Pipeline type centrifugal ventilation oil-gas separation device for aero-engine and application

Abstract

The invention discloses a pipeline type centrifugal ventilation oil-gas separation device for an aero-engine and application. The pipeline type centrifugal ventilation oil-gas separation device comprises a mounting base which is fixed to an engine rotating shaft and rotates along with the engine rotating shaft. The annular rectifying section is coaxially arranged on the mounting seat and is used for secondary centrifugal separation; the inlet sections are uniformly distributed on the outer wall of the rectifying section in the circumferential direction, extend in the radial direction and are used for guiding an oil-gas mixture to enter and implementing primary centrifugal separation; and the axial outlet section is coaxially arranged at the center of the rectifying section and is used for discharging separated gas. During working, an oil-gas mixture is primarily separated through the inlet section, and separated lubricating oil is reversely discharged; the airflow enters the rectifying section for secondary separation, and the separated lubricating oil is also collected and guided back to the inlet section to be discharged; purified gas flows into the outlet section through a branch pipeline communicated with the outlet section on the inner side of the rectifying section and is discharged out of the device. By means of the optimized pipeline type structure and the two-stage centrifugal separation principle, high separation efficiency and low pressure drop are achieved, and the two-stage centrifugal separator is suitable for aero-engines.

Description

Technical Field

[0001] The present invention belongs to the technical field of lubrication and ventilation of aero-engines, and relates to the optimized design of an oil-gas separation and ventilation structure. In particular, it relates to a pipe-type centrifugal ventilation oil-gas separation device for an aero-engine and its application, which can achieve efficient centrifugal separation of an oil-gas mixture and significantly reduce the system pressure drop. Background Art

[0002] In an aero-gas turbine engine, the lubrication system forms a key component, which shoulders the important task of providing lubrication for key components such as the high and low pressure rotor pivot bearings and transmission gears of the engine. As an important branch of the lubrication system, the ventilation and separation system mainly functions to effectively discharge the oil-gas mixture in the oil sump to the outside of the engine and separate the oil and gas on this basis. In this process, the lubricating oil is recycled back to the bearing cavity to maintain recycling, while the gas is discharged to the outside. As one of the core components of the lubrication system, the centrifugal ventilator functions to effectively discharge and separate the oil-gas mixture formed in the bearing cavity, and guide the oil back to the bearing cavity through its structure. Its performance directly affects the amount of lubricating oil discharged to the outside by the engine per unit time. Given the limited lubricating oil reserve of an aero-engine, if the lubricating oil loss per unit time is too high, it will inevitably shorten the stable operation period of the engine, thus having a negative impact on the maximum flight distance of the aircraft.

[0003] The existing centrifugal ventilators for aero-engines are mainly divided into two types: radial plate type and porous medium type. Among them, the radial plate type centrifugal ventilator (such as Chinese invention patents CN116832533A, CN103485895B, etc.) relies on the rotating radial plates to generate centrifugal force to throw the oil droplets in the oil-gas mixture to the periphery to achieve oil-gas separation. However, due to its structure, the radial plate has a smaller specific volume under the same volume, resulting in a larger volume of the radial plate type centrifugal ventilator. At the same time, due to the frequent flow direction changes and local blockages caused by the flow of the oil-gas mixture around the radial plates, the fluid resistance increases and the pressure drop rises significantly, thus reducing the system ventilation efficiency and increasing the load and power consumption of the engine. The porous medium type centrifugal ventilator (such as Chinese utility model patents CN205422872U, CN204532551U, etc.) separates the oil and gas by means of the complex microporous network in the high-porosity medium (such as metal foam, porous ceramics, etc.). The oil droplets are captured and recycled by multiple collisions, diffusion, and inertial deposition in the micropores, and the gas penetrates through the porous layer and is discharged out of the system. Although the porous medium type centrifugal ventilator has a larger specific volume, due to its relatively dense porous medium area, the pressure drop is large, which is not conducive to energy conservation and emission reduction of aero-engines. At the same time, due to material limitations, the porous medium has complex manufacturing processes, high costs, difficult maintenance, and is prone to performance degradation due to pollution and blockage during long-term use.

[0004] Aeroengines for today's drones and other aircraft are subject to size constraints and extremely stringent requirements for lightweighting and low energy consumption. Consequently, the centrifugal blowers they require must be smaller, offer higher separation efficiency, and minimize pressure drop. However, commonly used radial plate and porous media centrifugal blowers require a trade-off between size, separation efficiency, and pressure drop. For example, they sacrifice pressure drop for separation efficiency, or reduce separation effectiveness to minimize structural complexity and manufacturing difficulty. This results in overall system performance failing to meet practical application requirements.

