CN115069027B - Oil-gas separation device and aeroengine - Google Patents
Oil-gas separation device and aeroengine Download PDFInfo
- Publication number
- CN115069027B CN115069027B CN202110264198.4A CN202110264198A CN115069027B CN 115069027 B CN115069027 B CN 115069027B CN 202110264198 A CN202110264198 A CN 202110264198A CN 115069027 B CN115069027 B CN 115069027B
- Authority
- CN
- China
- Prior art keywords
- baffle
- oil
- gas separation
- separation device
- housing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000926 separation method Methods 0.000 title claims abstract description 73
- 230000008859 change Effects 0.000 claims abstract description 15
- 239000000203 mixture Substances 0.000 claims abstract description 14
- 230000004888 barrier function Effects 0.000 claims description 47
- 230000001105 regulatory effect Effects 0.000 claims description 9
- 230000000694 effects Effects 0.000 abstract description 16
- 239000007789 gas Substances 0.000 description 81
- 239000003921 oil Substances 0.000 description 27
- 238000007789 sealing Methods 0.000 description 19
- 239000010687 lubricating oil Substances 0.000 description 13
- 230000001965 increasing effect Effects 0.000 description 11
- 239000012530 fluid Substances 0.000 description 8
- 230000000903 blocking effect Effects 0.000 description 6
- 230000000670 limiting effect Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000002411 adverse Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000002708 enhancing effect Effects 0.000 description 3
- 239000004677 Nylon Substances 0.000 description 2
- 239000004698 Polyethylene Substances 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 229920006378 biaxially oriented polypropylene Polymers 0.000 description 2
- 239000011127 biaxially oriented polypropylene Substances 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229920001778 nylon Polymers 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 229920002457 flexible plastic Polymers 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000002985 plastic film Substances 0.000 description 1
- 229920006267 polyester film Polymers 0.000 description 1
- -1 polyethylene Polymers 0.000 description 1
- 229920000573 polyethylene Polymers 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000005060 rubber Substances 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 239000004634 thermosetting polymer Substances 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D45/00—Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces
- B01D45/12—Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces
- B01D45/14—Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by rotating vanes, discs, drums or brushes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
Abstract
The invention relates to an oil-gas separation device and an aeroengine, wherein the oil-gas separation device comprises a rotatable shell (6) and a multi-stage baffle, a first cavity is arranged in the shell (6), and the first cavity is provided with an inlet and an outlet; the multistage baffle is arranged in the first cavity and is arranged along the axial direction of the shell (6), the multistage baffle forms a spiral first flow passage, the flow resistance of the first flow passage changes along with the change of the rotating speed of the shell (6), and the oil-gas mixture (13) realizes oil-gas separation in the first flow passage. The aero-engine comprises an oil-gas separation device. The oil-gas separation device can adjust the pressure in the bearing cavity according to the rotating speed of the engine, thereby improving the oil-gas separation effect.
Description
Technical Field
The invention relates to the technical field of oil-gas separation, in particular to an oil-gas separation device and an aeroengine.
Background
In an aero gas turbine engine, a bearing component is included for supporting the main shaft of the engine for high speed rotation. In order to protect the bearings from the high temperature combustion gases in the engine, it is necessary to arrange the bearings in the bearing cavities. The bearing chamber is provided with sealing means to prevent oil used for lubricating the bearing from leaking out of the bearing chamber. In order to ensure the sealing effect, the bearing cavity sealing device needs to have sealing pressure difference. The sealing pressure difference is established by the difference between the high-pressure gas pressure outside the bearing cavity and the pressure inside the bearing cavity.
The high pressure air outside the bearing cavity is typically introduced by the engine compressor, the pressure of which varies continuously with the speed of the engine. When the engine rotates at a low speed, the air pressure introduced by the air compressor is smaller, when the engine operates at a high speed, the introduced air pressure is higher, and the pressure in the bearing cavity is communicated with the outside atmosphere, so that the change in the operation process of the engine is small. The pressure differential experienced by the bearing cavity seals is thus constantly changing, which will lead to increased wear of the bearings and the risk of fire from the intrusion of high temperature gases into the bearing cavity at large pressure differentials, and the risk of leakage of oil from the bearing cavity at small pressure differentials.
Meanwhile, sealing gas is used for mixing lubricating oil through a bearing cavity to form an oil-gas mixture, the oil-gas mixture is led to the outside atmosphere from the axis of the rotating shaft, if proper measures are not adopted to separate the lubricating oil from air and send the lubricating oil back into the bearing cavity, a large amount of lubricating oil is required to be carried away from the bearing cavity, so that the lubricating oil is consumed, and particularly in a high-rotating-speed state of an engine, the bearing is insufficiently cooled due to excessive consumption of the lubricating oil, so that the bearing is in failure danger.
It should be noted that the information disclosed in the background section of the present invention is only for increasing the understanding of the general background of the present invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.
Disclosure of Invention
The embodiment of the invention provides an oil-gas separation device and an aeroengine, which are beneficial to improving the oil-gas separation effect.
According to one aspect of the present invention, there is provided an oil-gas separation device comprising:
A rotatable housing having a first cavity therein, the first cavity having an inlet and an outlet; and
The multistage baffle is arranged in the first cavity and is arranged along the axial direction of the shell, the multistage baffle forms a spiral first flow passage, the flow resistance of the first flow passage changes along with the change of the rotating speed of the shell, and the oil-gas separation of the oil-gas mixture in the first flow passage is realized.
In some embodiments, the multi-stage baffle includes a first baffle plate fixedly connected to the inner wall of the housing and a second baffle plate connected to the inner wall of the housing and rotatable relative to the first baffle plate to vary the position of the second baffle plate in the circumferential direction relative to the first baffle plate to thereby adjust the flow resistance of the first flow passage.
