014] Preferably, the turbine device with oil-gas separation structure further comprises an oil-gas separator arranged in the central axis hole, and the second vent hole, the oil-gas separator and the ejector nozzle are sequentially arranged at intervals along the exhaust direction of the central axis hole;

[0015] The oil-gas separator comprises a conical air guide cylinder, an exhaust ring and a fixed ring which are sequentially arranged along the axial direction, the exhaust ring and the inner wall of the central axis hole are spaced apart to form a third exhaust chamber, the conical air guide cylinder is used to guide the oil-gas mixture flowing in along the second vent hole into the third exhaust chamber, the exhaust ring is provided with a third vent hole, and the third vent hole connects the third exhaust chamber with the inner ring of the exhaust ring;

[0016] A sealing groove is provided at one end of the fixing ring close to the exhaust ring, and an installation clamp is provided at one end of the fixing ring away from the exhaust ring. The sealing groove is used to embed the sealing ring and elastically abut the inner wall of the central axis hole through the sealing ring, and the installation clamp is used to clamp with a preset installation structure on the inner wall of the central axis hole.

[0017] Preferably, the turbine device with oil-gas separation structure further comprises a turbine disc, a second bearing, a second bearing seat, a first sealing component, a second sealing component and a third sealing component;

[0018] The turbine disk is coaxially arranged relative to the turbine shaft, the inner ring of the second bearing is mounted on the turbine disk, the outer ring of the second bearing is mounted on the second bearing seat, the second bearing seat is sealed and connected to the first bearing seat, the first sealing component is arranged at an end of the first bearing seat away from the second bearing seat and is used to seal the gap between the first bearing seat and the turbine shaft, the second sealing component is arranged at an end of the second bearing seat away from the first bearing seat and is used to seal the gap between the second bearing seat and the turbine disk, the third sealing component is used to seal the gap between the turbine disk and the turbine shaft, and the first bearing seat, the second bearing seat, the turbine shaft and the turbine disk together enclose the lubricating oil chamber.

[0019] According to a second aspect of the present invention, there is also provided an aircraft engine comprising the turbine device with the above-mentioned oil-gas separation structure.

[0020] The present invention has the following beneficial effects:

[0021] In the turbine device with oil-gas separation structure provided by the present invention, a first exhaust chamber is formed between the oil-gas separation ring and the transmission shaft, and a second exhaust chamber is formed between the transmission shaft and the turbine shaft. After the oil-gas mixture in the lubricating oil chamber enters the first exhaust chamber through the oil-gas separation hole on the oil-gas separation ring, since the density of the lubricating oil is much greater than the density of air, most of the lubricating oil can be separated out by centrifugal force and thrown onto the inner wall surface of the oil-gas separation ring and returned to the lubricating oil chamber along the oil-gas separation hole; and the remaining oil-gas mixture can enter the second exhaust chamber along the first ventilation hole on the transmission shaft, and the oil-gas mixture in the second exhaust chamber can also separate part of the lubricating oil from the lubricating oil chamber under the action of centrifugal force, throw it onto the inner wall surface of the transmission shaft and return along the first ventilation hole. Moreover, since the first ventilation hole and the second ventilation hole are respectively arranged at the two ends of the second exhaust chamber, there is sufficient space to realize the oil-gas separation. The invention can avoid the oil-gas mixture in the second exhaust chamber being discharged along the second vent hole before the oil-gas separation is achieved, thereby achieving a better oil-gas separation effect; the remaining oil-gas mixture can enter the central shaft hole of the turbine shaft along the second vent hole on the turbine shaft, and the oil-gas mixture in the central shaft hole can also separate part of the lubricating oil under the action of centrifugal force and throw it onto the inner wall surface of the central shaft hole and return along the second vent hole, so that the final oil-gas mixture contains only a very small amount of lubricating oil and can be directly discharged along the central shaft hole of the turbine shaft. The device can not only realize multi-stage oil-gas separation operation, improve the oil-gas separation effect, and avoid lubricating oil waste, but also integrate the oil-gas separation structure on the turbine shaft and the transmission shaft, without the need to arrange an independent oil-gas separation device in the lubricating oil chamber, which can make the structure of the turbine more compact and lighter, and is more conducive to the miniaturization design of aircraft engines.