[0005] In summary, existing centrifugal ventilator technology for aircraft engines struggles to balance high separation efficiency, low pressure drop, and compact size. This makes it difficult to fully meet the urgent demands of new aircraft engines, particularly those for drones, for high performance, lightweight design, and long flight times. Therefore, developing a new centrifugal ventilator that can significantly reduce pressure drop and size while maintaining high separation efficiency is a pressing technical challenge in the field of aircraft engine lubrication and ventilation technology. Summary of the Invention

[0006] (1) Purpose of the invention In response to the above-mentioned defects and deficiencies in the prior art, the present invention aims to provide a pipeline-type centrifugal ventilation oil-gas separation device and its application for aircraft engines. It adopts a regular pipeline configuration to replace the traditional radial plate and porous medium designs, and innovatively introduces a rectifying section composed of an annular chamber to achieve secondary separation of oil and gas. While ensuring efficient separation performance, it significantly reduces the airflow pressure drop, improves the system operation stability and ventilation efficiency. The device has a compact structure and is suitable for aircraft engine systems such as drones with limited space. The whole device adopts one-piece casting, which has good manufacturing processability and high speed strength adaptability. It achieves an optimized balance between high separation efficiency, low pressure drop and structural strength in a limited space, and improves the reliability and economy of the aircraft engine lubrication system.

[0007] (2) Technical solution In order to achieve the purpose of the invention and solve the technical problems, the present invention adopts the following technical solutions: The first object of the present invention is to provide a pipeline-type centrifugal ventilation oil-gas separation device for an aircraft engine, which is used to efficiently separate and discharge the oil-gas mixture in the bearing cavity of the aircraft engine with low resistance. The oil-gas separation device includes: The mounting seat is a cylindrical base or flange structure, the end of which is fixedly connected to the engine rotating shaft and supports the entire device to be arranged in the engine bearing cavity and rotate synchronously with the rotating shaft; The rectifying section is an annular closed chamber structure, one end face of which is coaxially arranged on the mounting seat, and the annular chamber is formed to rectify and perform secondary centrifugal separation on the oil-gas mixture entering therein; The inlet sections are provided in multiple numbers and are circumferentially and uniformly arranged on the outer peripheral wall of the rectifying section. Each inlet section is a hollow tubular structure extending radially. Its outer end inlet communicates with the bearing cavity environment, and its inner end outlet extends to communicate with the annular chamber of the rectifying section. It is used to guide the oil-gas mixture in the bearing cavity into its tubular inner cavity for primary centrifugal separation, and discharge the oil-gas mixture after primary separation into the annular chamber of the rectifying section. Moreover, the lubricating oil secondarily centrifugally separated in the annular chamber of the rectifying section flows back to each inlet section and is discharged from the outer end inlet of each inlet section together with the lubricating oil primarily centrifugally separated in each inlet section; The outlet section is a hollow cylindrical pipe extending axially, and is arranged coaxially with the engine rotating shaft as a whole. Its closed end is concentrically arranged at the center of the rectifying section, and its open end is located downstream of the rectifying section axially and extends outside the bearing cavity to discharge the separated gas. Moreover, a plurality of radially extending branch connecting pipes are circumferentially and uniformly arranged between the outer peripheral wall near the closed end of the outlet section and the inner peripheral wall of the rectifying section. Both ends of each branch connecting pipe communicate with the tubular inner cavity of the outlet section and the annular chamber of the rectifying section respectively.

[0008] The second object of the present invention is to provide an aviation engine lubricating oil ventilation system, including the above-mentioned pipeline-type centrifugal ventilation oil-gas separation device for an aviation engine of the present invention.