In some embodiments, the side of the first baffle adjacent to the inlet is provided with an annular boss protruding in a direction toward the inlet, the boss being configured to be streamlined.
In some embodiments, the inner wall of the housing is provided with a first chute extending in a circumferential direction, and the end of the second baffle is provided with a first sliding portion, and the first sliding portion is disposed in the first chute.
In some embodiments, the oil-gas separation device further includes a first elastic member disposed in the first chute for resetting the second baffle.
In some embodiments, the multi-stage baffle further comprises a third baffle coupled to the inner wall of the housing and rotatable relative to the first baffle, the third baffle disposed between the first baffle and the second baffle.
In some embodiments, the oil and gas separation device further includes a first flexible barrier connected between the first baffle and the third baffle and a second flexible barrier connected between the second baffle and the third baffle.
In some embodiments, the oil and gas separation device further includes a drive device configured to drive the second baffle plate to rotate relative to the first baffle plate.
In some embodiments, the driving device includes a rotating member, a sliding block and a flexible member, the rotating member is disposed in the first cavity, the second baffle is relatively fixedly connected with the rotating member, the first baffle is rotatably connected with the rotating member, a second sliding groove extending along a radial direction is disposed in the first baffle, the sliding block is slidably disposed in the second sliding groove, the flexible member is wound on the rotating member, one end of the flexible member is connected with the sliding block, and the other end of the flexible member is connected with the rotating member.
In some embodiments, the rotating member is provided with circumferentially arranged grooves in which the flexible member is wound.
In some embodiments, the end of the rotor near the end of the inlet is configured to be streamlined.
In some embodiments, each stage of baffles comprises at least two bars arranged circumferentially of the housing.
In some embodiments, the inner wall of the housing is provided with a spiral second flow passage through which the separated oil flows back, the spiral direction of the second flow passage being opposite to the spiral direction of the first flow passage.
In some embodiments, the depth of the second flow channel increases gradually in the direction of flow of the lubricating oil.
According to another aspect of the invention, an aeroengine is provided, comprising a rotating shaft and the oil-gas separation device, wherein the rotating shaft is used as a shell.
Based on the above technical scheme, in the embodiment of the invention, the flow resistance of the first flow channel for realizing oil-gas separation changes along with the change of the rotation speed of the shell, and when the rotation speed of the shell changes, the flow resistance of the fluid flowing through the first flow channel also changes along with the change of the rotation speed of the shell, so that the pressure difference of the chamber for generating the oil-gas mixture can be matched with the rotation speed of the shell, and adverse effects caused by the change of the pressure difference are avoided; in addition, the first flow channel in the embodiment of the invention is a spiral flow channel, so that the fluid flowing through the first flow channel can do spiral movement, thereby enhancing the oil-gas separation effect and improving the oil-gas separation efficiency.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute a limitation on the application. In the drawings:
FIG. 1 is a schematic structural view of an embodiment of an aircraft engine according to the present invention.
FIG. 2 is an internal schematic view of a portion of the structure of an embodiment of an aircraft engine according to the present invention.
FIG. 3 is a schematic illustration of the internal structure of an embodiment of an oil and gas separator of the present invention, partially broken away.
FIG. 4 is a schematic view of a portion of an embodiment of an oil-gas separator according to the present invention.
FIG. 5 is an internal cross-sectional view of an embodiment of the oil and gas separation device of the present invention.
Fig. 6 is a cross-sectional view taken along section C-C in fig. 5.
Fig. 7 is a first state sectional view taken along A-A in fig. 5.
Fig. 8 is a second state sectional view taken along A-A in fig. 5.
Fig. 9 is a first state sectional view taken along the B-B section in fig. 5.
Fig. 10 is a second state sectional view taken along the B-B section in fig. 5.
In the figure:
1. An aero-engine; 2. a first bearing cavity; 3. a second bearing cavity; 4. a high-pressure rotor; 5. a low pressure rotor; 6. a housing; 7. a fixing assembly; 8. a first bearing; 9. a second bearing; 10. the outside of the bearing cavity; 11. a bearing cavity interior; 12. sealing the gas; 13. an oil-gas mixture; 14. a spiral air flow; 15. lubricating oil; 16. a seal assembly; 17. a radial hole; 18. a rotor assembly; 19. a separation assembly;
61. a second flow passage; 62. a third chute; 63. a first chute;
30. A first baffle; 31. a second chute; 32. a first sleeve; 33. a first barrier strip; 34. a through hole; 35. a boss;
40. A third baffle; 41. a third barrier strip; 42. a second sleeve; 43. a second sliding part; 44. a second elastic member;
50. A second baffle; 51. a second barrier strip; 52. a first sliding portion;
60. a first flexible barrier; 70. a second flexible barrier;
81. a rotating member; 82. a slide block; 83. a flexible member;
811. an end head; 812. a first shaft section; 813. a second shaft section; 814. a third shaft section; 815. and a fourth shaft section.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "center," "lateral," "longitudinal," "front," "rear," "left," "right," "upper," "lower," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present invention.
As shown in fig. 1 to 3, in some embodiments of the oil-gas separation device provided by the invention, the oil-gas separation device comprises a multi-stage baffle plate and a rotatable shell 6, a first cavity is arranged in the shell 6, the first cavity is provided with an inlet and an outlet, the multi-stage baffle plate is arranged in the first cavity and is arranged along the axial direction of the shell 6, the multi-stage baffle plate forms a spiral first flow passage, the flow resistance of the first flow passage changes along with the change of the rotating speed of the shell 6, and the oil-gas mixture 13 realizes oil-gas separation in the first flow passage.