[0022] 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

[0023] 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:

[0024] Figure 1 A schematic structural diagram of a turbine device with an oil-gas separation structure provided in an embodiment of the present invention;

[0025] Figure 2 for Figure 1 The oil and gas flow path diagram of the turbine device with an oil and gas separation structure shown in the figure, wherein the arrows show the flow direction of the oil and gas;

[0026] Figure 3 for Figure 1 A partial enlarged view of region A in a turbine device with an oil-gas separation structure shown;

[0027] Figure 4 for Figure 1 A three-dimensional view of an oil-gas separation ring in a turbine device with an oil-gas separation structure;

[0028] Figure 5 for Figure 1 A radial cross-sectional view of an oil-gas separator in a turbine device with an oil-gas separation structure is shown.

[0029] Legend:

[0030] 1. Turbine shaft; 11. Second vent hole; 12. Center shaft hole; 2. Transmission shaft; 21. First vent hole; 3. First bearing; 4. First bearing seat; 5. Oil-gas separation ring; 51. Oil-gas separation hole; 511. Long strip hole; 512. Round hole; 52. First segment; 53. Second segment; 54. Limiting flange; 6. Oil collecting ring; 61. Exhaust hole; 62. Mounting ring; 63. Retaining ring; 7. Injection nozzle; 8. Oil-gas separator; 81. Conical air guide cylinder; 82. Exhaust ring; 821. Third air vent; 83. Retaining ring; 831. Sealing groove; 832. Mounting position; 91. Turbine disk; 92. Second bearing; 93. Second bearing seat; 94. First sealing assembly; 95. Second sealing assembly; 96. Third sealing assembly; 100. Lubricating oil chamber; 200. First exhaust chamber; 300. Second exhaust chamber; 400. Oil-gas separation chamber; 500. Third exhaust chamber. DETAILED DESCRIPTION

[0031] 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.

[0032] Figures 1 to 5 The figures collectively show a turbine device with an oil-gas separation structure provided by an embodiment of the present invention. The turbine device has its own oil-gas separation structure, which can perform multi-stage oil-gas separation operations, thereby improving the oil-gas separation effect, and does not require an independent oil-gas separation device to be arranged in the lubricating oil cavity. The turbine device can have a more compact structure and lighter weight, which is more conducive to the miniaturization design of aircraft engines.

[0033] like Figure 1 As shown, the turbine device with an oil-gas separation structure includes a turbine shaft 1, a transmission shaft 2, a first bearing 3, a first bearing seat 4 and an oil-gas separation ring 5. The transmission shaft 2 is sleeved on the outer periphery of the turbine shaft 1 and is used to install the inner ring of the first bearing 3. The outer ring of the first bearing 3 is installed on the first bearing seat 4. The space between the first bearing seat 4 and the turbine shaft 1 forms a lubricating oil cavity 100. The oil-gas separation ring 5 is sleeved on the outer periphery of the transmission shaft 2.

[0034] Please combine Figure 2and Figure 3 The oil-gas separation ring 5 and the transmission shaft 2 enclose a first exhaust chamber 200, and the transmission shaft 2 and the turbine shaft 1 enclose a second exhaust chamber 300. The oil-gas separation ring 5 is provided with an oil-gas separation hole 51, and the oil-gas separation hole 51 connects the lubricating oil chamber 100 with the first exhaust chamber 200; the first air vent 21 is provided at the first end of the transmission shaft 2 corresponding to the second exhaust chamber 300, and the first air vent 21 connects the first exhaust chamber 200 with the second exhaust chamber 300; the second end of the turbine shaft 1 corresponding to the second exhaust chamber 300 is provided with a second air vent 11, and the second air vent 11 connects the second exhaust chamber 300 with the central shaft hole 12 of the turbine shaft 1.