[0009] (3) Technical effects Compared with the prior art, the pipeline-type centrifugal ventilation oil-gas separation device for an aviation engine and its application of the present invention have the following beneficial and remarkable technical effects: (1) By providing an inlet section and a rectifying section to form a series-connected two-stage centrifugal separation structure for secondary separation of oil and gas. First, when the oil-gas mixture enters the radially arranged inlet section, it is subjected to the first-stage centrifugal force, and oil droplets with larger diameters are effectively thrown towards the pipe wall and discharged countercurrently to complete the primary separation. Subsequently, the airflow containing fine oil mist enters the annular rectifying section, and under the action of a stronger centrifugal force field and a possible rectifying structure, secondary fine separation is carried out to further capture tiny oil droplets. In addition, the preferably provided gradually decreasing inner diameter structure of the inlet section, the inner wall guide ribs or spiral shallow grooves, and the convergent design of the branch connecting pipes all strengthen the migration, aggregation of oil droplets towards the wall surface and prevent them from entering the next stage or the outlet, jointly ensuring extremely high oil-gas separation efficiency and the cleanliness of the outlet gas.

[0010] (2) By optimizing the structural design, the present invention can ensure a lower pressure drop while maintaining a small size of the system, thereby improving the engine efficiency. The overall device adopts a regular pipeline structure. Compared with traditional complex flow channels or separators containing porous media, the internal flow path is more direct and smooth, significantly reducing the local pressure loss (greatly reducing the elbow loss) caused by a sharp change in flow direction or flowing through high-resistance elements (such as web structures). In particular, the setting of the annular rectifying section not only serves for secondary separation, but also plays an important role in guiding and rectifying the air flow, suppressing the generation of eddy currents and reducing energy dissipation.

[0011] (3) The present invention adopts an integrated casting process, which has high reliability and is easy to cast. The overall device is integrally cast and formed, forming a seamless connection overall structure, avoiding the structural weaknesses and sealing failure risks caused by the connection of multiple components, enhancing the overall rigidity and coaxial rotation stability, and being able to operate stably for a long time under high-speed rotation, high-temperature and high-vibration conditions, meeting the stringent strength and safety requirements of aviation applications. Brief Description of the Drawings

[0012] The accompanying drawings forming a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments and descriptions thereof of the present invention are used to explain the present invention and do not constitute an improper limitation to the present invention. Hereinafter, the embodiments of the present invention will be described in detail with reference to the drawings, wherein: Figure 1 is the orthographic isometric view of the pipeline-type centrifugal ventilation oil-gas separation device of the present invention.

[0013] Figure 2 is the front view of the pipeline-type centrifugal ventilation oil-gas separation device of the present invention.

[0014] Figure 3 is the sectional view taken along the A-A direction of the pipeline-type centrifugal ventilation oil-gas separation device of the present invention.

[0015] Figure 4 is the right view of the pipeline-type centrifugal ventilation oil-gas separation device of the present invention.

[0016] Figure 5 is the pressure distribution diagram of the pipeline-type centrifugal ventilation oil-gas separation device of the present invention.

[0017] Description of the Reference Numerals: Mounting seat 10, rectifying section 20, inlet section 30, inlet end 31, outlet section 40, outlet end 41, branch communication pipeline 42. Detailed Embodiments

[0018] The present invention aims to provide a pipeline-type centrifugal ventilation oil-gas separation device for an aeroengine and its application. To make the purpose, technical solution, and advantages of the implementation of the present invention clearer, the following will describe the technical solution in the embodiments of the present invention in more detail with reference to the accompanying drawings in the embodiments of the present invention. The described embodiments are part of the embodiments of the present invention, not all of them, and the described embodiments are exemplary and are intended to explain the present invention, but should not be construed as a limitation to the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0019] Embodiment 1: Overall Structure As Figures 1 to 4 shown, the pipeline-type centrifugal ventilation oil-gas separation device for an aeroengine provided in the embodiment of the present invention is used for efficiently separating and low-resistance discharging the oil-gas mixture in the bearing cavity of the aeroengine. The whole oil-gas separation device is integrally formed by casting with aluminum alloy material, forming a seamless connected overall structure, and mainly consists of four parts: a mounting seat 10, a rectifying section 20, an inlet section 30, and an outlet section 40. This integrated structure not only simplifies the subsequent assembly process, reduces the leakage risk and stress concentration problems that may be caused by the existence of the connection interface, but also significantly improves the overall structural strength, rigidity, and operational stability and durability of the device under high-speed rotation, high vibration, and complex temperature stress environments, and is particularly suitable for the harsh working conditions of aeroengines. At the same time, the selection of aluminum alloy material makes the device have a lower mass and higher strength, meeting the dual requirements of aeroengines for lightweight and high strength.