In the above embodiment, the flow resistance of the first flow passage for realizing oil-gas separation varies with the variation of the rotation speed of the housing 6, and when the rotation speed of the housing varies, the flow resistance of the fluid flowing through the first flow passage also varies, so that the pressure difference of the chamber for generating the oil-gas mixture can be matched with the rotation speed of the housing, and adverse effects caused by the variation of the pressure difference are avoided; moreover, the first flow channel in the above embodiment is a spiral flow channel, so that the fluid flowing through the first flow channel can perform spiral movement, thereby enhancing the oil-gas separation effect and improving the oil-gas separation efficiency.
For example, when the oil-gas separation device provided by the embodiment of the invention is applied to an aeroengine, the rotating shaft of the engine can be used as the shell 6, when the rotating speed of the rotating shaft changes, the flow resistance of the fluid flowing through the first flow passage changes along with the rotating shaft, and the pressure in the bearing cavity can be influenced after the flow resistance changes, so that the pressure difference inside and outside the bearing cavity is regulated, the pressure difference of the bearing cavity is prevented from being influenced by the rotating speed of the rotating shaft, and the pressure difference can be kept unchanged as much as possible. When the rotating speed of the rotating shaft is higher, the pressure of sealing gas introduced into the bearing cavity is higher, at the moment, the adjusting requirement of the pressure difference between the inside and the outside of the bearing cavity is smaller, and when the rotating speed of the rotating shaft is higher, the flowing resistance of a first flow passage in the oil-gas separation device is smaller, and the pressure adjusting effect of the first flow passage on the bearing cavity is smaller, so that the pressure adjusting requirement of the first flow passage is exactly matched with the adjusting requirement of the pressure difference; when the rotating speed of the rotating shaft is low, the pressure of sealing air introduced into the bearing cavity is small, the pressure difference between the inside and the outside of the bearing cavity is large, at the moment, the regulating requirement of the pressure difference between the inside and the outside of the bearing cavity is large, and when the rotating speed of the rotating shaft is low, the flow resistance of a first runner in the oil-gas separation device is large, so that the internal pressure of the bearing cavity can be improved, the pressure regulating effect on the bearing cavity is increased, the pressure difference between the inside and the outside of the bearing cavity is effectively reduced, and the influence of the change of the rotating speed of the rotating shaft on the pressure difference of the bearing cavity is avoided.
In some embodiments, the multi-stage baffle includes a first baffle 30 and a second baffle 50, the first baffle 30 being relatively fixedly connected to the inner wall of the housing 6, the second baffle 50 being connected to the inner wall of the housing 6 and being rotatable relative to the first baffle 30 to vary the position of the second baffle 50 circumferentially relative to the first baffle 30 to thereby adjust the flow resistance of the first flow passage.
The first baffle 30 is fixedly connected with the housing 6, and the first baffle 30 rotates along with the rotation of the housing 6. The second baffle 50 and the first baffle 30 can rotate relatively, and when the second baffle 50 and the first baffle 30 rotate relatively, the second baffle 50 and the first baffle 30 are staggered or the staggered angle is increased in the circumferential direction, so that the blocking area of the flow section is increased, the flow resistance of fluid is increased, and the adjustment of the internal pressure of the bearing cavity is realized.
According to the embodiment of the invention, the flow resistance of the first flow channel is regulated in a mode of regulating the flow area of the flow section, so that the internal pressure of the bearing cavity is regulated, the relative balance of the pressure difference between the inside and outside of the bearing cavity is maintained, and the influence of the rotating speed of the rotating shaft on the pressure difference is avoided. The flow cross section refers to a cross section of the first flow passage taken in a direction perpendicular to the fluid flow direction.
In some embodiments, the side of the first baffle 30 near the inlet is provided with an annular protrusion 35 protruding in a direction near the inlet, the protrusion 35 being configured in a streamline shape. By providing the streamlined nose 35, the flow resistance of the air flow when passing through the first baffle 30 can be reduced, the air flow disturbance at the first baffle 30 is avoided, and the aerodynamic loss is reduced. The streamlined nose 35 has a guiding effect on the airflow.
In some embodiments, the inner wall of the housing 6 is provided with a first sliding groove 63 extending in the circumferential direction, and the end of the second shutter 50 is provided with a first sliding portion 52, and the first sliding portion 52 is disposed in the first sliding groove 63. The first sliding groove 63 has an arc shape, the first sliding portion 52 slides in the first sliding groove 63, and the first sliding groove 63 has guiding and limiting effects on the first sliding portion 52. By the cooperation of the first sliding portion 52 and the first sliding groove 63, the rotation of the second shutter 50 with respect to the housing 6 and thus the rotation of the second shutter 50 with respect to the first shutter 30 can be achieved.
In some embodiments, the oil and gas separation device further includes a first resilient member disposed within the first chute 63 for resetting the second baffle 50. By providing the first elastic member, the second shutter 50 can be restored to the original position by the elastic potential energy of the first elastic member when the rotation speed of the housing 6 is low.
In some embodiments, the multi-stage baffle further comprises a third baffle 40, the third baffle 40 being connected to the inner wall of the housing 6 and being rotatable relative to the first baffle 30, the third baffle 40 being disposed between the first baffle 30 and the second baffle 50.
By providing the third baffle 40, the flow path of the fluid flowing through the first flow passage can be made more spiral, the larger the spiral angle of the spiral flow passage, the more remarkable the pressure regulating effect thereof on the bearing chamber. The number of third baffles 40 may be one or more.