[0035] Specifically, since the first exhaust chamber 200 is enclosed between the oil-gas separation ring 5 and the transmission shaft 2, and the second exhaust chamber 300 is enclosed between the transmission shaft 2 and the turbine shaft 1, after the oil-gas mixture in the lubricating oil chamber 100 enters the first exhaust chamber 200 through the oil-gas separation hole 51 on the oil-gas separation ring 5, since the density of the lubricating oil is much greater than the density of the air, most of the lubricating oil can be separated out by centrifugal force and thrown onto the inner wall surface of the oil-gas separation ring 5 and return to the lubricating oil chamber 100 along the oil-gas separation hole 51; and the remaining oil-gas mixture can enter the second exhaust chamber 300 along the first air hole 21 on the transmission shaft 2, and the oil-gas mixture in the second exhaust chamber 300 can also separate part of the lubricating oil under the action of centrifugal force, throw it onto the inner wall surface of the transmission shaft 2 and return along the first air hole 21, and since the first air hole 21 and the second air hole 11 are respectively arranged at both ends of the second exhaust chamber 300, there is sufficient space The oil-gas separation operation is realized to prevent the oil-gas mixture in the second exhaust chamber 300 from being discharged along the second vent hole 11 before the oil-gas separation is realized, thereby achieving a better oil-gas separation effect; and the remaining oil-gas mixture can enter the central shaft hole 12 of the turbine shaft 1 along the second vent hole 11 on the turbine shaft 1, and the oil-gas mixture in the central shaft hole 12 can also separate part of the lubricating oil under the action of centrifugal force and throw it onto the inner wall surface of the central shaft hole 12 and return along the second vent hole 11, so that the final oil-gas mixture contains only a very small amount of lubricating oil and can be directly discharged along the central shaft hole 12 of the turbine shaft 1. The device can not only realize multi-stage oil-gas separation operations, improve the oil-gas separation effect, and avoid lubricating oil waste, but also integrate the oil-gas separation structure on the turbine shaft 1 and the transmission shaft 2, without arranging an independent oil-gas separation device in the lubricating oil chamber 100, which can make the structure of the turbine more compact and lighter, and is more conducive to the miniaturization and lightweight design of aircraft engines.

[0036] like Figure 4 As shown, preferably, the oil-gas separation ring 5 includes a first segment 52 and a second segment 53 arranged along the axial direction, the oil-gas separation hole 51 includes an elongated hole 511 arranged on the first segment 52 and a circular hole 512 arranged on the second segment 53, and the first air vent 21 is arranged corresponding to the second segment 52.

[0037] Specifically, the oil-gas separation hole 51 includes a plurality of long strip holes 511 and a plurality of round holes 512, wherein the plurality of long strip holes 511 are arranged on the first segment 52, and the plurality of round holes 512 are arranged on the second segment 53. The long strip holes 511 have a larger opening length and a larger air intake than the round holes 512, so that the oil-gas mixture in the lubricating oil cavity 100 can fully enter the first exhaust cavity 200 along the long strip holes 511 for oil-gas separation. Accordingly, since the round holes 512 have a smaller opening and a smaller air flow than the long strip holes 511, the oil-gas mixture in the first exhaust cavity 200 can be prevented from being directly discharged along the round holes 512, so that the second segment 53 has a better oil-gas separation effect, and the lubricating oil is discharged through the round holes 512 after the lubricating oil is fully separated.

[0038] Preferably, the elongated holes 511 and the circular holes 512 are both provided in multiple rows along the axial direction of the oil-gas separation ring 5, and the number of rows of the elongated holes 511 is greater than the number of rows of the circular holes 512. In this embodiment, the circular holes 512 are provided in two rows, and the elongated holes 511 are provided in three rows or more than three rows, so as to control the axial dimension of the oil-gas separation ring 5 and ensure that the air intake of the first segment 52 is greater than the air flow of the second stage 53, thereby improving the oil-gas separation effect.

[0039] like Figure 3 As shown, preferably, the radial width of the first exhaust chamber 200 corresponding to the first segment 52 is smaller than the radial width of the first exhaust chamber 200 corresponding to the second segment 53, so as to increase the space of the first exhaust chamber 200 corresponding to the second segment 53, so that the oil-gas mixture in the first exhaust chamber 200 can flow toward the second segment 53 under the action of negative pressure and pass through the circular hole 512 on the second segment 53 to perform sufficient oil-gas separation operation, thereby further improving the oil-gas separation effect.