[0020] In the embodiment of the present invention, the mounting seat 10 is generally in the shape of a cylindrical base or flange structure, and its mounting end face is provided with a plurality of mounting holes evenly distributed in the circumferential direction for connecting and fixing with the bearing cavity of the aeroengine. And a central positioning hole is provided at the center of the bottom surface of the mounting seat for coaxial positioning with the engine rotating shaft and transmitting rotational power, ensuring the coaxiality and dynamic balance of the device under high-speed rotation.

[0021] In the embodiment of the present invention, the rectifying section 20 is generally in the shape of an annular closed chamber structure, and one of its end faces is coaxially arranged on the mounting seat 10, and its annular chamber is formed to rectify and secondarily centrifugally separate the oil-gas mixture entering it. Preferably, the annular chamber of the rectifying section 20 has a circumferentially continuous and smooth inner wall structure, and is provided with a streamlined guiding rib or groove array for adjusting the internal pressure gradient distribution to improve the rotational rectification process of the oil-gas mixture therein, reduce local eddy currents and pressure losses, and thus improve the stability of the secondary separation.

[0022] In the embodiment of the present invention, a plurality of inlet sections 30 are arranged and evenly distributed circumferentially on the outer peripheral wall of the rectifying section 20. Each inlet section 30 is a hollow tubular structure extending radially. Its outer end inlet is communicated with the bearing cavity environment, and its inner end outlet extends to be communicated with the annular chamber of the rectifying section 20, for guiding the oil-gas mixture in the bearing cavity into its tubular inner cavity to achieve primary centrifugal separation, and discharging the oil-gas mixture after primary separation into the annular chamber of the rectifying section 20. Moreover, the lubricating oil secondarily centrifugally separated in the annular chamber of the rectifying section 20 flows back to each inlet section 30 and is discharged from the outer end inlet of each inlet section together with the lubricating oil primarily centrifugally separated in each inlet section.

[0023] Preferably, the number of the inlet sections 30 is set to be 6 to 12. Each inlet section is discretely arranged at equal intervals in the circumferential direction along the outer peripheral wall of the rectifying section 20, so that the device provides sufficient oil-gas mixture inlet channels while maintaining a compact volume, reduces the flow imbalance phenomenon through uniform distribution, and ensures reasonable inlet resistance and flow distribution at the same time. In addition, the inner cavity of each inlet section 30 is preferably set to have a gradually decreasing inner diameter structure from its inlet end 31 to its outlet end, so as to increase the collection efficiency of the oil-gas mixture and reduce the local flow resistance at the inlet; and the inner wall of each inlet section 30 is provided with a guiding rib extending axially or a shallow groove guiding structure arranged in a spiral direction, so as to increase the disturbance of the oil-gas mixture during its flow in the inlet section, strengthen the migration, collision and aggregation of oil droplets towards the pipe wall under the action of centrifugal force, improve the effect of primary centrifugal separation, and help to form a stable liquid film flow, promoting the backflow and discharge of the separated lubricating oil along the pipe wall.

[0024] In the embodiment of the present invention, the outlet section 40 is a hollow cylindrical pipe extending axially, and is arranged coaxially with the engine rotating shaft as a whole. Its closed end is concentrically arranged at the center of the rectifying section 20. Its outlet end 41 is located downstream of the rectifying section 20 in the axial direction and extends outside the bearing cavity to discharge the separated gas. And a plurality of branch connecting pipes 42 extending radially are evenly distributed circumferentially between the outer peripheral wall near the closed end of the outlet section 40 and the inner peripheral wall of the rectifying section 20. Both ends of each branch connecting pipe 42 are respectively communicated with the tubular inner cavity of the outlet section 40 and the annular chamber of the rectifying section 20.

[0025] Preferably, there are 3 to 8 branch connecting pipes 42 arranged at equal circumferential intervals between the outlet section 40 and the rectifying section 20. Each branch connecting pipe 42 extends radially and is respectively communicated with the annular chamber of the rectifying section 20 and the hollow tubular cavity of the outlet section 40 to ensure multi-point pressure equalized transportation, improve the uniformity of gas discharge and the ventilation efficiency of the system. In addition, the inner diameter or the effective flow cross-sectional area of each branch connecting pipe 42 preferably gradually decreases from the rectifying section 20 to the outlet section 40, forming a converging flow channel as a whole, so as to throw the tiny oil droplets that may be entrained in the air flow and have not been completely separated to the wall surface of the branch connecting pipe 42 and prevent them from entering the outlet section 40, and contribute to optimizing the flow pattern of the air flow from the rectifying section 20 to the outlet section 40, reducing the generation of local eddy currents and energy dissipation, and reducing the local resistance loss when the air flow passes through.