The third baffle 40 and the housing 6 can rotate relatively, and when the second baffle 50 rotates relative to the first baffle 30, the second baffle 50 drives the third baffle 40 to rotate relative to the first baffle 30. The rotation angle of the second barrier 50 is greater than the rotation angle of the third barrier 40.
In some embodiments, the oil and gas separation device further includes a first flexible barrier 60 and a second flexible barrier 70, the first flexible barrier 60 being connected between the first baffle 30 and the third baffle 40, and the second flexible barrier 70 being connected between the second baffle 50 and the third baffle 40.
By providing the first flexible barrier 60 and the second flexible barrier 70, a smooth, more closed, spiral first flow path may be formed with the first baffle 30, the second baffle 50, and the third baffle 40, facilitating the transport of the airflow and the separation of the oil and gas. Moreover, by providing the first flexible blocking member 60 and the second flexible blocking member 70, a linkage action can be formed between the second baffle 50 and the third baffle 40, and when the second baffle 50 rotates relative to the first baffle 30, the third baffle 40 can be driven to rotate.
The first flexible barrier 60 and the second flexible barrier 70 have soft, deformable, stretchable and elastic properties to facilitate the formation of smooth channels, and may be made of a film material made of a high thermosetting polymer, such as a flexible plastic film material with better elasticity and strength, such as biaxially oriented polyethylene film (PE stretched film), biaxially oriented polyester film (BOPET) or biaxially oriented polypropylene film (BOPP), or may be a bellows or other elastic material.
In some embodiments, the oil and gas separation device further includes a drive device configured to drive the second baffle 50 to rotate relative to the first baffle 30.
The specific structure of the driving device can be selected in various ways. Some possible embodiments are presented below:
In some embodiments, the driving device includes a rotating member 81, a sliding block 82 and a flexible member 83, the rotating member 81 is disposed in the first cavity, the second baffle 50 is relatively fixedly connected with the rotating member 81, the first baffle 30 is rotatably connected with the rotating member 81, a second sliding groove 31 extending along a radial direction is disposed in the first baffle 30, the sliding block 82 is slidably disposed in the second sliding groove 31, the flexible member 83 is wound on the rotating member 81, one end of the flexible member 83 is connected with the sliding block 82, and the other end is connected with the rotating member 81.
When the shell 6 rotates, the first baffle 30 is driven to rotate together, when the first baffle 30 rotates, the sliding block 82 slides outwards in the radial direction in the second chute 31 under the action of centrifugal force, the sliding block 82 pulls the rotating piece 81 to rotate through the flexible piece 83, the rotating piece 81 rotates and then drives the second baffle 50 to rotate relative to the shell 6, and the third baffle 40 also rotates relative to the shell 6 under the drive of the second baffle 50, so that a spiral channel is formed.
The flexible member 83 may be a flexible connection member such as a steel wire rope or a nylon rope, and the flexible member 83 is not stretchable, so as to avoid affecting the movement stroke of the slider 82.
In some embodiments, the rotating member 81 is provided with circumferentially arranged grooves in which the flexible member 83 is wound. By providing the groove, the flexible member 83 can be accommodated therein, and the flexible member 83 is prevented from being confused in the course of the repeated movement and winding, and the movement of the flexible member 83 in the axial direction of the rotary member 83 can be restricted.
In some embodiments, the end of the rotary member 81 near the end of the inlet is configured to be streamlined. The advantage of this arrangement is that it can make the air flow smoother, prevent the air flow flowing through the rotating member 81 from generating air flow disturbance, and is beneficial to reduce aerodynamic loss; it can also form a diversion effect on the airflow.
In some embodiments, each stage of baffles comprises at least two bars arranged along the circumference of the housing 6. Through setting up a plurality of blend stops, be convenient for realize the adjustable of flow cross section area to and the adjustable of flow resistance. When the barrier strips of each stage of baffle are overlapped in the circumferential direction, the flow area of the first flow channel is the largest; when each baffle rotates relatively, the flow area of the first flow channel can be adjusted, and the flow resistance can also be adjusted.
In some embodiments, the inner wall of the housing 6 is provided with a spiral-shaped second flow channel 61, through which second flow channel 61 the separated oil 15 flows back, the spiral direction of the second flow channel 61 being opposite to the spiral direction of the first flow channel. This arrangement allows oil and gas separation to be accomplished while driving the oil 15 back to increase the driving force of the oil 15 back to the bearing cavity.
In some embodiments, the depth of the second flow channel 61 increases gradually in the direction of flow of the lubricating oil 15. This allows the oil 15 to flow back more smoothly.
Based on the oil-gas separation device, the invention also provides an aeroengine, which comprises a rotating shaft and the oil-gas separation device, wherein the rotating shaft is used as a shell 6 in the oil-gas separation device.
The positive technical effects of the oil-gas separation device in the above embodiments are also applicable to aeroengines, and are not described here again.
The structure and operation of one embodiment of the oil-gas separation device of the present invention will be described with reference to fig. 1 to 10:
the description will be given taking an example of the application of the oil-gas separation device to an aircraft engine.
As shown in fig. 1, the aeroengine 1 comprises a high-pressure rotor 4 and a low-pressure rotor 5, the high-pressure rotor 4 and the low-pressure rotor 5 being supported for rotation by bearings, respectively, which are enclosed in a first bearing chamber 2 and a second bearing chamber 3.