[0040] Preferably, the turbine device with oil-gas separation structure further comprises an oil collecting ring 6, which is sleeved on the outer periphery of the oil-gas separation ring 5 and encloses the oil-gas separation ring 5 to form an oil-gas separation chamber 400, and the oil collecting ring 6 is provided with an exhaust hole 61 for connecting the lubricating oil chamber 100 with the oil-gas separation chamber 400. Similarly, after the oil-gas mixture in the lubricating oil chamber 100 enters the oil-gas separation chamber 400 through the exhaust hole 61, since the density of the lubricating oil is much greater than the density of the air, most of the lubricating oil can be separated out by centrifugal force and thrown onto the inner wall surface of the oil collecting ring 6 and return to the lubricating oil chamber 100 along the exhaust hole 61. Before the oil-gas mixture enters the oil-gas separation ring 5, the preliminary oil-gas separation operation is first performed through the oil collecting ring 6 to discharge most of the lubricating oil, thereby preventing a large amount of lubricating oil from entering the first exhaust chamber 200, and ensuring the oil-gas separation effect of the oil-gas separation ring 5.

[0041] Further, the oil collecting ring 6 includes a mounting ring 62 and a retaining ring 63, wherein the mounting ring 62 is mounted on the transmission shaft 2, the first end of the retaining ring 63 is connected to the mounting ring 62, the second end of the retaining ring 63 extends to the side of the oil-gas separation ring 5 away from the mounting ring 62 and abuts against a preset limiting flange 54 on the oil-gas separation ring 5, and the exhaust hole 61 is provided on the retaining ring 63. While the preliminary oil-gas separation operation is realized by the oil collecting ring 6, the radial fixation of the oil-gas separation ring 5 can be realized by the cooperation between the retaining ring 63 and the limiting flange 54, and the axial fixation of the oil-gas separation ring 5 can be realized by the axial cooperation between the mounting ring 62 and the oil-gas separation ring 5, thereby realizing the positioning and fixation of the oil-gas separation ring 5 without the need for an additional assembly structure.

[0042] Please combine Figure 1 and Figure 2 The turbine device with oil-gas separation structure also includes an ejector nozzle 7, which is penetrated in the central shaft hole 12 and is used to eject gas toward the rear end of the turbine shaft 1, so that the oil-gas mixture in the central shaft hole 12 is accelerated to be ejected toward the rear end of the turbine shaft 12, and the flow speed of the oil-gas mixture can be accelerated in the low speed state of the turbine shaft 1 and the transmission shaft 2, thereby improving the oil-gas separation effect.

[0043] Preferably, the turbine device with oil-gas separation structure also includes an oil-gas separator 8 arranged in the central axis hole 12, and the second air vent 11, the oil-gas separator 8 and the ejector nozzle 7 are sequentially arranged at intervals along the exhaust direction of the central axis hole 12.

[0044] Please combine Figure 5Specifically, the oil-gas separator 8 includes a conical air guide cylinder 81, an exhaust ring 82 and a fixed ring 83 which are arranged in sequence along the axial direction. The exhaust ring 82 is spaced apart from the inner wall of the central axis hole 12 to form a third exhaust chamber 500. The conical air guide cylinder 81 is used to guide the oil-gas mixture flowing in along the second air hole 11 into the third exhaust chamber 500. The exhaust ring 82 is provided with a third air hole 821, and the third air hole 821 connects the third exhaust chamber 500 with the inner circle of the exhaust ring 82. Similarly, after the oil-gas mixture in the third exhaust chamber 500 enters the inner ring of the exhaust ring 82 through the third air vent 821, most of the lubricating oil can be separated by centrifugal force and thrown onto the inner wall of the exhaust ring 82 and return to the third exhaust chamber 500 along the third air vent 821, thereby realizing one more level of oil-gas separation operation in the central axis hole 12, thereby improving the oil-gas separation effect. In addition, the space of the third exhaust chamber 500 is gradually reduced by the conical air guide tube 81, thereby increasing the flow rate of the oil-gas mixture and enhancing the oil-gas separation effect through high flow rate.

[0045] Furthermore, a sealing groove 831 is provided at one end of the fixing ring 83 close to the exhaust ring 82, and a mounting clamping position 832 is provided at one end of the fixing ring 83 away from the exhaust ring 82. The sealing groove 821 is used to embed a sealing ring and elastically abut against the inner wall of the central shaft hole 12 through the sealing ring, and the mounting clamping position 832 is used to clamp with a preset mounting structure on the inner wall of the central shaft hole 12. The axial ends of the fixing ring 83 are respectively closely matched with the central shaft hole 12 through the mounting clamping position 832 and the sealing ring, so as to ensure the installation strength and improve the sealing effect between the fixing ring 83 and the inner wall of the central shaft hole 12.