[0026] Preferably, the axis of the hollow tubular cavity of the outlet section is coaxially arranged with the engine rotation axis, and the open end extending outside the bearing cavity is formed into an outward-expanded structure to reduce the flow resistance when the gas is discharged. At the same time, a reinforcing rib structure is provided on the outer wall of the pipe to enhance the rigidity and vibration stability of the pipe under the high-speed rotation state and prevent the pipe from deforming due to centrifugal force.

[0027] When the pipe-type centrifugal ventilation oil-gas separation device of the embodiment of the present invention is working, the oil-gas mixture enters the device from the inlet end 31, flows through the inlet section 30, the rectifying section 20, and the outlet section 4o in sequence, and finally flows out through the outlet end 41. The oil and gas are separated at the first stage in the inlet section 30 and at the second stage in the rectifying section 20. The separated oil is discharged from the inlet end 31 to realize oil-gas separation. The centrifugal oil-gas separation device as a whole rotates around the engine rotation axis. In addition, the pipe-type centrifugal ventilation oil-gas separation device of the present invention improves the strength by adopting integral casting, reduces the inlet and outlet pressure drops by reducing the number of elbows, and meets the strength design requirements.

[0028] The working principle of the pipe-type centrifugal ventilation oil-gas separation device for an aeroengine of the present invention is as follows: When the aeroengine is in a normal operating state, the lubrication system continuously transports lubricating oil to key parts such as the bearing cavity to meet the cooling and lubrication requirements. During this process, a large amount of oil-gas mixture is generated in the bearing cavity due to high temperature, high pressure and the agitation of lubricating oil by high-speed rotation of parts. The centrifugal oil-gas separation device arranged in the bearing cavity is installed on the engine rotation axis through its mounting seat 10 and rotates synchronously at a high speed with the aeroengine rotation axis. The oil-gas mixture enters from the inlet end 31 of the device under the action of the pressure difference, flows through the inlet section 30, the rectifying section 20, and the outlet section 40 and flows out through the outlet end 41. The separated oil is discharged from the inlet and recycled by the bearing cavity.

[0029] Specifically, the oil-gas mixture fluid first enters the interior of the device through the inlet ends 31 of a plurality of inlet sections 30 evenly distributed on the outer peripheral wall of the rectifying section 20. After the oil-gas mixture enters the tubular inner cavity of the inlet section 30 extending radially (or at a specific angle), under the action of centrifugal separation, the heavier lubricating oil droplets are thrown towards the tube wall of the inlet section 30, forming an oil film and flowing along the wall surface. According to the design, this part of the lubricating oil initially separated will flow upstream along the inner wall of the inlet section 30 (opposite to the gas flow direction), and finally be discharged through its inlet end 31 and returned to the bearing cavity.

[0030] After the primary separation in the inlet section 30, the gas-liquid mixture still containing finer oil mist continues to flow inward and enters the annular closed chamber of the rectifying section 20 from the inner end outlet of the inlet section 30. Inside the rectifying section 20, the gas flow is further rectified and subjected to a stronger secondary centrifugal separation effect. Due to the annular structure of the rectifying section 20 and continuous high-speed rotation, the remaining tiny oil droplets are again effectively thrown towards the outer peripheral wall of the rectifying section 20 and converge on the wall surface. This part of the lubricating oil separated secondarily will, according to the design, flow along the wall surface of the rectifying section 20 and finally be guided to the return path and also returned to each inlet section 30 for discharge.

[0031] After two-stage high-efficiency centrifugal separation, the gas with a smaller density and relatively pure is gathered in the inner region of the rectifying section 20 close to the rotation center. Subsequently, these clean gases flow radially inward through a plurality of branch connecting pipes 42 evenly arranged circumferentially between the inner peripheral wall of the rectifying section 20 and the outer peripheral wall of the outlet section 40 into the hollow tubular inner cavity of the outlet section 40 located at the center of the device.

[0032] Finally, the separated gas flows along the axial channel of the outlet section 40, is discharged from the outlet end 41 of the oil-gas separation device, enters the overall ventilation system of the engine, and is finally led out of the engine or subjected to subsequent treatment. In this way, through a compact pipe-type design and the principle of multi-stage centrifugal separation, the efficient and continuous separation of the oil-gas mixture in the bearing cavity of the aero-engine is achieved.