As shown in fig. 2, the first bearing 8 and the second bearing 9 are encapsulated in the bearing cavity 11, and are used for supporting the rotor assembly 18 on the fixed assembly 7, the rotor assembly 18 and the fixed assembly 7 are sealed by the labyrinth seal assembly 16 and enclose the first bearing cavity 2, and the seal assembly 16 seals the bearing cavity 11 by using compressed air as sealing gas 12. In order to prevent leakage of the oil, the pressure inside the bearing chamber 11 is lower than the pressure outside the bearing chamber 10, so that the seal gas 12 flows through the seal assembly 16 into the bearing chamber 11 to be mixed with the oil to form the oil-gas mixture 13, the oil-gas mixture 13 flows through the radial holes 17 into the first cavity of the housing 6 for oil-gas separation, the separated oil 15 flows back to the bearing chamber 11 along the inner wall of the housing 6, and the separated spiral air flow 14 is discharged to the outside of the engine.
As shown in fig. 3, a separation assembly 19 is provided in a first cavity of a rotating shaft (housing 6) of the engine, and the separation assembly 19 can change the gas circulation capacity of the rotating shaft of the engine according to the operation state of the engine.
As shown in fig. 4, the separation assembly 19 includes a first baffle 30, a second baffle 50, and a third baffle 40, with a first flexible barrier 60 disposed between the first baffle 30 and the third baffle 40, and a second flexible barrier 70 disposed between the third baffle 40 and the second baffle 50.
As shown in fig. 5, the first shutter 30 is fixedly installed on the inner wall of the housing 6. The first barrier 30 includes a first sleeve 32 and three first barrier ribs 33, and the three first barrier ribs 33 are mounted on the first sleeve 32 at intervals along the circumferential direction of the first sleeve 32. The first sleeve 32 is fitted around the outer periphery of the rotating member 81, and the first sleeve 32 can rotate relative to the rotating member 81. The first barrier rib 33 is arc-shaped, the second sliding groove 31 is arranged in the first barrier rib 33, the sliding block 82 is arranged in the second sliding groove 31, the sliding block 82 slides in the second sliding groove 31, and the second sliding groove 31 has guiding and limiting effects on the movement of the sliding block 82. The revolute pair between the first shutter 30 and the rotary member 81 forms a first fulcrum of the rotary member 81.
The second baffle 50 is fixedly installed on the rotating member 81, and is integrally connected with the rotating member 81 to form a rotating member. The second barrier 50 includes three second barrier ribs 51, the second barrier ribs 51 having an arc shape, the three second barrier ribs 51 being circumferentially mounted on the rotating member 81 at intervals. The inner wall of the housing 6 is provided with a first sliding groove 63, one side of the second barrier strip 51 far away from the rotating member 81 is provided with a first sliding part 52, the first sliding part 52 is located in the first sliding groove 63, and the first sliding part 52 and the second barrier strip 51 form a structure with a T-shaped cross section so as to prevent the first sliding part 52 from being separated from the first sliding groove 63. The connection of the second shutter 50 to the housing 6 serves as a second fulcrum for the rotary member 81.
The third barrier 40 includes a second sleeve 42 and three third barrier ribs 41, and the three third barrier ribs 41 are installed on the second sleeve 42 at intervals along the circumferential direction of the second sleeve 42. The second sleeve 42 is sleeved on the outer periphery of the rotating member 81, and the second sleeve 42 can rotate relative to the rotating member 81. The third barrier rib 41 has an arc shape. The inner wall of the housing 6 is provided with a third sliding groove 62, one side of the third barrier strip 41 far away from the rotating member 81 is provided with a second sliding part 43, the second sliding part 43 is located in the third sliding groove 62, and the second sliding part 43 and the third barrier strip 41 form a structure with a T-shaped cross section so as to prevent the second sliding part 43 from being separated from the third sliding groove 62.
The rotary member 81 includes a head 811, a first shaft segment 812, a second shaft segment 813, a third shaft segment 814, and a fourth shaft segment 815, which are connected in this order. The end 811 is streamlined and cone-like in shape so as to guide the air flow to the rear side of the rotary member 81. The end 811 is screwed with the first shaft portion 812 to prevent the rotary member 81 from coming off the first sleeve 32. The second shaft section 813 has a diameter smaller than the diameter of the first shaft section 812 and smaller than the diameter of the third shaft section 814. The flexible member 83 may be a steel wire rope or a nylon rope, and is wound around the outer periphery of the second shaft section 813, the first sleeve 32 is provided with a through hole 34, and the flexible member 83 passes through the first sleeve 32 through the through hole 34 and is connected with the slider 82 located in the second chute 31. The diameter of the fourth shaft section 815 is greater than that of the third shaft section 814, the first sleeve 32 and the second sleeve 42 are both sleeved on the periphery of the third shaft section 814, one end of the first sleeve 32 extends to the second shaft section 813, the other end extends to the second sleeve 42, and the second sleeve 42 is limited by a shoulder formed at the joint of the first sleeve 32 and the fourth shaft section 815 and the third shaft section 814, so that the second sleeve 42 is prevented from moving axially. The side of the first sleeve 32 remote from the second sleeve 42 may be axially restrained by a head 811.
As shown in fig. 6, the side of the first barrier 33 far from the third baffle 40 has a protrusion 35, and the protrusion 35 is streamline, which is beneficial to reducing the flow resistance of the air flow, avoiding the abrupt change of the air flow, and guiding the air flow to flow backward more stably.
As shown in fig. 7, a cross-sectional view of the first baffle 30 can be seen, when the housing 6 (i.e. the rotating shaft of the aeroengine) is at a stationary or low rotation speed N0, the slider 82 with a preset weight in the second runner 31 of the first baffle 30 is connected to the rotating member 81 by the non-stretchable flexible member 83, the slider 82 is at the position a0, the third baffle 40 and the second baffle 50 are both at the starting position b0, and the third baffle 40 and the second baffle 50 are blocked by the first baffle 30 when viewed in the airflow direction, and the three stages of baffles axially overlap, at this time, a gas flow channel is formed, and the flow area in the housing 6 is the largest.