[0046] like Figure 1 As shown, the turbine device with oil-gas separation structure also includes a turbine disc 91, a second bearing 92, a second bearing seat 93, a first sealing component 94, a second sealing component 95 and a third sealing component 96.

[0047] The turbine disk 91 is coaxially arranged relative to the turbine shaft 1, the inner ring of the second bearing 92 is mounted on the turbine disk 91, the outer ring of the second bearing 92 is mounted on the second bearing seat 93, the second bearing seat 93 is sealed and connected to the first bearing seat 4, the first sealing component 94 is arranged at the end of the first bearing seat 4 away from the second bearing seat 93 and is used to seal the gap between the first bearing seat 4 and the turbine shaft 1, the second sealing component 95 is arranged at the end of the second bearing seat 93 away from the first bearing seat 4 and is used to seal the gap between the second bearing seat 93 and the turbine disk 91, the third sealing component 96 is used to seal the gap between the turbine disk 91 and the turbine shaft 1, the first bearing seat 4, the second bearing seat 93, the turbine shaft 1 and the turbine disk 91 together enclose the lubricating oil chamber 100.

[0048] Further, the first sealing component 94, the second sealing component 95 and / or the third sealing component 96 include a graphite sealing track and a graphite ring, the graphite ring abuts against the graphite sealing track and is used to rotate along the graphite sealing track, and the sealing is achieved through the sliding cooperation between the graphite sealing track and the graphite ring, so as to achieve a better sealing effect and reduce the cooling gas from entering the lubricating oil cavity 100. In other embodiments, the first sealing component 94, the second sealing component 95 and / or the third sealing component 96 can also be sealed with a comb tooth or an expansion ring, which can also achieve a certain sealing effect.

[0049] As a second aspect, an embodiment of the present invention further provides an aircraft engine, comprising the above-mentioned turbine device with an oil-gas separation structure. Since the turbine device with an oil-gas separation structure has its own oil-gas separation structure, it can perform multi-stage oil-gas separation operations, thereby improving the oil-gas separation effect, and there is no need to arrange an independent oil-gas separation device in the lubricating oil cavity. The turbine structure can be more compact and lighter, which is more conducive to the miniaturization and lightweight design of the aircraft engine.

[0050] 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. A turbine device with an oil-gas separation structure, characterized in that: The invention comprises a turbine shaft (1), a transmission shaft (2), a first bearing (3), a first bearing seat (4) and an oil-gas separation ring (5), wherein the transmission shaft (2) is sleeved on the outer periphery of the turbine shaft (1) and is used to mount the inner ring of the first bearing (3), the outer ring of the first bearing (3) is mounted on the first bearing seat (4), the space between the first bearing seat (4) and the turbine shaft (1) forms a lubricating oil cavity (100), and the oil-gas separation ring (5) is sleeved on the outer periphery of the transmission shaft (2); A first exhaust chamber (200) is enclosed between the oil-gas separation ring (5) and the transmission shaft (2), and a second exhaust chamber (300) is enclosed between the transmission shaft (2) and the turbine shaft (1). An oil-gas separation hole (51) is arranged on the oil-gas separation ring (5), and the oil-gas separation hole (51) connects the lubricating oil chamber (100) with the first exhaust chamber (200); a first ventilation hole (21) is arranged at a first end of the transmission shaft (2) corresponding to the second exhaust chamber (300), and the first ventilation hole (21) connects the first exhaust chamber (200) with the second exhaust chamber (300); a second ventilation hole (11) is arranged at a second end of the turbine shaft (1) corresponding to the second exhaust chamber (300), and the second ventilation hole (11) connects the second exhaust chamber (300) with the central shaft hole (12) of the turbine shaft (1).

2. The turbine device with oil-gas separation structure according to claim 1, characterized in that: The oil-gas separation ring (5) comprises a first segment (52) and a second segment (53) arranged along the axial direction; the oil-gas separation hole (51) comprises an elongated hole (511) arranged on the first segment (52) and a circular hole (512) arranged on the second segment (53); and the first ventilation hole (21) is arranged corresponding to the second segment (53).

3. The turbine device with oil-gas separation structure according to claim 2, characterized in that: The elongated holes (511) and the circular holes (512) are both arranged in multiple rows along the axial direction of the oil-gas separation ring (5), and the number of rows of the elongated holes (511) is greater than the number of rows of the circular holes (512).