[0033] In addition, it should be noted that in the pipe-type centrifugal oil-gas separation device of the present invention, there is no porous medium structure or web structure along the air flow direction to cause local resistance loss in the flow, and at the same time, there is a longer effective distance along the radial direction for oil-gas separation. Moreover, the overall structure of the present invention is simple and regular, and can be directly integrally cast, thereby reducing the casting cost and improving its strength.

[0034] The pipe-type centrifugal oil-gas separation device of the present invention is internally provided with a rectification area (i.e., the rectification section 20 in the form of an annular closed chamber structure). The rectification area is connected to the inlet section 30 and the outlet section 40, and can guide and rectify the air flow, reduce the eddy current and pressure loss generated by the sudden change of the air flow direction, and reduce the frictional loss of the small air flow, thereby improving the overall efficiency of oil-gas separation. The rectification section 20 is arranged between the inlet section 30 and the outlet section 40, is concentric with the inlet section 30 and the outlet section 40, and each inlet is connected to the rectification section. There are three pipes connecting the rectification section and the outlet section, and the three pipes are arranged equidistantly and concentrically along the rotation axis. The pipe-type centrifugal oil-gas separation device of the present invention reduces the pressure difference between the inlet and the outlet in a way that greatly reduces the elbow loss, so as to meet the requirements of improving the separation efficiency while controlling the pressure drop, and meet the strength design requirements, and has the advantages of good separation effect and small pressure difference between the inlet and the outlet.

[0035] Example 2: Specific design parameters and performance verification Based on the overall structural design, preferred features and working principle of the pipe-type centrifugal ventilation oil-gas separation device for aeroengines described in Example 1, this Example 2 aims to further illustrate the practical application feasibility and engineering effectiveness of the technical solution of the present invention in aeroengines by providing a set of specific key geometric dimension parameters and preset simulated operating conditions.

[0036] In this Example 2, the hydraulic diameter of each inlet section 30 is set to 5.5 mm, and the total hydraulic diameter of 10 inlet sections 30 is 55 mm. The hydraulic diameter of the outlet section 40 is set to 13.71 mm. The internal fluid is an oil-gas mixture (the main components are air and lubricating oil, and the proportion of lubricating oil is less than 10%). The fluid temperature is 20 °C, and the fluid inlet flow rate is 1.58 m / s. Under these parameter settings and operating conditions, as Figure 5 shown, the internal flow field of the centrifugal oil-gas separation device is simulated and calculated by CFD. It can be clearly observed from Figure 5 that the total pressure is the highest in the outer end inlet area of each inlet section 30 (shown as red and orange areas in the figure, with the value in the range of about 60,000 - 67,685 Pa), which conforms to the initial state of the fluid entering the pipe. Along the flow path of the oil-gas mixture, that is, from the inlet section 30 through the rectification section 20 (green and yellow areas in the figure, with the pressure in the range of about 41,000 - 60,000 Pa), and finally reaching the outlet section 40 (blue area in the figure, about 30,000 Pa), the total pressure shows an obvious and gradually decreasing trend. At the end of the outlet section 40, the total pressure reaches the lowest value (dark blue area in the figure, about 30,000 Pa). The total pressure drop between the inlet and the outlet of the whole device (dropping from about 67,685 Pa to about 30,000 Pa) is effectively controlled within a reasonable range.

[0037] Comprehensive CFD simulation results analysis shows that for the pipe-type centrifugal oil-gas separation device for aero-engines of the present invention, there is no significant pressure drop mutation area in the entire oil-gas channel, indicating that the device has low flow resistance characteristics while maintaining high separation efficiency, meeting the low-pressure loss design principle. Combining the simulation analysis, it is verified that the device operates stably under typical working conditions, has high separation efficiency, and small pressure difference between the inlet and outlet, and is particularly suitable for the lubrication system of aero-engines with compact structure and high efficiency requirements.

[0038] Through the above embodiments, the object of the present invention is completely and effectively achieved. Those skilled in the art can understand that the present invention includes but is not limited to the content described in the drawings and the above specific embodiments. Although the present invention has been described with respect to the currently considered most practical and preferred embodiments, it should be understood that the present invention is not limited to the disclosed embodiments, and any modifications that do not deviate from the functional and structural principles of the present invention will be included in the scope of the claims.