As shown in fig. 8, it can be seen that when the housing 6 is accelerated from the stationary or low rotational speed N0 to a certain high rotational speed N1, the slider 82 will move from the starting position a0 to the position a1 along the second chute 31 due to the centrifugal force, thereby pulling the rotation member 81 to rotate counterclockwise relative to the housing 6 by the flexible member 83, and the rotation axis of the rotation member 81 coincides with the rotation axis of the housing 6. The rotating member 81 drives the second baffle 50 to move from the position b0 to the position b1, and since the tertiary support plates are all connected through the first flexible blocking member 60 and the second flexible blocking member 70, the third baffle 40 adaptively moves from the position c0 to the position c1 along with the second baffle 50 due to the traction of the second flexible blocking member 70, so that a smooth spiral flow channel is formed between the tertiary baffles. At this time, the oil-gas mixture 13 from the bearing chamber of the engine can only flow along the spiral flow channel, so that certain pressure loss is caused, and the spiral flow channel generates a certain degree of stagnation on the gas flow, so that the pressure in the bearing chamber 11 is increased. As the rotational speed of the housing 6 increases, the centrifugal force to which the slider 82 is subjected increases, the angle θ by which the second baffle 50 rotates increases, and the degree of spiral of the gas flow path formed by the three-stage baffles increases, which results in a lower gas flow capacity and a higher pressurizing effect on the bearing chamber interior 11. Therefore, along with the change of the rotating speed of the rotating shaft of the aero-engine, the oil-gas separation device can adaptively adjust the circulation capacity of the airflow channel, so that the pressure adjusting function of the oil-gas separation device on the bearing cavity inner 11 is realized.
Meanwhile, the adjusting capacity of the spiral channel can be adjusted by adjusting the axial distances D1 and D2 between the three-stage baffles. The smaller the axial distances D1 and D2, the more pronounced the pressure regulating capability for the same engine speed and vice versa. The maximum pressure adjustment range may be adjusted by changing the maximum rotation angle θ of the second shutter 50.
When the aeroengine 1 rotates at low rotational speeds, the pressure difference between the bearing chamber exterior 10 and the bearing chamber interior 11 is small due to the small pressure of the sealing gas 12 introduced from the compressor for sealing the bearing chamber; when the aero-engine 1 runs at a high speed, the working efficiency of the compressor is improved, the pressure of the sealing gas 12 introduced into the sealing bearing cavity is increased, the pressure difference between the outer part 10 of the bearing cavity and the inner part 11 of the bearing cavity is increased, namely, the pressure difference at the sealing assembly 16 can continuously fluctuate along with the change of the rotating speed of the aero-engine 1, and the adverse effect is generated. After the oil-gas separation device in the embodiment of the invention is adopted, the separation assembly 19 is arranged in the shell 6, and when the aeroengine 1 rotates at a low rotation speed, the better gas circulation capacity of the aeroengine makes the supercharging effect of the bearing cavity not obvious, so that the pressure difference between the outer part 10 of the bearing cavity and the inner part 11 of the bearing cavity is adjusted less; with the rising of the rotation speed of the aero-engine 1, the separation assembly 19 generates a certain degree of supercharging effect on the bearing cavity interior 11 by adaptively adjusting the circulation capacity of the internal airflow spiral channel, so that the pressure difference between the bearing cavity exterior 10 and the bearing cavity interior 11 is basically maintained stable, that is, the pressure difference between the front and the rear of the sealing assembly 16 is not fluctuated along with the change of the rotation speed of the engine.
In addition, three spiral second flow passages 61 with semicircular cross sections are circumferentially formed in the inner wall of the housing 6, and in the flow direction, the depth of the second flow passages 61 is gradually increased, as shown in fig. 5, the second flow passages have a gradient included angle β, so that the lubricating oil 15 at the rear end of the air flow can more smoothly flow back to the bearing cavity interior 11. Meanwhile, in order to increase the driving force of the oil droplet return, the spiral direction of the second flow passage 61 is opposite to the spiral direction of the first flow passage, thereby enhancing the oil return capability of the oil-gas separation device.
When the oil-gas mixture 13 from the bearing cavity inside 11 passes through the spiral first flow passage of the oil-gas separation device, the tangential speed of the gas is increased, and the motion track of the separated gas also moves spirally, so that oil gas in the gas is subjected to larger centrifugal force, and oil drops under the action of the centrifugal force are thrown on the inner wall of the shell 6 due to larger weight, thereby realizing the oil-gas separation function.
In order to enable the oil-gas separation device to adjust the pressure adjusting capability along with the rotation speed of the rotating shaft of the engine, as shown in fig. 9 and 10, a reset device is designed on the third baffle 40, and the reset device of the third baffle 40 comprises a second elastic member 44 arranged in a third chute 62, and the second elastic member 44 can be a spring or rubber. The initial state of the second elastic member 44 is shown in fig. 9, and is a natural non-compressed state; when the third barrier 40 is rotated by the driving force, as shown in fig. 9, the second elastic member 44 is stretched to generate a restoring force against the driving force to the third barrier 40, and when the position of the third barrier 40 is stabilized, the restoring force and the driving force are balanced. When the rotation speed of the engine decreases, the driving force to the third damper 40 also decreases, and the second elastic member 44 generates a restoring force, thereby pulling the third damper 40 back to a new equilibrium position. Thus, the second elastic member 44 of the third barrier 40 cooperates with the driving means to adaptively create a fixed structural state of the oil and gas separator at each engine speed.