4. The turbine device with oil-gas separation structure according to claim 2, characterized in that: The radial width of the first exhaust cavity (200) corresponding to the first segment (52) is smaller than the radial width of the first exhaust cavity (200) corresponding to the second segment (53).

5. The turbine device with oil-gas separation structure according to claim 1, characterized in that: The turbine device with the oil-gas separation structure also includes an oil collecting ring (6), which is sleeved on the outer circumference of the oil-gas separation ring (5) and encloses the oil-gas separation ring (5) to form an oil-gas separation chamber (400), and the oil collecting ring (6) is provided with an exhaust hole (61) for connecting the lubricating oil chamber (100) with the oil-gas separation chamber (400).

6. The turbine device with oil-gas separation structure according to claim 5, characterized in that: The oil collecting ring (6) comprises a mounting ring (62) and a retaining ring (63); the mounting ring (62) is mounted on the transmission shaft (2); a first end of the retaining ring (63) is connected to the mounting ring (62); a second end of the retaining ring (63) extends to a side of the oil-gas separation ring (5) away from the mounting ring (62) and abuts against a preset limiting flange (54) on the oil-gas separation ring (5); and the exhaust hole (61) is provided on the retaining ring (63).

7. The turbine device with oil-gas separation structure according to claim 1, characterized in that: The turbine device with an oil-gas separation structure also includes an ejector nozzle (7), which is inserted into the central axis hole (12) and is used to eject gas toward the rear end of the turbine shaft (1), thereby accelerating the oil-gas mixture in the central axis hole (12) and ejecting it toward the rear end of the turbine shaft (1).

8. The turbine device with oil-gas separation structure according to claim 7, characterized in that: The turbine device with an oil-gas separation structure further comprises an oil-gas separator (8) arranged in the central axis hole (12), and the second vent hole (11), the oil-gas separator (8) and the ejector nozzle (7) are sequentially arranged at intervals along the exhaust direction of the central axis hole (12); The oil-gas separator (8) comprises a conical air guide cylinder (81), an exhaust ring (82) and a fixed ring (83) which are sequentially arranged along the axial direction; the exhaust ring (82) and the inner wall of the central axis hole (12) are arranged at intervals to form a third exhaust chamber (500); the conical air guide cylinder (81) is used to guide the oil-gas mixture flowing in along the second vent hole (11) into the third exhaust chamber (500); the exhaust ring (82) is provided with a third vent hole (821); the third vent hole (821) connects the third exhaust chamber (500) with the inner ring of the exhaust ring (82); A sealing groove (831) is provided at one end of the fixing ring (83) close to the exhaust ring (82), and a mounting clamping position (832) is provided at one end of the fixing ring (83) away from the exhaust ring (82). The sealing groove (831) is used to embed the sealing ring and elastically abut the inner wall of the central axis hole (12) through the sealing ring, and the mounting clamping position (832) is used to clamp with a preset mounting structure on the inner wall of the central axis hole (12).

9. The turbine device with oil-gas separation structure according to claim 1, characterized in that: The turbine device with an oil-gas separation structure further comprises a turbine disk (91), a second bearing (92), a second bearing seat (93), a first sealing component (94), a second sealing component (95) and a third sealing component (96); The turbine disk (91) is coaxially arranged relative to the turbine shaft (1); the inner ring of the second bearing (92) is mounted on the turbine disk (91); the outer ring of the second bearing (92) is mounted on the second bearing seat (93); the second bearing seat (93) is sealed and connected to the first bearing seat (4); the first sealing component (94) is arranged at one end of the first bearing seat (4) away from the second bearing seat (93) and is used to seal the gap between the first bearing seat (4) and the turbine shaft (1); the second sealing component (95) is arranged at one end of the second bearing seat (93) away from the first bearing seat (4) and is used to seal the gap between the second bearing seat (93) and the turbine disk (91); the third sealing component (96) is used to seal the gap between the turbine disk (91) and the turbine shaft (1); the first bearing seat (4), the second bearing seat (93), the turbine shaft (1) and the turbine disk (91) together enclose the lubricating oil chamber (100).

10. An aircraft engine, characterized in that: A turbine device with an oil-gas separation structure comprising the turbine device according to any one of claims 1 to 9.

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