Claims

1. A pipeline-type centrifugal ventilation oil-gas separation device for an aeroengine, characterized in that, Comprising: A mounting base, in the structure of a cylindrical base or a flange, whose end is fixedly connected to the engine rotating shaft, and supports the whole device to be arranged in the engine bearing cavity and rotate synchronously with the rotating shaft; A rectifying section, in the structure of an annular closed chamber, one end face of which is coaxially arranged on the mounting base, and its annular chamber is formed to rectify and secondarily centrifugally separate the oil-gas mixture entering therein; Inlet sections, which are provided in a plurality and are circumferentially and evenly distributed on the outer peripheral wall of the rectifying section. Each inlet section is in the structure of a hollow tubular shape extending radially. Its inlet end communicates with the bearing cavity environment, and its outlet end extends to communicate with the annular chamber of the rectifying section, and is used to guide the oil-gas mixture in the bearing cavity into its tubular inner cavity to achieve primary centrifugal separation, and discharge the separated oil-gas mixture into the rectifying section; An outlet section, in the structure of a hollow cylindrical pipe extending axially, is integrally arranged coaxially with the engine rotating shaft. Its closed end is concentrically arranged at the center of the rectifying section. Its open end is axially located downstream of the rectifying section and extends outside the bearing cavity to discharge the separated gas. And there are a plurality of radially extending branch connecting pipes circumferentially and evenly arranged between the outer peripheral wall near the closed end of it and the inner peripheral wall of the rectifying section. The two ends of each branch connecting pipe are respectively communicated with the hollow tubular inner cavity of the outlet section and the annular chamber of the rectifying section.

2. The pipe-type centrifugal ventilation oil-gas separation device for an aero-engine according to claim 1, wherein: The mounting base, the rectifying section, the inlet sections and the outlet section are integrally cast and formed from an aluminum alloy material, forming a seamless connected integral structure.

3. The pipeline type centrifugal ventilation oil-gas separation device for an aeroengine according to claim 1, wherein: The number of the inlet sections is set to be 6 to 12, and each inlet section is discretely arranged at equal circumferential intervals along the circumferential direction of the outer peripheral wall of the rectifying section.

4. The pipe-type centrifugal ventilation oil-gas separation device for an aeroengine according to claim 1 or 3, characterized in that: The tubular inner cavity of each inlet section is in an overall structure with a gradually decreasing inner diameter from its inlet end to its outlet end, and the inner wall surface of each inlet section is provided with a flow guiding rib extending axially or a shallow groove flow guiding structure arranged in a spiral direction, so as to increase the disturbance when the oil-gas mixture flows in the inlet section.

5. The pipeline-type centrifugal ventilation oil-gas separation device for an aeroengine according to claim 1, wherein: The annular chamber of the rectifying section has an inner wall structure that is continuously smooth in the circumferential direction, and is provided with a streamline guiding rib or a groove array for adjusting the internal pressure gradient distribution.

6. The pipeline-type centrifugal ventilation oil-gas separation device for an aeroengine according to claim 1, characterized in that: There are 3 to 8 branch connecting pipes arranged at equal circumferential intervals between the outlet section and the rectifying section. Each branch connecting pipe extends radially and is respectively communicated with the annular chamber of the rectifying section and the hollow tubular cavity of the outlet section.

7. The pipeline-type centrifugal ventilation oil-gas separation device for an aeroengine according to claim 1 or 6, characterized in that: The inner diameter or the effective flow cross-sectional area of each branch connecting pipe gradually decreases from the rectifying section to the outlet section direction, and an overall convergent flow channel is formed.

8. The pipeline-type centrifugal ventilation oil-gas separation device for an aeroengine according to claim 1, characterized in that: The axis of the outlet section is coaxially arranged with the engine rotating shaft, and its open end extending outside the bearing cavity is formed into an outward expanding structure, and at the same time, a reinforcing rib structure is provided on the outer wall of the pipe.

9. The pipe-type centrifugal ventilation oil-gas separation device for an aeroengine according to claim 1, characterized in that: A plurality of mounting holes are circumferentially and evenly arranged on the cylindrical base or the flange of the mounting base, which are used for reliably fixedly connecting with the aeroengine bearing cavity, and a central positioning hole is provided at the center of the bottom surface of the mounting base, which is used for coaxial positioning with the engine rotating shaft and transmitting rotational power.

10. An aero-engine lubricating oil ventilation system, characterized in that, Including the pipe-type centrifugal ventilation oil-gas separation device for an aeroengine according to any one of the above claims 1 to 9.

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