The resetting means of the second shutter 50 may be identical to the resetting position of the third shutter 40, for example, a first elastic member is disposed in the first chute 63, and the second shutter 50 is reset and reaches a new balance by the first elastic member, which will not be described in detail herein.
In the embodiment of the invention, the number of stages of the baffles, the number of barrier ribs in each stage of the baffles, the axial distance between each stage of the baffles and the maximum rotation angle of the baffles can be selected in other ways.
Through the explanation of the embodiment of the oil-gas separation device, the embodiment of the invention can be arranged in the axial vent pipe of the engine, and the flow resistance of the spiral first flow passage can be adaptively adjusted according to the rotating speed of the engine so as to control the flow area in the axial vent pipe, thereby changing the pressure in the bearing cavity; meanwhile, the spiral flow passage increases the circumferential tangential velocity of the air flow, so that oil drops in the air can be effectively separated by utilizing centrifugal force and are thrown to the inner wall surface of the rotating shaft, and then are conveyed back into the bearing cavity through the reverse spiral oil return groove of the opposite spiral passage.
By adopting the oil-gas separation device, the pressure difference of the bearing cavity sealing device can be basically maintained at a fixed value under different rotating speeds of the engine, the working condition of the sealing device is greatly optimized, the working life of the bearing cavity sealing device can be prolonged, and the risk of ignition and lubricating oil leakage of the bearing cavity is effectively reduced. Meanwhile, as the rotation speed of the engine increases, the oil-gas separation effect of the spiral channel is more remarkable, so that the efficient recovery of the lubricating oil in the oil gas can be effectively realized, and the lubricating oil consumption rate of the engine is greatly reduced.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same; while the invention has been described in detail with reference to the preferred embodiments, those skilled in the art will appreciate that: modifications and equivalents of the features disclosed herein may be made to the specific embodiments of the invention or to parts of the features may be substituted without departing from the principles of the invention, and such modifications and equivalents are intended to be encompassed within the scope of the invention as claimed.
Claims (14)
1. An oil-gas separation device, comprising:
A rotatable housing (6), a first cavity being provided in the housing (6), the first cavity having an inlet and an outlet; and
The multistage baffles are arranged in the first cavity and are arranged along the axial direction of the shell (6), the multistage baffles form a spiral first flow passage, the flow resistance of the first flow passage changes along with the change of the rotating speed of the shell (6), and the oil-gas mixture (13) realizes oil-gas separation in the first flow passage;
The multistage baffle comprises a first baffle (30) and a second baffle (50), wherein the first baffle (30) is connected with the inner wall of the shell (6) relatively fixedly, the second baffle (50) is connected with the inner wall of the shell (6) and can rotate relative to the first baffle (30) so as to change the position of the second baffle (50) relative to the first baffle (30) in the circumferential direction, and then the flow resistance of the first flow channel is regulated.
2. The oil and gas separation device according to claim 1, characterized in that a side of the first baffle plate (30) close to the inlet is provided with an annular protrusion (35) protruding in a direction close to the inlet, the protrusion (35) being configured as a streamline.
3. The oil and gas separation device according to claim 1, characterized in that the inner wall of the housing (6) is provided with a first chute (63) extending in the circumferential direction, the end of the second baffle (50) is provided with a first sliding part (52), and the first sliding part (52) is arranged in the first chute (63).
4. A gas and oil separator device according to claim 3, further comprising a first resilient member arranged in the first chute (63) for resetting the second baffle (50).
5. The oil and gas separation device according to claim 1, characterized in that the multiple stages of baffles further comprise a third baffle (40), the third baffle (40) being connected to the inner wall of the housing (6) and being rotatable with respect to the first baffle (30), the third baffle (40) being arranged between the first baffle (30) and the second baffle (50).
6. The oil and gas separation device of claim 5, further comprising a first flexible barrier (60) and a second flexible barrier (70), the first flexible barrier (60) being connected between the first baffle (30) and the third baffle (40), the second flexible barrier (70) being connected between the second baffle (50) and the third baffle (40).
7. The oil and gas separation device of claim 1, further comprising a drive device configured to drive the second baffle (50) in rotation relative to the first baffle (30).
8. The oil-gas separation device according to claim 7, wherein the driving device comprises a rotating member (81), a sliding block (82) and a flexible member (83), wherein the rotating member (81) is arranged in the first cavity, the second baffle (50) is relatively fixedly connected with the rotating member (81), the first baffle (30) is rotatably connected with the rotating member (81), a second sliding groove (31) extending along the radial direction is arranged in the first baffle (30), the sliding block (82) is slidably arranged in the second sliding groove (31), one end of the flexible member (83) is connected with the sliding block (82), and the other end of the flexible member (83) is connected with the rotating member (81).
9. The oil and gas separation device according to claim 8, characterized in that the rotating member (81) is provided with circumferentially arranged grooves in which the flexible member (83) is wound.
10. The oil and gas separation device according to claim 8, characterized in that the end of the rotating member (81) near the end of the inlet is configured as a streamline.
11. The oil and gas separation device according to any one of claims 1-10, characterized in that each stage of the baffle plate comprises at least two bars, at least two bars being arranged in the circumferential direction of the housing (6).
12. The oil-gas separation device according to any one of claims 1-10, characterized in that the inner wall of the housing (6) is provided with a spiral-shaped second flow channel (61), through which second flow channel (61) the separated oil (15) flows back, the spiral direction of the second flow channel (61) being opposite to the spiral direction of the first flow channel.
13. The oil and gas separation device according to claim 12, characterized in that the depth of the second flow channel (61) increases gradually in the flow direction of the oil (15).
14. An aeroengine (1), characterized by comprising a rotating shaft as the housing (6) and an oil-gas separation device as claimed in any one of claims 1 to 13.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110264198.4A CN115069027B (en) | 2021-03-11 | 2021-03-11 | Oil-gas separation device and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110264198.4A CN115069027B (en) | 2021-03-11 | 2021-03-11 | Oil-gas separation device and aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115069027A CN115069027A (en) | 2022-09-20 |
| CN115069027B true CN115069027B (en) | 2024-04-26 |
Family
ID=83241005
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110264198.4A Active CN115069027B (en) | 2021-03-11 | 2021-03-11 | Oil-gas separation device and aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115069027B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117101313B (en) * | 2023-08-24 | 2024-05-07 | 中国航发燃气轮机有限公司 | Oil mist separator and gas turbine thereof |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4561867A (en) * | 1983-12-14 | 1985-12-31 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Apparatus for separating a liquid from a gas, particularly for turboengine bearing cases |
| JPH04234512A (en) * | 1990-12-29 | 1992-08-24 | Suzuki Motor Corp | Oil separator structure for engine |
| CN102348871A (en) * | 2009-03-10 | 2012-02-08 | 蒂森克虏伯普雷斯塔技术中心股份公司 | Hollow body comprising an integrated oil separator unit |
| CN102872982A (en) * | 2012-10-08 | 2013-01-16 | 中国航空动力机械研究所 | Oil gas separation device |
| CN106975576A (en) * | 2017-02-24 | 2017-07-25 | 宁波神通模塑有限公司 | A kind of adjustable cyclonic separator |
| CN108204281A (en) * | 2016-12-20 | 2018-06-26 | 中国航发商用航空发动机有限责任公司 | Gs-oil separator, oil and gas separating system and aero-engine |
| CN208918624U (en) * | 2018-10-26 | 2019-05-31 | 常熟塑擎汽车零部件有限公司 | A kind of gas-oil separation device of automobile engine |
| WO2020026407A1 (en) * | 2018-08-02 | 2020-02-06 | 東京濾器株式会社 | Oil separator |
| CN110917734A (en) * | 2019-12-05 | 2020-03-27 | 中国航发四川燃气涡轮研究院 | Centrifugal impeller type ventilator and gear box |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016088725A1 (en) * | 2014-12-02 | 2016-06-09 | 株式会社 横田製作所 | Gas-liquid separation device |
-
2021
- 2021-03-11 CN CN202110264198.4A patent/CN115069027B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4561867A (en) * | 1983-12-14 | 1985-12-31 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Apparatus for separating a liquid from a gas, particularly for turboengine bearing cases |
| JPH04234512A (en) * | 1990-12-29 | 1992-08-24 | Suzuki Motor Corp | Oil separator structure for engine |
| CN102348871A (en) * | 2009-03-10 | 2012-02-08 | 蒂森克虏伯普雷斯塔技术中心股份公司 | Hollow body comprising an integrated oil separator unit |
| CN102872982A (en) * | 2012-10-08 | 2013-01-16 | 中国航空动力机械研究所 | Oil gas separation device |
| CN108204281A (en) * | 2016-12-20 | 2018-06-26 | 中国航发商用航空发动机有限责任公司 | Gs-oil separator, oil and gas separating system and aero-engine |
| CN106975576A (en) * | 2017-02-24 | 2017-07-25 | 宁波神通模塑有限公司 | A kind of adjustable cyclonic separator |
| WO2020026407A1 (en) * | 2018-08-02 | 2020-02-06 | 東京濾器株式会社 | Oil separator |
| CN208918624U (en) * | 2018-10-26 | 2019-05-31 | 常熟塑擎汽车零部件有限公司 | A kind of gas-oil separation device of automobile engine |
| CN110917734A (en) * | 2019-12-05 | 2020-03-27 | 中国航发四川燃气涡轮研究院 | Centrifugal impeller type ventilator and gear box |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115069027A (en) | 2022-09-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7293955B2 (en) | Supersonic gas compressor | |
| EP3018355B1 (en) | Adjustable-trim centrifugal compressor, and turbocharger having same | |
| CN105626239B (en) | Adjustable TRIM centrifugal compressor with valve cover and turbocharger with adjustable TRIM centrifugal compressor | |
| KR101021827B1 (en) | Centrifugal compressor | |
| US8932091B2 (en) | Propulsion system | |
| CN104968944A (en) | Centrifugal compressor | |
| CN115069027B (en) | Oil-gas separation device and aeroengine | |
| CN102257276A (en) | Scroll fluid machine | |
| WO2019174497A1 (en) | Magnetic levitation compressor | |
| JP2016522357A (en) | Centrifugal rotor | |
| US20160160834A1 (en) | Hydraulic machine | |
| KR20190070497A (en) | Turbocharger for vehicle | |
| US9784376B2 (en) | Check valve assembly | |
| US20040151579A1 (en) | Supersonic gas compressor | |
| EP2851569B1 (en) | Gas turbine engine with vortex fluid flow device | |
| US11603859B2 (en) | Variable geometry turbine and supercharger | |
| CN114837813B (en) | Gas turbine engine and bearing cavity pressure adjusting device thereof | |
| CN102628446B (en) | Centrifugal vacuum pump and the method for producing negative pressure | |
| KR20190105792A (en) | Turbo compressor | |
| CN208486918U (en) | A kind of nozzle assembly aperture ring driving structure | |
| US20220333498A1 (en) | Turbine | |
| CN208138006U (en) | Vehicle and its turbocharger | |
| GB2332242A (en) | A pitot tube pump | |
| Lawlor et al. | Supersonic gas compressor | |
| JPH0120319B2 (en) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |